Gregorio Zaltzman D'Ambrosio | Aerospace Engineering

DATA BLOCK 01

Skills

Software & CAD

SolidWorks SolidWorks Flow Simulation OpenVSP AVL XFLR5 XFOIL Fusion 360 STK (Systems Tool Kit) Technical Drawings & CAD Assemblies

Analysis & Simulation

MATLAB Python Aerodynamic Sizing & Trade Studies Constraint Analysis Drag Build-Up Methods VLM / Low-Fidelity Aero Tools Stability & Static Margin Controls Fundamentals (Signals & Systems) Thin-Walled Structures (Shear Flow) FEA Fundamentals

Hardware & Lab

Arduino IDE Sensor Instrumentation (lab-scale) Data Logging & Post-Processing Experimental Heat Transfer Rapid Prototyping RC Aircraft Integration Support Flight Test Support (student team)

DATA BLOCK 02

Timeline

Sep 2022

UC San Diego — B.S.c Aerospace

Commenced a Bachelor of Science in Aerospace Engineering, building a rigorous theoretical foundation. Completed extensive core coursework spanning Fluid Dynamics, Solid Mechanics, Thermodynamics, Aerospace Structures, Propulsion, Orbital Mechanics, Linear Control, and Engineering Experimental Techniques, bridging theoretical mathematics with applied aerospace physics.

Sep 2023

ITS Service Desk Technician

Service Desk technician, worked extensively to resolve campus-wide technical issues and improved support workflows. Also collaborated with other ITS teams to help increase support efficiency and improve quality of service for customers.

May 2025

Promoted — Service Desk Lead

Helped lead a 60+ member technician team, overseeing daily campus-wide IT operations, complex troubleshooting, and cross-departmental coordination. Drove long-term organizational growth by facilitating staff training, supporting the hiring pipeline, managing documentation.

Jun 2025

RPL at UCSD

Supported the design, build, and launch of a G-class model rocket (~2,100 ft), contributing to assembly, CAD support, testing preparation, and team design discussions while gaining exposure to rocket stability, avionics integration, and flight performance analysis.

Sep 2025

Design-Build-Fly (DBF)

Collaborated on the Aerodynamics and Structures subteams for a competition-scale RC aircraft. Drove performance-based design trade studies by assisting with airfoil selection, configuration optimization, structural sizing, and CAD modeling, translating theoretical engineering analysis into a manufactured flight-ready vehicle.

Present

Senior Design Capstone

Serving as Chief Engineer for an ultra-efficient Blended Wing Body commercial airliner concept. Leading cross-functional efforts spanning gradient-free aerodynamic optimization, unconventional structural layout, aft-propulsion integration, direct operating cost analysis, and dynamic stability, culminating in a fully verified 3D CAD model.

DATA BLOCK 03

Experience

Design Build Fly (DBF)

Aerodynamics Team

Contributed to UCSD’s Design-Build-Fly effort by supporting aerodynamic configuration decisions and practical build-to-test iteration on a student RC aircraft. Performed airfoil screening and low-fidelity analysis (XFOIL/XFLR5) to compare lift/drag trends under Reynolds-number constraints typical of competition-scale aircraft, and used results to inform geometry choices and stability targets. Helped translate analysis into CAD updates and manufacturing-ready geometry, then supported flight readiness through preflight checks and post-flight review. Worked with onboard telemetry limited to battery voltage and link/signal strength to improve operational reliability and reduce “unknowns” during test days.

UCSD ITS

Service Desk Lead

Progressed from Service Desk Technician to Lead, taking responsibility for shift operations, escalation triage, and technician support during high-impact incidents. Mentored newer technicians, improved consistency in ticket handling through clearer triage routines and documentation, and served as a primary escalation point for complex account, device, and software issues. Coordinated with higher-tier teams when incidents required deeper network or systems support, focusing on fast communication, accurate handoffs, and restoring service with minimal user downtime. Also founded an ITS Social Media account to act as a zero-tier support for our customers.

DATA BLOCK 04

Projects

Executive Summary

Conceptual design study for an ultra-efficient blended-wing-body (BWB) commercial transport named "Manta", focused on configuration trades, propulsion-airframe integration, and performance-driven sizing. The design targets a 7,400 nmi long-haul route carrying 250 passengers at Mach 0.85, significantly improving upon traditional Tube and Wing (TAW) architectures.

Design Optimization & Analysis

Gradient-Free Optimization: Utilized Particle Swarm Optimization (PSO) via Python to maximize cruise L/D, improving the baseline from 24.85 to an optimized 25.30 while satisfying strict material yield stress and stability constraints.
Sensitivity Analysis: Conducted a Monte Carlo simulation using Latin Hypercube sampling to map the design space, revealing that aspect ratio has the greatest influence on L/D, while chord length drives cost per seat-mile.
Stability & Control: Implemented a digital Fly-By-Wire (FBW) active control system to counteract the inherent dynamic instabilities of the reflexed center body and outer wing sections.

Key Engineering Decisions

Cabin Architecture: A triple-aisle (2-4-4-2) main cabin configuration housed within a PRSEUS (Pultruded Rod Stitched Efficient Unitized Structures) reinforced fuselage to handle asymmetric internal pressurization.
Propulsion Integration: Twin GEnX-1B high-bypass turbofan engines mounted on the aft upper-surface to maximize boundary layer ingestion (BLI) and provide acoustic shielding.
Materials: Carbon Fiber Reinforced Polymer (CFRP) and High Modulus Carbon Fiber used for primary lifting structures to minimize empty weight.

Technical Specifications

Passenger Capacity	250 PAX
Max Takeoff Weight	1,435,400 N
Range	7,400 NMI
Cruise Mach / Altitude	Mach 0.85 / 40,000 ft
Wingspan (Code E gate limit)	64.7 m
Cruise L/D	25.30
Cost per Available Seat Mile (CASM)	$0.0873
Powerplant	2x GEnX-1B

// HRD-01

BWB Airliner Concept "Manta"

Ultra-efficient commercial aircraft concept targeting Mach 0.85.

