Assessment of Real Gas Effects on Approximate and Boundary Layer Equations for Hypersonic Laminar Flow over Axisymmetric Bodies

Abstract:

Two efficient computational procedures based on the boundary layer equations and approximate relations areassessedin prediction of the laminar hypersonic flowfield for both the perfect gas and equilibrium air around the axisymmetric blunt body configurations. For the boundary layer procedure, the boundary layer equationsutilize the integral matrix solution algorithm for the blunt nose and after body region by using a space marching technique. The integral matrix procedure able us to create accurate and smooth results using the minimum grid in the boundary layer and minimize the computational costs. Applying the approximate method creates a robust and efficient code for heating calculations over the blunt bodies which flies in hypersonic regimes. These algorithms are highly appropriate to design of hypersonic reentry vehicles. The effects of real gas on the flowfield characteristics are also studied in two procedures.

• Periodical: Advanced Materials Research (Volume 1016)
• Pages: 534-539
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.1016.534
• Online since: August 2014
• Authors: Ramin Kamali Moghadam*, Seyed Amir Hosseini
• Keywords: Approximate Method, Boundary Layer Equations, Equilibrium Air, Hypersonic Flow

References

[1] R.M. Kendall, E.P. Bartlett, R.A. Rindall, and C.B. Moyer, An analysis of chemically reacting boundary layer, (Issued by originator as Aerotherm Report No. 66-7, Part 1, 1961).

[2] D.A. Kopriva, Spectral Solution of the Viscous Blunt Body Problem. II: Multidomain Approximation, ( ICASE Report No. 94-73, 1994).

[3] R. Kamali-Moghadam, Dual-code TLNS-PNS solution procedure for efficient computing equilibrium hypersonic axisymmetric flows, (Ms. Thesis, The Sharif University of Technology, Tehran, Iran, December 2005).

[4] S. Srinivasan, J.C. Tannehill and K.J. Weilmuenster, Simplified curve fits for the thermodynamic properties of equilibrium air, (NASA RP-1-313, 1986).

[5] S. Srinivasan, J.C. Tannehill and K.J. Weilmuenster, Simplified curve fits for the transport properties of equilibrium air, (NASA RP-1181, 1987).

[6] E.V. Zoby, J.J. Moss, and K. Sutton, Approximate convective-heating equations for hypersonic flows , (Journal of Spacecraft and Rockets, Vol. 18, No. 1, pp.64-70, 1981).

DOI: 10.2514/3.57788

[7] F.R. Dejarnette , and H.H. Hamilton, K.J. Weilmuenster, and F.M. Cheatwood, A review of some approximate methods used in aerodynamic heating analysis, (Jurnal of Thermo physics, Vol. 1, No. 1, pp.5-12, 1978).

DOI: 10.2514/6.1985-906

[8] E.R.G. Eckert, 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).

[9] B.A. Bhutta and C.H. Lewis, Comparison of hypersonic experiments and PNS predictions, Part I: Aerothermodynamics, (Journal of Spacecraft and Rockets 28 (4), 1991).

DOI: 10.2514/3.55626

[10] C.G. Miller, J.R. Micol and P.A. Gnoffo, Laminar heat-transfer distribution on biconics at incidence in hypersonic-hypervelocity flows, (NASA TP-2213, 1985).

DOI: 10.2514/6.1983-1508