Projects

Selected work and engineering projects.

$ ls -la projects/ |

Fabrication of Particle Image Velocimetry Setup at Low Reynolds Number

Designed and fabricated a 40+ component modular PIV system (CATIA, structural FEA) for a 2 m towing tank, maintaining <5% blockage ratio and achieving a safety factor ≈15 under hydrostatic loading, enabling reliable low-Re aerodynamic testing.
Developed MATLAB-based PIV processing pipeline (FFT cross-correlation, CLAHE, vector validation) to reconstruct velocity and vorticity fields at Re = 2,000–10,000, achieving ±2% velocity measurement uncertainty and resolving laminar separation bubbles and vortex shedding.
Validated experimental results against ANSYS Fluent simulations, demonstrating strong agreement in separation location and velocity trends while systematically quantifying uncertainty sources (illumination, sedimentation, optical distortion).

Designed 2.8 m span, 8 kg MTOW fixed-wing UAV using XFLR5/X-Plane to meet 50–60 km inspection range at 18 m/s cruise while maintaining positive static margin for stable autonomous flight
Achieved low stall speed (~3.23 m/s) and short-field performance (21.9 m takeoff, 43.4 m landing) through high aspect ratio wing (AR=10) and lift-to-drag optimization
Performed trim, neutral point, climb/descent, and Cooper-Harper handling analysis to validate longitudinal stability, endurance efficiency, and safe low-speed operation in mountainous terrain

Engineered 900 mm diameter stainless steel thermal vacuum chamber for CubeSat qualification, performing external pressure vessel sizing per ASME Section VIII and optimizing shell thickness to 2 mm for structural efficiency
Led structural validation in ANSYS Mechanical, comparing head geometries and selecting a tori-spherical design with 143.98 MPa peak stress and <0.6 mm deformation under full atmospheric loading
Designed and integrated 1.4 kW closed-loop heating system with LN2-based cryoshroud cooling; validated thermal performance via steady-state simulation to achieve controlled satellite surface temperatures up to 46°C under vacuum

Designed single-stage axial compressor for 8.2 kg/s mass flow and 1.2 target pressure ratio using Python-based mean-line solver and free vortex modeling; defined blade angles, reaction, and rotor speed (~11,464 rpm) from first principles
Generated full 3D rotor–stator blade geometry in CATIA (NACA 65-series) and created 496k-node structured O–H mesh in ANSYS TurboGrid; conducted mesh independence validation with y+ ≈ 20
Executed steady RANS and transient URANS simulations in ANSYS CFX (SST k–ω), achieving 1.12 pressure ratio and ~78% isentropic efficiency while analyzing rotor–stator interaction and secondary flow losses

Designed and integrated strain-gauge load cell instrumentation with NI SCB-68 and LabVIEW DAQ system, sampling at 1000 Hz and implementing bias correction for real-time lift measurement in wind tunnel testing
Performed five-point calibration (R² = 0.9263) to derive force–voltage relationship and ensure reliable lift coefficient computation across −4° to 15° angle of attack
Validated experimental results against ANSYS Fluent simulations (k–ε model), achieving comparable stall prediction (12°–15° experimental vs 14° CFD) and identifying noise, mounting, and turbulence intensity as primary error sources

Developed and evaluated three structural concepts in CATIA for aircraft exhaust stack storage, reducing mass from 108 kg (Option A) to optimized 54.5 kg final design while meeting <60 kg requirement
Performed structural FEA and analytical member force calculations to validate welded steel frame under static loading; confirmed stresses below yield and negligible deflection under service conditions
Conducted stability and transport analysis (CG, rolling friction, incline testing), demonstrating 55° tip-over resistance and mobility on 12° incline with 120 N push force; completed BoQ with total cost ≈ Rs. 15,840