An Approximate Engineering Method for Aerodynamic Heating Solution around Blunt Body Nose
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.
[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.
[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.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:63785", author = "Sahar Noori and Seyed Amir Hossein and Mohammad Ebrahimi", title = "An Approximate Engineering Method for Aerodynamic Heating Solution around Blunt Body Nose", 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.", volume = "6", number = "10", pages = "2285-5", }