View Report & Model →

function [name, PID, dataOut1, dataOut2] = Wing_Analysis_Function(dataIn);
% + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + +
% +
% +  SE-160A:  Aerospace Structural Analysis I
% +
% +  Project: (2) Wing Analysis
% +
% +  Title:   Wing_Analysis_Function
% +  Author:  Student Name
% +  PID:     Student PID
% +  Version: (01) 02/14/2025
% +           (02) 02/22/2025
% +
% +  This function is the primary analysis function for the wing analysis 
% +  program.  All of the input data is brought into the function using 
% +  "dataIn". Next all the calculations are performed.  Finally, the 
% +  calculated results are written to "dataOut1" and "dataOut2", where 
% +  these two data sets are sent to the main program (p-code) where it is 
% +  written and plotted in an Excel output file.
% +
% +  SUMMARY OF WING ANALYSIS
% +
% +  A) SECTION PROPERTIES
% +     A.1) Modulus Weighted Section Properties (yc, zc, EA, EIyy, EIzz, EIyz)
% +     A.2) Torsion Constant (GJ)
% +     A.3) Shear Center Location (ysc, zsc)
% +     A.4) Total Half Span Wing Weight (lb)
% +
% +  B) LOADS
% +     B.1) Concentrated Loads (Px, Py, Pz, Mx, My, Mz)
% +     B.2) Distributed Aerodynamic Loads (lift, drag, moment)
% +     B.3) Maneuvering Loads (distributed weight)
% +     B.4) Wing Root Reactions - Axial, Shear, Torque, and Moment 
% +     B.5) Distributed Wing Internal Axial, Shear, Bend Moments, Torque
% +
% +  C) INTERNAL STRESSES
% +     C.1) Wing Root Axial Stress (sxx) and Shear Stress (txs)
% +     C.2) Allowable Stress, and Root Margin of Safety
% +     C.3) Distributed Wing Axial Stress (sxx) Plot
% +     C.4) Distributed Wing Shear Stress (tau) Plot
% +
% +  D) WING TIP DISPLACEMENTS, TWIST, AND BENDING SLOPES
% +     D.1) Distributed Wing X-direction (Axial) Displacement 
% +     D.2) Distributed Wing Y-direction (Drag ) Displacement 
% +     D.2) Distributed Wing Z-direction (Lift ) Displacement 
% +     D.3) Distributed Wing Twist Rotation
% +     D.4) Distributed Wing Bending Slopes (dv/dx, dw/dx)
% +
% +  Input Data Array: dataIn (57)
% +     dataIn(01):     Number of Output Plot Data Points (nplot)
% +     dataIn(02):     Wing Length (inch)
% +     dataIn(03):     Wing Chord  (inch)
% +     dataIn(04):     Maximum Wing Thickness (% of chord)
% +     dataIn(05):     Secondary Structure Added Wing Weight (% of distributed weight)
% +     dataIn(06):     Wing Skin Thickness (inch)
% +     dataIn(07):     Wing Skin Weight Density (lb/in^3)
% +     dataIn(08):     Skin Material Shear Modulus (Msi)
% +     dataIn(09):     Skin Material Yield Strength - Shear (Ksi)
% +     dataIn(10):     Skin Material Ultimate Strength - Shear (Ksi)
% +     dataIn(11):     Stringers #1 and #2: Y-location (% of chord)   
% +     dataIn(12):     Stringers #1 and #2: Section area (A) (inch^2)
% +     dataIn(13):     Stringers #1 and #2: Section inertia about y-axis (Iyy) (inch^4)  
% +     dataIn(14):     Stringers #1 and #2: Section inertia about z-axis (Izz) (inch^4)  
% +     dataIn(15):     Stringers #1 and #2: Section product of inertia   (Iyz) (inch^4)
% +     dataIn(16):     Stringers #1 and #2: Weight density (lb/in^3)
% +     dataIn(17):     Stringers #1 and #2: Young's modulus                 (Msi)
% +     dataIn(18):     Stringers #1 and #2: Yield strength    - tension     (Ksi)
% +     dataIn(19):     Stringers #1 and #2: Ultimate strength - tension     (Ksi)
% +     dataIn(20):     Stringers #1 and #2: Yield strength    - comptrddion (Ksi)
% +     dataIn(21):     Stringers #1 and #2: Ultimate strength - compression (Ksi)
% +     dataIn(22):     Stringers #3 and #4: Y-location (% of chord)   
% +     dataIn(23):     Stringers #3 and #4: Section area (A) (inch^2)
% +     dataIn(24):     Stringers #3 and #4: Section inertia about y-axis (Iyy) (inch^4)  
% +     dataIn(25):     Stringers #3 and #4: Section inertia about z-axis (Izz) (inch^4)  
% +     dataIn(26):     Stringers #3 and #4: Section product of inertia   (Iyz) (inch^4)
% +     dataIn(27):     Stringers #3 and #4: Weight density (lb/in^3)
% +     dataIn(28):     Stringers #3 and #4: Young's modulus                 (Msi)
% +     dataIn(29):     Stringers #3 and #4: Yield strength    - tension     (Ksi)
% +     dataIn(30):     Stringers #3 and #4: Ultimate strength - tension     (Ksi)
% +     dataIn(31):     Stringers #3 and #4: Yield strength    - comptrddion (Ksi)
% +     dataIn(32):     Stringers #3 and #4: Ultimate strength - compression (Ksi)
% +     dataIn(33):     Safety Factor - Yield
% +     dataIn(34):     Safety Factor - Ultimate
% +     dataIn(35):     First Load Location  - X (% of Length)
% +     dataIn(36):     Concentrated Force   - X Direction (lb)
% +     dataIn(37):     Concentrated Force   - Y Direction (lb)
% +     dataIn(38):     Concentrated Force   - Z Direction (lb) 
% +     dataIn(39):     Concentrated Torque  - About X Direction (lb-in)
% +     dataIn(40):     Concentrated Moment  - About Y Direction (lb-in)
% +     dataIn(41):     Concentrated Moment  - About Z Direction (lb-in)
% +     dataIn(42):     Second Load Location - X (% of Length)
% +     dataIn(43):     Concentrated Force   - X Direction (lb)
% +     dataIn(44):     Concentrated Force   - Y Direction (lb)
% +     dataIn(45):     Concentrated Force   - Z Direction (lb) 
% +     dataIn(46):     Concentrated Torque  - About X Direction (lb-in)
% +     dataIn(47):     Concentrated Moment  - About Y Direction (lb-in)
% +     dataIn(48):     Concentrated Moment  - About Z Direction (lb-in)
% +     dataIn(49):     Aircraft Load Factor
% +     dataIn(50):     Drag Distribution - Constant (lb/in)
% +     dataIn(51):     Drag Distribution - rth order (lb/in)
% +     dataIn(52):     Drag Distribution - polynomial order
