Hardware · Final Year
Subsonic Wind Tunnel
Final Year Project
Open-jet subsonic wind tunnel with an integrated gust generator, built for low-speed experimental aerodynamics research.
Wind-Tunnel Visualization
Your browser/device cannot render WebGL. A static conceptual illustration is shown instead of the interactive scene.
Experimental Aerodynamics & CFD
Engineering the invisible physics of flight.
I'm Nischal Raut, an aspiring aerospace engineer focused on experimental aerodynamics and computational fluid dynamics — bridging computational models with experimental validation in wind-tunnel environments.
Conceptual airflow visualization — illustrative particle streaks through a wind-tunnel test section, not solved flow-field data.
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Nischal Raut — Aerospace Engineer
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About
Grounded in theory, driven toward the test chamber.
An aspiring aerospace engineer interested in experimental aerodynamics and CFD, with an interest in bridging computational models with experimental validation.
My academic and project work spans low-speed wind-tunnel design, CFD analysis of aerodynamic surfaces, and UAV-based photogrammetry — with a recurring focus on connecting simulated predictions to physically measured flow behaviour.
76.71%B.E. Aggregate
0.88%Turbulence Intensity Validated
6Engineering Projects
Conceptual Aircraft Model
Interactive 3D unavailable on this device. This is a simplified, illustrative primitive-based model — not a validated CAD design.
Select a component
Click or tap any part of the model to highlight it and read a short description. Built from primitive geometry for illustration — not an engineering-grade CAD model.
Fuselage · Main Wing · Vertical Stabilizer · Horizontal Tail · Engine Nacelles — click any to inspect.
Capability
Technical skills
Tools and methods used across design, analysis, fabrication and reporting work.
CAD & Design
- CATIA
- SolidWorks
- AutoCAD
Simulation
- ANSYS
- MATLAB
Programming
- C
- Python
Experimental
- Wind-tunnel testing
- Flow visualization
Documentation
- LaTeX
- MS Office
Academic Background
Education
IOE
Bachelor's in Aerospace Engineering
Institute of Engineering, Pulchowk Campus · 2019 – 2025
76.71%Aggregate
OIC
+2 Science
Omega International College
3.5GPA
WW
SEE
West Wing Secondary School
4.0GPA
Career
Professional experience
Internship and industry engineering roles across UAV operations and aircraft integration/system testing.
Associate Engineer – Integration Test
· Airbus India
Dec 2024 – Present
Industry engineering role at Airbus India.
⚠ Dates overlap with other roles below — pending confirmation
Intern – System Testing
· Airbus India
Jul 2024 – Nov 2024
Internship in system testing at Airbus India.
Engineering Intern
· Airlift Technology, Nepal
2024 – Present
UAV operations and geospatial mapping work supporting Kathmandu Metropolitan City.
- Drone mapping and photogrammetry for Kathmandu Metropolitan City
- Generated 3D terrain models and orthomosaics
- Supported UAV mission planning and calibration
UAV Terrain Mapping
Interactive 3D unavailable on this device. Procedural terrain shown as static concept only.
UAV Photogrammetry Workflow
A simplified, illustrative reconstruction of the drone-mapping pipeline used for aerial survey work. Terrain is procedurally generated for demonstration, not sourced from real survey data.
A lawnmower-pattern flight path is planned over the survey area at a constant altitude to ensure consistent image overlap.
Interactive 3D
Engineering labs
Two interactive, illustrative 3D experiences built to explain engineering concepts behind flagship projects. These are conceptual demonstrations for explanatory purposes, not validated CAD or solved CFD output.
Subsonic Wind Tunnel — Interactive Assembly
Exploded-view model of the open-jet subsonic wind-tunnel concept: settling chamber, contraction cone, open test section, oscillating-vane gust generator, diffuser and fan/drive section.
Wind-Tunnel Assembly
Interactive 3D unavailable on this device. This is a simplified conceptual assembly, not a certified engineering drawing.
Selected
Click any component to see its name and role in the circuit. Use "Exploded View" to separate components along the flow axis, and the checkboxes to isolate internal parts.
Objective
Design and build an open-jet subsonic wind tunnel with an integrated gust generator to support low-speed experimental aerodynamics research and CFD validation work.
Methodology
Conceptual sizing and CAD modelling of the flow circuit (settling chamber, contraction, open test section, diffuser, fan/drive section), followed by fabrication and instrumented flow-quality testing in the assembled test section.
