An Approximate Engineering Method for Aerodynamic Heating Solution around Blunt Body Nose

Authors: Sahar Noori, Seyed Amir Hossein, Mohammad Ebrahimi

Abstract:

This paper is devoted to predict laminar and turbulent heating rates around blunt re-entry spacecraft at hypersonic conditions. Heating calculation of a hypersonic body is normally performed during the critical part of its flight trajectory. The procedure is of an inverse method, where a shock wave is assumed, and the body shape that supports this shock, as well as the flowfield between the shock and body, are calculated. For simplicity the normal momentum equation is replaced with a second order pressure relation; this simplification significantly reduces computation time. The geometries specified in this research, are parabola and ellipsoids which may have conical after bodies. An excellent agreement is observed between the results obtained in this paper and those calculated by others- research. Since this method is much faster than Navier-Stokes solutions, it can be used in preliminary design, parametric study of hypersonic vehicles.

Keywords: Aerodynamic Heating, Blunt Body, Hypersonic Flow, Laminar, Turbulent.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1083613

References:

[1] Shaw ST, Shan C. and Qin N. Development of a local MQ-DQ-based stencil adaptivemethod and its application to solve incompressible Navier-Stokes equations. Int JNumer Meth Fluids, Vol. 55, Issue 4, pp367 - 386, 2007.
[2] Shaw S.T. and Qin N. Solution of the Navier-Stokes equations for the flow around anaerofoil in oscillating free stream. Proceeding of the 20th Congress of the International Council of the Aeronautical Sciences, ICAS, Vol.1, pp19-29. ISBN 1-56347-219-8, 1996.
[3] Scalabrin L.C. and .Boyad L.D. Development of an unstructured Navier- Stokes for hypersonic nonequilibrium aerothermodynamics. 38th AIAA Thermo physics Conference, June 2005.
[4] Birch T., Prince S., Ludlow D.K and Qin N. The application of a parabolized Navier-Stokes solver to some hypersonic flow problems. AIAA 1753- 2001.
[5] Esfahanian V., Hejranfar K. and Mahmoodi Darian, H. Implementation of high-order compact finite-difference method to iterative parabolized Navier-Stokes equations.
[6] Proceedings of the 25th International Congress of the Aeronautical Sciences, ICAS2006, Hamburg, Sept, 2006.
[7] Noori S., Ghasemloo S. and Mani M. A., new method for solution of viscous shock layer equations. Journal of Aerospace Engineering, Vol. 224, part G, 2010.
[8] Miner E. W. and Lewis C. H., Hypersonic ionizing air viscous shock-layer flows over nonanalytical blunt bodies. NASA CR-2550, May 1975.
[9] Kuchi-Ishi S. The development of a new viscous shock-layer code for computing hypersonic flow around blunted body and Its applications. JAXA Research and Development Report, RR-05-001E, 2005.
[10] Thompson R. A., Comparison of nonequilibrium viscous shock-layer solutions with shuttle heating measurements. Journal of Thermophysics and Heat Transfer, Vol.4, No. 2, PP. 162-169, 1990.
[11] Hamilton H. H., Greene F. A. and Dejarnette F. R., An approximate method for calculating heating rates on three-dimensional vehicles. AIAA paper 93-2881, 1993.
[12] Zoby E. V. and simmonds A. L., Engineering flow field method with angle-of-attack applications. Journal of spacecraft and rockets, Vol. 22, No. 4, PP.398-405, 1985.
[13] Hamilton H. H., Greene F. A. and DeJarnette F. R. Approximate method for calculating heating rates on three-dimensional Vehicles. Journal of Spacecraft and rockets. Vol.31. No. 3, pp. 345-354. 1994.
[14] Maslen S.H. Inviscid hypersonic flow past smoth symmetric bodies. AIAA Journal, Vol. pp.1055-1061, 2, July 1964.
[15] Zoby E. V, Moss J. J and Sutton K. Approximate convective-heating equations for hypersonic flows. Journal of Spacecraft and Rockets, Vol. 18, No.1, pp.64- 70, 1981.
[16] Eckert E.R.G. Engineering relations for friction and heat transfer to surfaces in high velocity flow. Journal of the Aeronautical Sciences, Vol.22, No.8, pp. 585-587, 1955.
[17] Van Dyke, Milton D, and Gordon, Helen D. Supersonic flow past a family of blunt axisymmetric bodies. NASA TR R-1, 1959.
[18] Holt M and Hoffman G. Calculation of hypersonic flow past sphere and ellipsoids. American Rocket Soc., 61-209-1903., June 1961.
[19] Mitcheltree R. A, DiFulvio M, Horvath T. J and Braun R. D. Aero thermal heating predictions for mars microprobe. AIAA paper 98-0170, 1998.
[20] Murray A. L and Lewis C. H., Hypersonic three-dimensional viscous shock layer flows over blunt bodies. AIAA Journal, Vol. 16: pages 1279-1286, December 1978.
[21] Hollis B. R. and Perkins J. N. High enthalpy and perfect gas heating measurements on blunt cone. Journal of Spacecraft and Rockets, Vol. 33, No.5, pp.628-634, 1996.
[22] Miller III. C. G. Measured pressure distributions, aerodynamic coefficients, and shock shapes on blunt bodies at Incidence in Hypersonic Air and CF4. NASA TM-84489, Sept, 1982.