% +     dataIn(53):     Lift Distribution - Constant (lb/in)
% +     dataIn(54):     Lift Distribution - 2nd Order (lb/in)
% +     dataIn(55):     Lift Distribution - 4th Order (lb/in)
% +     dataIn(56):     Twist Moment Distribution - Constant (lb-in/in)
% +     dataIn(57):     Twist Moment Distribution - 1st Order (lb-in/in)
% +
% +  Output Data
% +   Name:              Name of author of this analysis function            
% +   PID:               UCSD Student ID number of author
% +   dataOut1:          Packed calculated output variable data
% +     dataOut1(01):   Modulus Weighted Centroid y-direction (inch)
% +     dataOut1(02):   Modulus Weighted Centroid z-direction (inch)
% +     dataOut1(03):   Cross-Section Weight rho*A (lb/in)
% +     dataOut1(04):   Axial   Stiffness EA   (lb)
% +     dataOut1(05):   Bending Stiffness EIyy (lb-in^2)   
% +     dataOut1(06):   Bending Stiffness EIzz (lb-in^2)   
% +     dataOut1(07):   Bending Stiffness EIyz (lb-in^2)   
% +     dataOut1(08):   Torsion Stiffness GJ   (lb-in^2)
% +     dataOut1(09):   Shear Center, y-direction (inch)
% +     dataOut1(10):   Shear Center, z-direction (inch)
% +     dataOut1(11):   Total Half-Span Wing Weight including added weight factor (lb)
% +     dataOut1(12):   Root Internal Force - X Direction (lb)
% +     dataOut1(13):   Root Internal Force - Y Direction (lb)
% +     dataOut1(14):   Root Internal Force - Z Direction (lb)
% +     dataOut1(15):   Root Internal Moment - about X Direction (lb-in)
% +     dataOut1(16):   Root Internal Moment - about Y Direction (lb-in)
% +     dataOut1(17):   Root Internal Moment - about Z Direction (lb-in)
% +     dataOut1(18):   Stringer (#1) Calculated Axial Stress (lb/in^2)
% +     dataOut1(19):   Stringer (#1) Allowable Stress - Tension (lb/in^2)
% +     dataOut1(20):   Stringer (#1) Allowable Stress - Compression (lb/in^2)
% +     dataOut1(21):   Stringer (#1) Margin of Safety
% +     dataOut1(22):   Stringer (#2) Calculated Axial Stress (lb/in^2)
% +     dataOut1(23):   Stringer (#2) Allowable Stress - Tension (lb/in^2)
% +     dataOut1(24):   Stringer (#2) Allowable Stress - Compression (lb/in^2)
% +     dataOut1(25):   Stringer (#2) Margin of Safety
% +     dataOut1(26):   Stringer (#3) Calculated Axial Stress (lb/in^2)
% +     dataOut1(27):   Stringer (#3) Allowable Stress - Tension (lb/in^2)
% +     dataOut1(28):   Stringer (#3) Allowable Stress - Compression (lb/in^2)
% +     dataOut1(29):   Stringer (#3) Margin of Safety
% +     dataOut1(30):   Stringer (#4) Calculated Axial Stress (lb/in^2)
% +     dataOut1(31):   Stringer (#4) Allowable Stress - Tension (lb/in^2)
% +     dataOut1(32):   Stringer (#4) Allowable Stress - Compression (lb/in^2)
% +     dataOut1(33):   Stringer (#4) Margin of Safety
% +     dataOut1(34):   Skin Panel (1.2) Calculated Shear Stress (lb/in^2)
% +     dataOut1(35):   Skin Panel (1.2) Allowable Stress - Shear (lb/in^2)
% +     dataOut1(36):   Skin Panel (1.2) Margin of Safety
% +     dataOut1(37):   Skin Panel (2.3) Calculated Shear Stress (lb/in^2)
% +     dataOut1(38):   Skin Panel (2.3) Allowable Stress - Shear (lb/in^2)
% +     dataOut1(39):   Skin Panel (2.3) Margin of Safety
% +     dataOut1(40):   Skin Panel (3.4) Calculated Shear Stress (lb/in^2)
% +     dataOut1(41):   Skin Panel (3.4) Allowable Stress - Shear (lb/in^2)
% +     dataOut1(42):   Skin Panel (3.4) Margin of Safety
% +     dataOut1(43):   Skin Panel (4.1) Calculated Shear Stress (lb/in^2)
% +     dataOut1(44):   Skin Panel (4.1) Allowable Stress - Shear (lb/in^2)
% +     dataOut1(45):   Skin Panel (4.1) Margin of Safety
% +     dataOut1(46):   Tip Displacement  - X Direction (inch)
% +     dataOut1(47):   Tip Displacement  - Y Direction (inch)
% +     dataOut1(48):   Tip Displacement  - Z Direction (inch)
% +     dataOut1(49):   Tip Twist (degree)
% +     dataOut1(50):   Tip Bending Slope (dv/dx) (inch/inch)
% +     dataOut1(51):   Tip Bending Slope (dw/dx) (inch/inch)
% +
% +   dataOut2(nplot,24):  Packed calculated output plot data
% +     column( 1):     X direction coordinate (inch)
% +     column( 2):     Applied distributed drag force (lb/in)   
% +     column( 3):     Applied distributed lift force (lb/in)   
% +     column( 4):     Applied distributed torque (lb-in/in)   
% +     column( 5):     Internal shear force  - Vx (lb)   
% +     column( 6):     Internal shear force  - Vy (lb)   
% +     column( 7):     Internal shear force  - Vz (lb)   
% +     column( 8):     Internal axial torque - Mx (lb-in)
% +     column( 9):     Internal bending moment - My (lb-in)
% +     column(10):     Internal bending moment - Mz (lb-in)
% +     column(11):     Stringer (#1) Axial Stress (lb/in^2) 
% +     column(12):     Stringer (#2) Axial Stress (lb/in^2) 
% +     column(13):     Stringer (#3) Axial Stress (lb/in^2) 
% +     column(14):     Stringer (#4) Axial Stress (lb/in^2) 
% +     column(15):     Skin Panel (1.2) Shear Stress (lb/in^2) 
% +     column(16):     Skin Panel (2.3) Shear Stress (lb/in^2) 
% +     column(17):     Skin Panel (3.4) Shear Stress (lb/in^2) 
% +     column(18):     Skin Panel (4.1) Shear Stress (lb/in^2)
% +     column(19):     Displacement - X Direction (inch) 
% +     column(20):     Displacement - Y Direction (inch) 
% +     column(21):     Displacement - z Direction (inch) 
% +     column(22):     Twist (Twist1 + Twist2 + Twist3) (degree)
% +     column(23):     Bending Slope (dv/dx) (inch/inch)
% +     column(24):     Bending Slope (dw/dx) (inch/inch)
% +     column(25):     Twist1 (Twist from Vy only)  (degree)
% +     column(26):     Twist2 (Twist from Vz only)  (degree)
% +     column(27):     Twist3 (Twist from Mx only)  (degree)
% +
% + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + +

% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#1): Unpack Input Data Array and Write User Name and PID
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (1) Unpack Input Data and Write User Name and PID')

   nplot    = dataIn( 1);              % number of output plot data points
   Lo       = dataIn( 2);              % Wing Length (inch)
   Co       = dataIn( 3);              % Wing Chord  (inch)
   tmax     = dataIn( 4)*Co/100;       % Maximum Wing Thickness (inch)
   Kaw      = dataIn( 5);              % Secondary Structure Added Weight (% of wing weight)

   T_sk     = dataIn( 6);              % Wing Skin Thickness (inch)
   rho_sk   = dataIn( 7);              % Wing Skin Weight Density (lb/inch^3)
   G_sk     = dataIn( 8)*(1000000.);   % Skin Material Shear Modulus (lb/in^2)
   Tau_y_sk = dataIn( 9)*(   1000.);   % Skin Material Yield Shear Strength (lb/in^2)
   Tau_u_sk = dataIn(10)*(   1000.);   % Skin Material Ultimate Shear Strength (lb/in^2)

   Yo(1)    = dataIn(11)*Co/100;       % Stringer #1 Y-location (inch)
   Zo(1)    = tmax/2.;                 % Stringer #1 Z-location (inch)
   As(1)    = dataIn(12);              % Stringer #1 Cross-Section Area (inch^2)
   Iyys(1)  = dataIn(13);              % Stringer #1 Iyy Inertia about the y-axis (inch^4)
   Izzs(1)  = dataIn(14);              % Stringer #1 Izz Inertia about the z-axis (inch^4)
   Iyzs(1)  = dataIn(15);              % Stringer #1 Iyz Product of Inertia (inch^4)
   rhos(1)  = dataIn(16);              % Stringer #1 Weight Density (lb/inch^3)
   Es(1)    = dataIn(17)*(1000000.);   % Stringer #1 Young's Modulus (lb/in^2)
   SyTs(1)  = dataIn(18)*(   1000.);   % Stringer #1 Yield Strength    - Tension (lb/in^2)
   SuTs(1)  = dataIn(19)*(   1000.);   % Stringer #1 Ultimate Strength - Tension (lb/in^2)
   SyCs(1)  = dataIn(20)*(   1000.);   % Stringer #1 Yield Strength    - Compression (lb/in^2)
   SuCs(1)  = dataIn(21)*(   1000.);   % Stringer #1 Ultimate Strength - Compression (lb/in^2)

   Yo(2)    = dataIn(11)*Co/100;       % Stringer #2 Y-location (inch)
   Zo(2)    =-tmax/2.;                 % Stringer #2 Z-location (inch)
   As(2)    = dataIn(12);              % Stringer #2 Cross-Section Area (inch^2)
   Iyys(2)  = dataIn(13);              % Stringer #2 Iyy Inertia about the y-axis (inch^4)
   Izzs(2)  = dataIn(14);              % Stringer #2 Izz Inertia about the z-axis (inch^4)
   Iyzs(2)  = dataIn(15);              % Stringer #2 Iyz Product of Inertia (inch^4)
   rhos(2)  = dataIn(16);              % Stringer #2 Weight Density (lb/inch^3)
   Es(2)    = dataIn(17)*(1000000.);   % Stringer #2 Young's Modulus (lb/in^2)
   SyTs(2)  = dataIn(18)*(   1000.);   % Stringer #2 Yield Strength    - Tension (lb/in^2)
   SuTs(2)  = dataIn(19)*(   1000.);   % Stringer #2 Ultimate Strength - Tension (lb/in^2)
   SyCs(2)  = dataIn(20)*(   1000.);   % Stringer #2 Yield Strength    - Compression (lb/in^2)
   SuCs(2)  = dataIn(21)*(   1000.);   % Stringer #2 Ultimate Strength - Compression (lb/in^2)

   Yo(3)    = dataIn(22)*Co/100;       % Stringer #3 Y-location (inch)
   Zo(3)    =-tmax/2.;                 % Stringer #3 Z-location (inch) 
   As(3)    = dataIn(23);              % Stringer #3 Cross-Section Area (inch^2)
   Iyys(3)  = dataIn(24);              % Stringer #3 Iyy Inertia about the y-axis (inch^4)
   Izzs(3)  = dataIn(25);              % Stringer #3 Izz Inertia about the z-axis (inch^4)
   Iyzs(3)  = dataIn(26);              % Stringer #3 Iyz Product of Inertia (inch^4)
   rhos(3)  = dataIn(27);              % Stringer #3 Weight Density (lb/inch^3)
   Es(3)    = dataIn(28)*(1000000.);   % Stringer #3 Young's Modulus (lb/in^2)
   SyTs(3)  = dataIn(29)*(   1000.);   % Stringer #3 Yield Strength    - Tension (lb/in^2)
   SuTs(3)  = dataIn(30)*(   1000.);   % Stringer #3 Ultimate Strength - Tension (lb/in^2)
   SyCs(3)  = dataIn(31)*(   1000.);   % Stringer #3 Yield Strength    - Compression (lb/in^2)
   SuCs(3)  = dataIn(32)*(   1000.);   % Stringer #3 Ultimate Strength - Compression (lb/in^2)

   Yo(4)    = dataIn(22)*Co/100;       % Stringer #4 Y-location (inch)
   Zo(4)    = tmax/2.;                 % Stringer #4 Z-location (inch) 
   As(4)    = dataIn(23);              % Stringer #4 Cross-Section Area (inch^2)
   Iyys(4)  = dataIn(24);              % Stringer #4 Iyy Inertia about the y-axis (inch^4)
   Izzs(4)  = dataIn(25);              % Stringer #4 Izz Inertia about the z-axis (inch^4)
   Iyzs(4)  = dataIn(26);              % Stringer #4 Iyz Product of Inertia (inch^4)
   rhos(4)  = dataIn(27);              % Stringer #4 Weight Density (lb/inch^3)
   Es(4)    = dataIn(28)*(1000000.);   % Stringer #4 Young's Modulus (lb/in^2)
   SyTs(4)  = dataIn(29)*(   1000.);   % Stringer #4 Yield Strength    - Tension (lb/in^2)
   SuTs(4)  = dataIn(30)*(   1000.);   % Stringer #4 Ultimate Strength - Tension (lb/in^2)
   SyCs(4)  = dataIn(31)*(   1000.);   % Stringer #4 Yield Strength    - Compression (lb/in^2)
   SuCs(4)  = dataIn(32)*(   1000.);   % Stringer #4 Ultimate Strength - Compression (lb/in^2)

   SFy      = dataIn(33);              % Safety Factor - Yield
   SFu      = dataIn(34);              % Safety Factor - Ultimate

   x1       = dataIn(35)*Lo/100;       % First Load Location (inch)
   Fx1      = dataIn(36);              % Concentrated Force - X Direction (lb)
   Fy1      = dataIn(37);              % Concentrated Force - Y Direction (lb)
   Fz1      = dataIn(38);              % Concentrated Force - Z Direction (lb)   
   Mx1      = dataIn(39);              % Concentrated Torque - About X Direction (lb-in)
   My1      = dataIn(40);              % Concentrated Moment - About Y Direction (lb-in)
   Mz1      = dataIn(41);              % Concentrated Moment - About Z Direction (lb-in)
   
   x2       = dataIn(42)*Lo/100;       % Second Load Location (inch)
   Fx2      = dataIn(43);              % Concentrated Force - X Direction (lb)
   Fy2      = dataIn(44);              % Concentrated Force - Y Direction (lb)
   Fz2      = dataIn(45);              % Concentrated Force - Z Direction (lb)   
   Mx2      = dataIn(46);              % Concentrated Torque - About X Direction (lb-in)
   My2      = dataIn(47);              % Concentrated Moment - About Y Direction (lb-in)
   Mz2      = dataIn(48);              % Concentrated Moment - About Z Direction (lb-in)

   LF       = dataIn(49);              % Aircraft Load Factor

   py0      = dataIn(50);              % Drag Distribution - Constant (lb/in)
   pyr      = dataIn(51);              % Drag Distribution - rth order (lb/in)
   rth      = dataIn(52);              % Drag Distribution - polynomial order
   pz0      = dataIn(53);              % Lift Distribution - Constant (lb/in)
   pz2      = dataIn(54);              % Lift Distribution - 2nd Order (lb/in)
   pz4      = dataIn(55);              % Lift Distribution - 4th Order (lb/in)
   mx0      = dataIn(56);              % Twist Moment Distribution - Constant (lb-in/in)
   mx1      = dataIn(57);              % Twist Moment Distribution - 1st Order (lb-in/in)

% Define author name and PID (Write in your name and PID)    
   name     = {'Gregorio Zaltzman'};
   PID      = {'A17415158'};

% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#2): Calculate the Centroid, Mass Properties, and Modulus- 
% .                Weighted Bending Section Properties.  
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (2) Calculate the Centroid and Bending Section Properties')



%  2.1) Calculate Modulus-Weighted Centroid.  Use stringers only.
%  --------------------------------------------------------------

EA = sum(Es .* As); % axial stifness 

% Centroid properties

Yc = sum(Lo * rhos * As * Yo) / EA; 
Zc = sum(Lo * As * rhos * Zo) / EA; 

%  2.2) Calculate Modulus-Weighted Stiffnesses (EIyy, EIzz, EIyz) about 
%       the modulus weighted centroid.  Use stringers only.
%  ---------------------------------------------------------------------

  
EIyy = sum(Es *(Iyys + As*((Zo-Zc).^2)));
EIzz = sum(Es *(Izzs + As*((Yo-Yc).^2)));
Eiyz = sum (Es * Iyzs); 

%  2.3) Calculate the cross-section weight (stringers and skin) and the total wing weight
%  --------------------------------------------------------------------------------------

% elipse properties 
a = co/4;
b =tmax/2;

% Cross sectional Areas
Elipse_Area = pi*a*b/2;
Flat_Area = tmax * Co/4;
Linear_Area = (Co/2)*(tmax)/2;
SA = Linear_Area + Flat_Area + Elipse_Area; % cross sectional area 

% Cross sectional Perimeter
Elipse_Per = 1/2 * (pi*(3*(a+b) - sqrt((3a+b) * (8a+3b)) ));
Flat_Peri = 2*Co/4;
Linear_Peri = 2* sqrt( (tmax/2).^2 + (Co).^2);
SC = Linear_Peri + Flat_Peri + Elipse_Area; % wing section circumfurence 

rhoA = (sum(rhos .* As) + rho_sk * T_sk * SC) * (1 + Kaw/100); % Cross-Section Weight (lb/inch)
Weight = rhoA * Lo;

% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#3): Calculate Root and Distributed Stress Resultants for
% .                Applied Concentrated Forces and Aerodynamic Loads
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (3) Calculate Root and Distributed Stress Resultants for Applied Loads')

% 3.a) Combine Applied Concentrated Forces (1) and (2).  These loads are at the centroid

% Root forces
Vxo = Fx1 + Fx2;
Vyo = Fy1 + Fy2 + Lo * (py0 + pyr / (rth+1) );
Vzo = Fz1 + Fz2 + Lo * (pz0 + pz2 * (2/3) + pz4 *(4/5) ) - LF * Weight;

% Root Moments
Mxo = Mx1 + Mx2 - LF * Weight * (Co/2 - Yc) - Lo*(pz0 + pz2/3 + pz4/5)*(Yc - Co/4) + mx0*Lo + (mx1*Lo)/2 - (Fz1+Fz2)*(Yc - Co/4);
Myo = My1 + My2 - Fz1*x1 - Fz2*x2 + LF * Weight * Lo/2 - (pz0*Lo^2)/2 - (pz2*Lo^2)/4 - (pz4*Lo^2)/6;
Mzo = Mz1 + Mz2 + Fy1*x1 + Fy2*x2 + (py0*Lo^2)/2 + (pyr*Lo^2)/(rth+2) + (Fx1+Fx2)*(Yc-Co/4);

% 3.b) Applied Aerodynamic Forces (move distributed lift from C/4 to
%      centroid.  Move distributed weight (nw) from C/2 to centroid.

pz = pz0 + pz2 * (x/Lo).^2 + pz4* (x/Lo).^4 - LF * Weight;
py = py0 + pyr(x/Lo).^rth;
px = 0;
mx = mx0 + mx1*x/Lo - (pz + LF * Weight/Lo)*(Yc - Co/4) - (LF * Weight/Lo) * (Co/2 - Yc);
my = 0;
mz = 0;


% 3.c) Calculate Distributions for Applied Loads and Internal Stress Resultants

% stress resultant distribution 
Vx = Vxo;
Vy = Vyo - (py0 * x + (pyr * x.^(rth+1)) / ((Lo^rth) * (rth+1)));
Vz = Vzo - (pz0 * x (pz2*x.^3)/3*L0.^2) + (pz4*x.^5)/5*L0.^4 - (LF * Weight * x)/Lo); 

for i = 1:nplot
    if x(i) > x1 
       Vx(i) = Vx(i) - Fx1;
       Vy(i) = Vy(i) - Fy1;
       Vz(i) = Vz(i) - Fz1;
    end
    if x(i) > x2
       Vx(i) = Vx(i) - Fx2;
       Vy(i) = Vy(i) - Fy2;
       Vz(i) = Vz(i) - Fz2; 
    end
end



% moment stress resultant distribution 

% Mx distribution
Mx = -(mx0 * x + (mx1 * x.^2) / (2 * Lo)) + Mxo ...
    + (pz0 * x + (pz2 * (x.^3)) / (3 * Lo^2) + (pz4 * (x.^5)) / (5 * Lo^4)) * (Yc - Co / 4) ...
    - (py0 * x + (pyr * x.^(rth+1)) / ((Lo^rth) * (rth+1))) * Zc ...
    + (LF * Weight / Lo) * x * (Co / 2 - Yc);

% My distribution
My = - (pz4 * x.^6) / (30 * Lo^4) - (pz2 * x.^4) / (12 * Lo^2) ...
    + ((LF * Weight - Lo * pz0) * x.^2) / (2 * Lo) + Vzo * x + Myo;

% Mz distribution 
Mz = (py0 * x.^2) / 2 + (pyr * (x.^(rth + 2))) / (Lo^rth * (rth + 1) * (rth + 2)) ...
    - Vyo * x + Mzo;

for i = 1:nplot
    if x(i) > x1 
       Mx(i) = Mx(i) - Mx1 + Fz1 * (Yc - Co/4);
       My(i) = My(i) - My1 - Fz1 * (x(i) - x1);
       Mz(i) = Mz(i) - Mz1 + Fy1 * (x(i) - x1) - Fx1 * (Yc - Co/4) ;
    end
    if x(i) > x2 
       Mx(i) = Mx(i) - Mx2 + Fz2 * (Yc - Co/4);
       My(i) = My(i) - My2 - Fz2 * (x(i) -x2);
       Mz(i) = Mz(i) - Mz2 +Fy2 * (x(i) - x2) - Fx2 * (Yc - Co/4); 
    end
end

 
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#4): STRINGER STRESSES: Calculate Allowable Properties, 
% .                Root Stresses, Margins of Safety, and Stress Distribution
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (4) Calculate Stringer Stress Distribution and Root Margins of Safety')

% 4.1) Calculate root stringer stresses and margins of safety 

% allowable stresses 
for i = 1:4
Sat(i) = min(SyTs(i)/SFy, SuTs(i)/SFu);
Sac(i) = max(SyCs(i)/SFy, SuCs(i)/SFu);
end

% axial stresses
for i = 1:4
Sxxo(i) = Es(i) * (Vxo/EA + ((Myo * abs(Zo(i)-Zc)) / EIyy) + ((Mzo * abs (Yc-Yo(i)))/EIzz));
end

