
About Me
I am a highly motivated aerospace engineering master's student with a strong focus on computational fluid dynamics (CFD) in high-speed aerodynamics and reentry vehicle analysis. My expertise includes numerical simulations of hypersonic flows, turbulence modeling, and aerothermal effects, with a particular emphasis on shape parameter optimization for reentry configurations. My research and academic projects have provided me with deep insights into aerothermodynamics, mesh sensitivity analysis, and shock-wave interactions in hypersonic regimes.
In my role as a Junior Aeromechanic Engineer at the Warsaw Institute of Aviation (EDC), I have gained hands-on experience in running aeromechanical analyses using ANSYS and GageMap, processing and interpreting large datasets from experimental campaigns, and preparing certification documentation. Working in an international team, I have developed strong collaboration and communication skills, ensuring high-precision results while effectively coordinating with engineers from diverse backgrounds.
As a member of the Students' Space Association - Rocketry Division, I contributed to the aerodynamic analysis of key rocket components, including the split canards of the FOK Rocket and the nose cone and fins of the GROT Rocket. This experience has sharpened my ability to optimize aerodynamic performance, troubleshoot complex simulations, and work under tight deadlines within a dynamic, team-driven environment.
My academic journey has also included practical research projects, such as my Bachelor's thesis on the aerodynamic performance of Falcon 9 grid fins across all Mach regimes. I performed detailed CFD analyses, mesh convergence studies, and post-processing in ANSYS Fluent, which deepened my expertise in high-fidelity aerodynamic simulations.
Beyond technical skills, I bring a proactive and problem-solving mindset, excellent adaptability, and a strong ability to work in interdisciplinary teams. My international project collaborations have strengthened my ability to communicate complex engineering concepts effectively. Additionally, I am highly organized, detail-oriented, and thrive in high-pressure environments that require both analytical and creative problem-solving skills.
Passionate about advancing aerospace technology, I am eager to contribute to innovative projects in spacecraft design, reusability, and aerothermodynamic optimization. Whether working independently or in a team, I am committed to continuous learning and pushing the boundaries of aerospace engineering.
Besides that, in my private time I enjoy travelling, whether it is in my close neighbourhood, Poland, or abroad. Lately I have visited Japan and South Korea, where I could observe differences between culture of western Asia and Eastern Europe. As my next trip I am planning to visit the USA and have the oportunity to watch a rocket launch in real life instead of YouTube đ .
This project wasnât just about flow over a wingâit was an appraoch to understand deeply what stands behind differemt CFD approaches. I simulated the iconic NACA 2412 airfoil at Re = 6.85Ă10â¶ using three turbulence strategiesâuRANS, DES, and LESâand analyzed their performance under deep separation conditions. The goal? Pinpoint how each model handles vortex shedding, boundary layer behavior, and wake formation under intense aerodynamic stress.
I tailored each mesh from the ground up, tuning yâș levels (~1 for uRANS/DES, less than 5 for LES), scaling inflation layers, and ensuring wake regions aligned with Taylor microscales. Solver stability was maintained using a density-based scheme, with CFL-guided timestep refinement. Even with LES pushing computer power limits, I captured the raw turbulence truth for 1 full second of physical timeâenough to see structures form, evolve, and stabilize.
The takeaway? uRANS is efficient but blind to dynamics. DES is a middle-ground. LES is kingâif my hardware survives đ . This study taught me when and where to deploy each model for high-fidelity CFD. A perfect analog for reentry vehicle flows, rocket separation dynamics, or any system where vortex truth matters more than just convergence.
đ„ Lessons Learned
- Hybrid turbulence strategy mastery: I now know how to pick, tune, and justify RANS/DES/LES depending on flow physics, separation behavior, and CPU/GPU availability.
- Mesh art for turbulence: Creating LES-grade meshes meant resolving down to Kolmogorov scales in separation zonesâan essential skill for complex simulations.
- Boundary layer resolution obsession: Achieving yâș â 1 and watching separation points shift gave me intuitive control over wall modeling and transition detection.
- Real-world turbulence intuition: I developed an eye for what turbulence "should" look likeâbeyond residualsâbased on vorticity patterns.
- Hardware balancing act: Managing LES simulations on a limited setup taught me how to optimize solver settings, post-process on-the-fly, and schedule smart saves.
- Communication under chaos: Turning 6 million cells and 3 turbulence models into one clear comparison table made me better at telling engineering stories.

Control Volume

RANS mesh Boundary Layer Modeling

DES mesh Boundary Layer Modeling

LES mesh Boundary Layer Modeling

RANS mesh

DES mesh

LES mesh

RANS mesh closeup

DES mesh closeup

LES mesh closeup
project 2
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project 3
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project 4
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project 4 (Hobby)
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project 5
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project 6
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project 7
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Bachelor Thesis: Falcon 9 Grid Fin Aerodynamics
My Bachelor thesis, titled "Aerodynamic Performance Analysis of Falcon 9 Grid Fins: A Computational Investigation", was a deep-dive CFD study into the aerodynamics of reusable rocketry. I analyzed the flow behavior around SpaceXâs Falcon 9 titanium grid fins across subsonic, transonic, and supersonic regimes, using ANSYS Fluent and the SST k-Ï turbulence model.
I developed high-fidelity 2D and 3D CFD models of the grid fin mounted on the booster stage, executed mesh sensitivity studies, and extracted aerodynamic coefficients (drag, lift, moment) across multiple Mach numbers. Realistic conditions were modeled based on actual Falcon 9 reentry altitudes and speeds, and the simulations revealed valuable insights about shockwave interaction, flow separation, and boundary layer behavior.
While the simulations were limited to Mach 1.91 due to hardware constraints, I ensured full convergence and physical accuracy through optimized meshing, inflation layers, and adaptive solver control. The final results showed how the back-swept design of SpaceX's titanium fins significantly improves supersonic performance and delays wave drag onsetâa key factor for reentry control.
đ Lessons Learned
- Mastering mesh quality: By tuning inflation layers for aâŻyâș around 1, I learned firsthand how aâŻwellâconstructed mesh can dramatically improve shock capturing and solution stability in supersonic flows.
- Modeling highâspeed air: Setting up correct boundary conditions and gas properties for MachâŻ>1 taught me the nuances of realâgas effects and how to predict bowâshock angles with confidence.
- Bowâshock familiarity: Watching shock waves wrap around grid fins showed me the practical side of obliqueâshock theoryâand inspired me to explore controlâsurface interactions in highly sonic conditions.
- Deepening CFD theory: Building everything soloâfrom geometry cleanup to solver setupâgave me a solid grasp of turbulence models (SST kâÏ), convergence criteria, and when to trust residuals versus physical trends.
- Independent problemâsolving: Tackling mesh refinement, solver crashes, and postâprocessing challenges alone honed my resilienceâand taught me to document each step so future peers (or employers) can pick up where I left off.
- Communicating complexity: Presenting my results to faculty members sharpened my ability to translate dense CFD data into clear, actionable insightsâan essential skill for any collaborative engineering environment.
Intermediate Project 2
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Masters Thesis
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Additional Project
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DSMC
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CFD-DSMC
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Kinetic Boltzmann
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ML Add-ons
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