This page is the portfolio of Hyunbin Kang, a master's student at Inha University, Department of Aerospace Engineering, Aerodynamic Analysis and Design Lab.
Name : Hyunbin Kang
Major : Computational Fluid Dynamics
- High Order Methods
- Hypersonic Aerodynamics
- Panel Methods
Education
- Inha University, Department of Aerospace Engineering, Bachelor's Degree (2017-2022)
- Inha University, Department of Aerospace Engineering, Master Course (2023-)
Email : qls1455@gmail.com(personal), qls1455@inha.edu(education)
Office : Inha University (Aerospace Campus), 36 Gaetbeol-ro, Yeonsu-gu Incheon 21999, Korea
About the projects I was involved in during my Master's Course.
Korean Society for Aeronautical and Space Science
Intro :
- In this study, aerodynamic investigation was conducted with Low Reynolds Number Airfoil of EFD-CFD workshop 5th case *.
- LRN airfoil has complex flow structure, so accurate computational is needed.
- In this study, We utilze the PyFR, a aerodynamic analysis framework using Large Eddy Simulation (LES)
Results :
Spanwise effect
Shorter spanwise length case has pool results of lift coefficients.
lift curve with several spanwise lengthThis result is caused by the 3-D effect of turbulent flow.
Q-criterion at angle of attack of 10 degreeLaminar Separation Bubble (LSB)
- Low Reynolds number flow has a complex flow structure such as laminar separation, transition, reattachment etc.
- This LSB reduce the aerodynamic performance.
- LES can solve the LSB with high resolution.
International Conference of Spactral and High Order Method
Intro :
- Based on the previous study (KSAS), parametric study is conducted for numerical and computational condition.
- Paramters : spanwise length, order of accuracy, grid system, and precision
Results :
Non-linearity
- LSB's movement cause the non-linear aerodynamic characteristics
non-linearity of lift coefficienttime-averaged x directional velocity contour
time-averaged pressure coefficient distributionStall structure :
- At high angle of attack region, LSB is genarated at leading edge of airfoil.
- Since the strong separation can't recover the pressure, full separation from LE to TE is captured.
time-averaged x directional velocity contour at high angle of attackDiscussion :
effect of Spanwise length
- We compared the result with (0.05, 0.1, 0.25, 0.5, 1.0) times of the chord length
- Short span is limited in including 3-D effect
- In high AoA region, spanwise length of 0.5 times of chord length is needed at least.
effect of Order of accuracy
- We performed the simulation with P2, P3, and P4 order with coarse, medium, and fine grid respectively
- If the grid is fine near the surface and wake region, there are slight difference in the case of P2 order compared with P2 and P3 order.
- The simulation with P2 coarse grid has inaccurate result. So lower order case has strong grid dependency.
effect of Grid system
- We constructed structured grid by PointWise and unstructured grid by Gmsh.
- There are no sigmificant difference with two grid system.
- However, there notable difference in computation time
- Unstructured grid's minimum edge length and minimum cell volume is 4 and 13 times smaller than structured grid. So the computation time of unstr case is 9 times larger than the structured case.
effect of precision
- There are no siginficant difference with single and double precision(FP32 and FP64)
Intro :
- Panel method is one of fast techniques of the aerodynamic analysis
- Panel method use the virtal wake panel to predict the lift
- When solving for high angle of attack condition, fixed wake model issues
- So variable wake model must be developed