% margin of safety 
for i = 1:4
MSs(i) = Sat(i)/sqrt(Sxxo(i).^2) - 1;
end

% 4.2) calculate stringer stress distributions 

% axial stress distribution

Sxx1 = Es(1) * (Vx/EA + ((My * abs(Zo(1)-Zc)) / EIyy) + (Mz * abs(Yc-Yo(1))) / EIzz);
Sxx2 = Es(2) * (Vx/EA - ((My * abs(Zo(2)-Zc)) / EIyy) + (Mz * abs(Yc-Yo(2))) / EIzz);
Sxx3 = Es(3) * (Vx/EA - ((My * abs(Zo(3)-Zc)) / EIyy) - (Mz * abs(Yc-Yo(3))) / EIzz);
Sxx4 = Es(4) * (Vx/EA + ((My * abs(Zo(4)-Zc)) / EIyy) - (Mz * abs(Yc-Yo(4))) / EIzz);

% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#5): WING BENDING DISPLACEMENTS AND SLOPES. Calculate tip 
% .                values and distributions
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (5) Calculate Wing Bending Displacements and Bending Slope Distributions')

Disp_X = zeros(1, nplot);
Disp_Y = zeros(1, nplot);
Disp_Z = zeros(1, nplot);
Twist = zeros(1, nplot);
DvDx = zeros(1, nplot);
DwDx = zeros(1, nplot);

% 5.1) Calculate displacements and slopes for concentrated force (#1)  (Don't include twist)

for i = 1:nplot
    if x(i) >= x1
        DvDx(i) = (F1 * (x(i) - x1)) / (E * Izz);
        Disp_Y(i) = (F1 * (x(i) - x1).^2) / (2 * E * Izz);
    end
end

% 5.2) Calculate displacements and slopes for concentrated force (#2)  (Don't include twist)

for i = 1:nplot
    if x(i) >= x2
        DvDx(i) = DvDx(i) + (F2 * (x(i) - x2)) / (E * Izz);
        Disp_Y(i) = Disp_Y(i) + (F2 * (x(i) - x2).^2) / (2 * E * Izz);
    end
end

% 5.3) Calculated displacements and slopes for aerodynamic loading (Don't include twist)

for i = 1:nplot
    DwDx(i) = (pz0 * x(i).^3) / (6 * E * Iyy) + ...
              (pz2 * x(i).^5) / (120 * E * Iyy * Lo^2) + ...
              (pz4 * x(i).^7) / (5040 * E * Iyy * Lo^4);
    
    Disp_Z(i) = (pz0 * x(i).^4) / (24 * E * Iyy) + ...
                (pz2 * x(i).^6) / (720 * E * Iyy * Lo^2) + ...
                (pz4 * x(i).^8) / (40320 * E * Iyy * Lo^4);
end

% 5.4) Combine displacements, slopes, and twist for concentrated loads and aero loads 

Disp_Y = Disp_Y + (pz0 * x.^4) / (24 * E * Izz) + (pz2 * x.^6) / (720 * E * Izz * Lo^2) + (pz4 * x.^8) / (40320 * E * Izz * Lo^4);
Twist = Twist_0 + (Mx / (G * J)) * x; % Assuming linear twist distribution


% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#6): SHEAR STUDIES:  Torsion and Transverse Loading. Calculatemx
% .                shear flow, shear stresses, and margin of safety.
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (6) Calculate Shear Flow, Shear Stresses, and Margins of Safety')

%  6.1) Preliminaries:  Calculate the leading edge ellipse area, perimeter,
%       and torsion constant (GJ)

% rest is in section 2.2
GJ = (4*G_sk*(A_airfoil^2)*T_sk)/S; % Torsion Stiffness 

%  6.2) Shear Flow Analysis
EA1y = Es(1) * As(1) * (Yo(1) - Yc);
EA2y = Es(2) * As(2) * (Yo(2) - Yc);
EA3y = Es(3) * As(3) * (Yo(3) - Yc);
EA4y = Es(4) * As(4) * (Yo(4) - Yc);

EA1z = Es(1) * As(1) * (Zo(1) - Zc);
EA2z = Es(2) * As(2) * (Zo(2) - Zc);
EA3z = Es(3) * As(3) * (Zo(3) - Zc);
EA4z = Es(4) * As(4) * (Zo(4) - Zc);

% Shear Force Contributions (Including EA1)
F1 = [EA1y / Izz; EA2y / Izz; EA3y / Izz; EA4y / Izz; -Zc];
F2 = [EA1z / Iyy; EA2z / Iyy; EA3z / Iyy; EA4z / Iyy; Yc - Co/4];
F3 = [0; 0; 0; 0; 1];
forces = [Vy; Vz; Mx];

% Define the Jump Matrix
jump = [F1 F2 F3];

% Define Cross-Sectional Areas for Shear Flow Computation
A12 = 0.5 * pi * a * b + tmax * (Yo(1) - a);
A23 = 0.5 * tmax * abs(Yo(1) - Yo(3));
A34 = 0.5 * tmax * 0.5 * Co + tmax * abs(Co/2 - Yo(3));
A41 = A23;

A_matrix = [A12 A23 A34 A41]; % Already multiplied by 2 for consistency

% Define Shear Flow Coefficient Matrix
q_matrix = [1 -1 0 0; 
            0  1 -1 0; 
            0  0  1 -1; 
            2 * A_matrix];

% Solve for Shear Flows
q_shear = q_matrix \ (jump * forces);


   %  Calculate the unit shear flows for the three cases (Vy, Vz, Mx) separately:


   %  Calculate the shear stress distribution along the length from (Mx), (Vy), and (Vz)


   %  Calculate the skin shear allowable stress and margin of safety (MS)
   %  at the root

Tau_allow_sk12 = min(Tau_u_sk / SFu, Tau_y_sk / SFy); % ksi
Tau_allow_sk23 = Tau_allow_sk12;
Tau_allow_sk34 = Tau_allow_sk12;
Tau_allow_sk41 = Tau_allow_sk12;

% Solve for Shear Flows (Assuming q_shear is computed already)
Tau_12 = q_shear(1) / t_skin; % ksi
Tau_23 = q_shear(2) / t_skin; % ksi
Tau_34 = q_shear(3) / t_skin; % ksi
Tau_41 = q_shear(4) / t_skin; % ksi

% Compute Margin of Safety (MS) for Each Panel
MS_sk12 = (Tau_allow_sk12 / Tau_12) - 1;
MS_sk23 = (Tau_allow_sk23 / Tau_23) - 1;
MS_sk34 = (Tau_allow_sk34 / Tau_34) - 1;
MS_sk41 = (Tau_allow_sk41 / Tau_41) - 1;
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#7): SHEAR STUDIES:  Torsion and Transverse Loading. Calculate
% .                the twist distribution and tip twist.
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (7) Calculate the Twist Distribution and Tip Twist')

% 7.1) Calculate the integrated (Vy, Vz, Mx) for applied concentrated force
%      (#1) and (#2) and aero loading

Int_py_moments = (py0 * x.^2) / 2 + (pyr * x.^(rth+2)) ./ ((Lo^rth) * (rth+1) * (rth+2));
Int_pz_moments = (pz0 * x.^2) / 2 + (pz2 * x.^4) / (12 * Lo^2) + (pz4 * x.^6) / (30 * Lo^4);