Tools
CATIA / SolidWorks for CAD development; wind-tunnel testing and flow-visualization methods for experimental characterisation.
Results
Experimentally validated turbulence intensity of 0.88% in the test section, reported in the existing project portfolio.
Limitations
Open-jet configuration restricts achievable test-section enclosure compared to closed-circuit tunnels; detailed dimensional and instrumentation specifications are documented in the full project report rather than summarised here.
Related Research Interest
Synchronized oscillating-vane gust generation for low-speed unsteady aerodynamics studies — an active extension of this project.
windtunnel1.jpeg
windtunnel2.jpeg
windtunnel3.jpeg
Aerodynamics & CFD — Illustrative Flow Model
Airfoil section with illustrative streamlines and a conceptual pressure-field representation. Adjust angle of attack to see a simplified, non-solved illustration of flow separation.
Illustrative Airflow Model
Interactive 3D unavailable on this device. Diagram shown is illustrative only, not solved CFD data.
Reading
At low angles of attack, flow remains attached over the upper surface. Increase the angle to illustrate flow separation behaviour near the trailing edge.
Objective
Evaluate lift–drag characteristics of a scaled F-15 model across a range of angles of attack using CFD analysis.
Methodology
CAD geometry preparation, mesh generation, and steady-state flow simulation in ANSYS to assess aerodynamic coefficients across the test angle range.
Tools
CATIA/SolidWorks for geometry preparation; ANSYS for CFD simulation.
Results
Comparative lift and drag trends across angle of attack, documented in the full project report. Specific coefficient values are not restated here to avoid summarising beyond the verified source report.
Limitations
Simplified scaled geometry, mesh resolution and turbulence-model assumptions limit direct comparison to full-scale flight data.
Note on this visualization
The 3D panel above is a hand-built illustrative aid for explaining flow attachment and separation concepts — it is not the actual ANSYS solution field.
Selected Work
Projects
Six projects spanning experimental hardware, conceptual design studies, CFD analysis and software development.
Hardware · Final Year
B-52 Air Launch
Conceptual Rocket Carrier
Conceptual design exercise exploring a B-52-type carrier aircraft configuration for air-launched rocket deployment.
Methodology & scope
Objective
Conceptual-level analysis of an air-launch carrier configuration as an academic design exercise.
Tools
CAD modelling and hand/analytical calculations.
Limitations
Conceptual only — not a validated or flight-certified engineering design.
Styrofoam Glider
Design and Test Flights
Lightweight styrofoam glider designed and hand-built to study basic flight stability and glide performance.
Methodology & scope
Objective
Study basic flight stability, control-surface effect and glide performance through a low-cost build.
Tools
Hand-fabrication with styrofoam airframe, manual CG balancing.
Limitations
Qualitative, non-instrumented test flights — observational data only.
U-2 Conversion
Payload Testbed Study
Conceptual academic study examining a U-2-type high-altitude airframe layout adapted toward a payload testbed role.
Methodology & scope
Objective
Conceptual payload/mass layout study based on a high-altitude airframe reference.
Tools
CAD layout and literature-based reference review.
Limitations
Conceptual-level only — no fabrication, structural or CFD validation performed.
F-15 Scale Model
Lift–Drag CFD Study
CFD study of a scaled F-15 model geometry to evaluate lift and drag characteristics across angle of attack.
</> C PROGRAM
Software
Canteen Billing System
C Programming
Console-based billing and order-record system built in C for a canteen-style menu and invoicing workflow.
Methodology & scope
Objective
Automate menu-based order billing and basic record-keeping via a console application.
Tools
C programming language, file-based record storage.
Limitations
No graphical interface, local file storage only, no concurrent-user handling.
Looking Forward
Research interests
Areas I want to pursue further, building directly on the wind-tunnel and UAV mapping work above.
01
Synchronized Oscillating-Vane Gust Generation
Extending the existing gust-generator mechanism toward phase-synchronized oscillating vanes for controllable, repeatable unsteady inflow conditions.
02
Low-Speed Unsteady Aerodynamics
Experimental characterisation of unsteady aerodynamic response in low-speed flow regimes, relevant to gust-response and small-scale aircraft stability.
03
CFD–Experiment Correlation
Using wind-tunnel-measured flow quality and force data to validate and refine corresponding CFD simulation setups.
04
UAV-Based Photogrammetry
Applying drone-based image capture and terrain reconstruction workflows to aerodynamic and geospatial survey applications.
Get in touch
Contact
Open to opportunities in experimental aerodynamics, CFD, and aerospace systems engineering.