Numerical Framework for Aerospace Applications: from Subsonic to Hypersonic NonEquilibrium
We developed the highfidelity simulation framework for various aerospace applications ranging from subsonic to hypersonic nonequilibrium flow regimes. The applications include aerodynamics and rotor control for urban air mobility and eVTOL vehicles, buffeting of the tail and wings during transonic regime, understanding the effect of turbulence on aircraft performance during the transonic regimes, reentry vehicles (including problems with ionization and ablation), and more. The framework is based on stabilized and variational multiscale methods for fluid mechanics. The finite elements method (FEM) is used for discretization and special techniques (weak imposition of the Dirichlet boundary conditions and sliding interface formulation) is adopted to simulate complex flow behaviour.
Aerodynamic simulation (right) of the ducted propeller for smallscale UAVs (top)
Our group is currently working on extending the framework to the highspeed reacting flows, including the combustion modeling, and fluidthermalstructure interaction (FTSI).
Aerodynamic simulation (top) of the makeup model of the Kratos XQ58A Valkyrie UAS (bottom) at the subsonic flow regime.
Numerical simulation of the double cone at M=12.2, Re=1.5e+5, H=5.44 MJ/kg. Two simulations are performed, reacting equilibrium and reacting nonequilibrium. Results shown are: 2D slice of the Mach contour (left), surface pressure distribution (righttop), surface heat transfer distribution (rightbottom). Results are compared with experiment from LENS facility, LAURA and US3D codes.
Mach contours and wall pressure coefficient distribution for the VLC capsuleat angle of attack of 20degree, M=6, Re=1.24e+6: the full energy predictions (left), results predicted by LAURA code (centre), normal force coefficient (right).
Publications

M. R. Rajanna, M. Jaiswal, E. L. Johnson, N. Liu, A. Korobenko, Y. Bazilevs, J. Lua, N. Phan, M.C. Hsu
Fluid–structure interaction modeling with nonmatching interface discretizations for compressible flow problems: simulating aircraft tail buffeting, Computational Mechanics, 2023, under review 
D. Codoni, A. Bayram, M. Rajanna, C. Johansen, M.C. Hsu, Y. Bazilevs, A. Korobenko
Heat flux prediction for hypersonic flows using stabilized formulation, Computational Mechanics, 2023, accepted 
B. Dalman, A. Korobenko, P. Ziade, A. RamirezSerrano, C. Johansen
Validation and verification of a conceptual design tool for evaluating smallscale, supersonic, unmanned aerial vehicles, 2023, under preparation 
M. R. Rajanna, E. L. Johnson, F. Xu, N. Liu, J. Lua, N. Phan, Y. Bazilevs, A. Korobenko, M.C. Hsu
Fluid–structure interaction modeling with nonmatching interface discretizations for compressible flow problems: application to aircraft simulations, Mathematical Models and Methods in Applied Sciences, 32(12), 24972528, 2022 
D. Codoni, C. Johansen, A. Korobenko
A StreamlineUpwind PetrovGalerkin stabilized method for the analysis of nonionized reacting hypersonic flows in thermal nonequilibrium, Computer Methods in Applied Mechanics and Engineering, 398, 115185, 2022 
M. Rajanna, E. L. Johnson, D. Codoni, A. Korobenko, Y. Bazilevs, N. Liu, J. Lua, N. Phan, M.C. Hsu
Finite element methodology for aircraft aerodynamics: development, simulation, and validation, Computational Mechanics, 70(3), 549563, 2022 
G. Doerksen, P. Ziade, A. Korobenko, C. Johansen
A numerical investigation of recirculation in axisymmetric confined jets, Chemical Engineering Science, 254, 117603, 2022 
D. Codoni, G. Moutsanidis, M.C. Hsu, Y. Bazilevs, C.T. Johansen, A. Korobenko
Stabilized finite element formulation for highspeed compressible flows: towards hypersonic simulations, Computational Mechanics, 67(3), 785809, 2021 
H. H. Stoldt, C. T. Johansen, A. Korobenko, P. Ziadé
Verification and Validation of a HighFidelity OpenSource Simulation Tool for Supersonic Aircraft Aerodynamic Analysis, Journal of Verification, Validation and Uncertainty Quantification,6(4), 041005 (11 pages), 2021