% Integrated Shear Forces
IntVy = Vyo * x - Int_py_moments;
IntVz = Vzo * x - Int_pz_moments - (LF * W_wing / Lo) * (x.^2) / 2;

% Integrated Bending Moment
IntMx = Mxo * x - (mx0 * x.^2) / 2 - (mx1 * x.^3) / (6 * Lo) ...
        + (LF * W_wing / Lo) * (x.^2) * (Co/2 - Yc) / 2 ...
        + Int_pz_moments * (Yc - Co/4) - Int_py_moments * Zc;

% Store Continuity Matrices for Calculation
Vycont = [IntVy; zeros(nplot); zeros(nplot)];
Vzcont = [zeros(nplot); IntVz; zeros(nplot)];
Mxcont = [zeros(nplot); zeros(nplot); IntMx];

% lb
% int2_py_moments = py0*(x.^2)/2 + (pyr*x.^(rth+2))/((Lo^rth)*(rth+1)*(rth+2)); %lb
% IntVy = Vyo*x - (py0*(x.^2)/2 + (pyr*x.^(rth+2))/((Lo^rth)*(rth+1)*(rth+2)));
% IntVz = Vzo*x - (pz0*(x.^2)/2 + (pz2*(x.^4))/(12*Lo^2) + (pz4*(x.^6))/(30*Lo^4) -
% (LF*W_wing/Lo)*(x.^2)/2);
% IntMx = Mxo*x -(mx0*(x.^2)/2 + (mx1*x.^3)/(6*Lo)) + (LF*W_wing/Lo)*(x.^2)*(Co/2 -
% Yc)/2 + int2_pz_moments*(Yc-Co/4) - int2_py_moments*Zc;
% Vycont = [IntVy; zeros(nplot); zeros(nplot)];
% Vzcont = [zeros(nplot); IntVz; zeros(nplot)];
% Mxcont = [zeros(nplot); zeros(nplot); IntMx];


Ss = [C_ellipse C_flat/2 C_linear C_flat/2];
A_full = sum(A_matrix);
Twist1 = (180/pi)*(Ss*q_matrix*F1*IntVy)./(2*A_full*G_sk*T_sk);
Twist2 = (180/pi)*(Ss*q_matrix*F2*IntVz)./(2*A_full*G_sk*T_sk);
Twist3 = (180/pi)*(Ss*q_matrix*F3*IntMx)./(2*A_full*G_sk*T_sk);

     % Integrated Concentrated Force (#1) for Vy, Vz, and Mx


     % Integrated Concentrated Force (#2) for Vy, Vz, and Mx


     % Integrated aero loading for Vy, Vz, and Mx

   
     % Combine integrated loading for force #1, #2, and aero loading


% 7.2) Calculate twist separately for force #1, #2, and aero loading


     % Total twist = twist1 + twist2 + twist3


% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#8): SHEAR STUDIES:  Torsion and Transverse Loading.
% .                Calculate the shear center location.
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (8) Calculate the Shear Center Location')

   %  Calculate the shear center location (y-direction).  Apply a unit tip 
   %  load (Vz = Pz = 1) that is offset from the centroid by (ey) such that 
   %  (Mx = Pz*ey).  Calculate the twist rate and set to zero.  Solve for (ey).


   %  Calculate the shear center location (z-direction).  Apply a unit tip 
   %  load (Vy = Py = 1) that is offset from the centroid by (ez) such that 
   %  (Mx = -Py*ez).  Calculate the twist rate and set to zero. Solve for (ez).


% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#9): Pack Calculated Data into the "dataOut1" Array size: (51)
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (9) Pack the Calculated Data into Array: dataOut1')
   dataOut1     = zeros(51);
%     dataOut1(01) = Yc;                % Modulus Weighted Centroid y-direction (inch)
%     dataOut1(02) = Zc;                % Modulus Weighted Centroid z-direction (inch)
%     dataOut1(03) = rhoA;              % Cross-Section Weight (lb/inch)
%     dataOut1(04) = EA;                % Axial   Stiffness (lb)
%     dataOut1(05) = EIyy;              % Bending Stiffness (lb-in^2)   
%     dataOut1(06) = EIzz;              % Bending Stiffness (lb-in^2)   
%     dataOut1(07) = EIyz;              % Bending Stiffness (lb-in^2)   
%     dataOut1(08) = GJ;                % Torsion Stiffness (lb-in^2)
%     dataOut1(09) = Ysc_LE;            % Shear Center y-direction (inch)
%     dataOut1(10) = Zsc_LE;            % Shear Center z-direction (inch)
%     dataOut1(11) = W_wing;            % Total Half-Span Wing Weight (lb)
%     dataOut1(12) = Vxo;               % Root Internal Force - X Direction (lb)
%     dataOut1(13) = Vyo;               % Root Internal Force - Y Direction (lb)
%     dataOut1(14) = Vzo;               % Root Internal Force - Z Direction (lb)
%     dataOut1(15) = Mxo;               % Root Internal Moment - about X Direction (lb-in)
%     dataOut1(16) = Myo;               % Root Internal Moment - about Y Direction (lb-in)
%     dataOut1(17) = Mzo;               % Root Internal Moment - about Z Direction (lb-in)
%     dataOut1(18) = Sxxo(1);           % Stringer (#1) Calculated Axial Stress (lb/in^2)
%     dataOut1(19) = Sat(1);            % Stringer (#1) Allowable Stress - Tension (lb/in^2)
%     dataOut1(20) = Sac(1);            % Stringer (#1) Allowable Stress - Compression (lb/in^2)
%     dataOut1(21) = MSs(1);            % Stringer (#1) Margin of Safety
%     dataOut1(22) = Sxxo(2);           % Stringer (#2) Calculated Axial Stress (lb/in^2)
%     dataOut1(23) = Sat(2);            % Stringer (#2) Allowable Stress - Tension (lb/in^2)
%     dataOut1(24) = Sac(2);            % Stringer (#2) Allowable Stress - Compression (lb/in^2)
%     dataOut1(25) = MSs(2);            % Stringer (#2) Margin of Safety
%     dataOut1(26) = Sxxo(3);           % Stringer (#3) Calculated Axial Stress (lb/in^2)
%     dataOut1(27) = Sat(3);            % Stringer (#3) Allowable Stress - Tension (lb/in^2)
%     dataOut1(28) = Sac(3);            % Stringer (#3) Allowable Stress - Compression (lb/in^2)
%     dataOut1(29) = MSs(3);            % Stringer (#3) Margin of Safety
%     dataOut1(30) = Sxxo(4);           % Stringer (#4) Calculated Axial Stress (lb/in^2)
%     dataOut1(31) = Sat(4);            % Stringer (#4) Allowable Stress - Tension (lb/in^2)
%     dataOut1(32) = Sac(4);            % Stringer (#4) Allowable Stress - Compression (lb/in^2)
%     dataOut1(33) = MSs(4);            % Stringer (#4) Margin of Safety
%     dataOut1(34) = Tau_12(1);         % Skin Panel (1.2) Calculated Shear Stress (lb/in^2)
%     dataOut1(35) = Tau_allow_sk12;    % Skin Panel (1.2) Allowable Shear Stress  (lb/in^2)
%     dataOut1(36) = MS_sk12;           % Skin Panel (1.2) Margin of Safety
%     dataOut1(37) = Tau_23(1);         % Skin Panel (2.3) Calculated Shear Stress (lb/in^2)
%     dataOut1(38) = Tau_allow_sk23;    % Skin Panel (2.3) Allowable Shear Stress  (lb/in^2)
%     dataOut1(39) = MS_sk23;           % Skin Panel (2.3) Margin of Safety
%     dataOut1(40) = Tau_34(1);         % Skin Panel (3.4) Calculated Shear Stress (lb/in^2)
%     dataOut1(41) = Tau_allow_sk34;    % Skin Panel (3.4) Allowable Shear Stress  (lb/in^2)
%     dataOut1(42) = MS_sk34;           % Skin Panel (3.4) Margin of Safety
%     dataOut1(43) = Tau_41(1);         % Skin Panel (4.1) Calculated Shear Stress (lb/in^2)
%     dataOut1(44) = Tau_allow_sk41;    % Skin Panel (4.1) Allowable Shear Stress  (lb/in^2)
%     dataOut1(45) = MS_sk41;           % Skin Panel (4.1) Margin of Safety
%     dataOut1(46) = Disp_X(nplot);     % Tip Diplacement - X Direction (inch)
%     dataOut1(47) = Disp_Y(nplot);     % Tip Diplacement - Y Direction (inch)
%     dataOut1(48) = Disp_Z(nplot);     % Tip Diplacement - Z Direction (inch)
%     dataOut1(49) = Twist(nplot);      % Tip Twist (degree)
%     dataOut1(50) = DvDx(nplot);       % Tip Bending Slope (dv/dx) (inch/inch)
%     dataOut1(51) = DwDx(nplot);       % Tip Bending Slope (dw/dx) (inch/inch)

% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
% .  SECTION (#10): Pack the plot data arrays into "dataOut2" 
% .                 matrix size: (nplot,24)  
% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
   disp('     (10) Pack the Calculated Plot Data into Array: dataOut2')
   dataOut2     = zeros(nplot,27);

   for i = 1:nplot;
%     dataOut2(i, 1) = x(i);            % x-location (inch)
%     dataOut2(i, 2) = py(i);           % drag force (lb/in)
%     dataOut2(i, 3) = pz(i);           % lift force (lb/in)
%     dataOut2(i, 4) = mx(i);           % distributed torque (lb-in/in)
%     dataOut2(i, 5) = Vx(i);           % Internal shear force - Vx (lb)
%     dataOut2(i, 6) = Vy(i);           % Internal shear force - Vy (lb)
%     dataOut2(i, 7) = Vz(i);           % Internal shear force - Vz (lb)
%     dataOut2(i, 8) = Mx(i);           % Internal axial force - Mx (lb-in)
%     dataOut2(i, 9) = My(i);           % Internal shear force - My (lb-in)
%     dataOut2(i,10) = Mz(i);           % Internal shear force - Mz (lb-in)
%     dataOut2(i,11) = Sxx1(i);         % Stringer (#1) Axial Stress (lb/in^2) 
%     dataOut2(i,12) = Sxx2(i);         % Stringer (#2) Axial Stress (lb/in^2) 
%     dataOut2(i,13) = Sxx3(i);         % Stringer (#3) Axial Stress (lb/in^2) 
%     dataOut2(i,14) = Sxx4(i);         % Stringer (#4) Axial Stress (lb/in^2) 
%     dataOut2(i,15) = Skin Panel (1.2) Shear Stress (lb/in^2) 
%     dataOut2(i,16) = Skin Panel (2.3) Shear Stress (lb/in^2) 
%     dataOut2(i,17) = Skin Panel (3.4) Shear Stress (lb/in^2) 
%     dataOut2(i,18) = Skin Panel (4.1) Shear Stress (lb/in^2)
%     dataOut2(i,19) = Displacement - X Direction (inch) 
%     dataOut2(i,20) = Disp_Y(i);       % Displacement - Y Direction (inch)
%     dataOut2(i,21) = Disp_Z(i);       % Displacement - z Direction (inch) 
%     dataOut2(i,22) = Twist(i);        % Wing Twist (degree)
%     dataOut2(i,23) = DvDx(i);         % Bending Slope (dv/dx) (inch/inch)
%     dataOut2(i,24) = DwDx(i);         % Bending Slope (dw/dx) (inch/inch)
%     dataOut2(i,25) = Twist1(i);       % Wing Twist from Vy (degree)
%     dataOut2(i,26) = Twist2(i);       % Wing Twist from Vz (degree)
%     dataOut2(i,27) = Twist3(i);       % Wing Twist from Mx (degree)

   end;
   
end

%  End of Function: Wing_Analysis_Function
%  ------------------------------------------------------------------------

// HRD-02

Wing Spar Analysis

MATLAB Structural Tool.

View Full Report →

// HRD-03

Wind Tunnel Testing

Clark Y-14 Airfoil Aerodynamics.

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// HRD-04

SeaGlide AUV

Autonomous underwater glider with variable buoyancy.

View Media & Report →

// HRD-05

4-Piston Engine CAD

Mechanical Design & Kinematics.

View Model →

// HRD-06

Lab Operations

Acoustics & Thermodynamics.

View Full Reports →

DATA BLOCK 05

Aspirations

My long-term goal is to help propel humanity into the next era of space exploration by contributing to the development of advanced astronautical vehicles and space systems. I aspire to work at the forefront of spacecraft design, system integration, and propulsion innovation, developing technologies that strengthen human capabilities on Earth while expanding our presence beyond it. I am particularly motivated by cutting-edge vehicle concepts and emerging technologies that push the boundaries of what is currently possible.

I’m exploring Master’s programs in Europe with a focus aligned with space engineering, while keeping a strong interest in the broader aerospace ecosystem and advanced vehicle development.

DATA BLOCK 06

Wing Span (b)	51 cm
Wing Area (S)	382.5 cm²
Dry Weight	10.32 N
Buoyancy Change (Dive)	+0.0589 N
Buoyancy Change (Climb)	-0.2551 N
Max Pitch Attitude Angle	±44.5°

Skills

Timeline

Sep 2022

UC San Diego — B.S.c Aerospace

Sep 2023

ITS Service Desk Technician

May 2025

Promoted — Service Desk Lead

Jun 2025

RPL at UCSD

Sep 2025

Design-Build-Fly (DBF)

Present

Senior Design Capstone

Experience

Design Build Fly (DBF)

UCSD ITS

Projects

Executive Summary

Design Optimization & Analysis

Key Engineering Decisions

Technical Specifications

BWB Airliner Concept "Manta"

Executive Summary

Problem Framing

Methods & Tools

Key Results

Wing Spar Analysis

Executive Summary

Objectives & Problem Framing

Methods & Tools

Wind Tunnel Testing

Executive Summary

Hardware & Build

Hydrodynamic Analysis

Technical Specifications

SeaGlide AUV

Executive Summary

Scope

4-Piston Engine CAD

Executive Summary

Heat Transfer Work

Acoustics Work

Lab Operations

Aspirations

Contact