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Computation of aerodynamic coefficients of a re-entry vehicle at Mach 6

  • R.C. Mehta (Department of Aeronautical Engineering, Noorul Islam Centre for Higher Education) ;
  • E. Rathakrishnan (Department of Aerospace Engineering, Indian institute of Technology)
  • Received : 2023.09.06
  • Accepted : 2023.11.28
  • Published : 2023.09.25
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Abstract

The paper evaluates the aerodynamic coefficients on a blunt-nose re-entry capsule with a conical cross-section followed by a cone-flare body. A computer code is developed to solve three-dimensional compressible inviscid equationsfor flow over a Space Recovery Experiment (SRE) configuration at different flare-cone half-angle at Mach 6 and angle of attack up to 5°, at 1° interval. The surface pressure variation is numerically integrated to obtain the aerodynamic forces and pitching moment. The numerical analysis reveals the influence of flare-cone geometry on the flow characteristics and aerodynamic coefficients. The numerical results agree with wind tunnel results. Increase of cone-flare angle from 25° to 35° results in increase of normal force slope, axial forebody drag, base drag and location of centre of pressure by 62.5%, 56.2% and 33.13%, respectively, from the basic configuration ofthe SRE of 25°.

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References

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