Application of axisymmetric analog to unstructured grid for aeroheating prediction of hypersonic vehicles
International Journal of Numerical Methods for Heat & Fluid Flow
ISSN: 0961-5539
Article publication date: 15 May 2009
Abstract
Purpose
The purpose of this paper is to present an engineering inviscid‐boundary layer method for the calculation of convective heating rates on three‐dimensional non‐axisymmetric geometries at angle of attack.
Design/methodology/approach
Based on the axisymmetric analog, convective heating rates are calculated along the surface streamlines which are determined using the inviscid properties calculated on an unstructured grid.
Findings
Since the method is capable of using inviscid properties calculated on an unstructured grid, it is applicable to a variety of configurations and it requires much less computational effort than a Navier‐Stokes code. The results of the present method are evaluated on different wing body configurations in laminar and turbulent hypersonic equilibrium flows. In comparison to experimental data, the present results are found to be fairly accurate in the windward and leeward regions.
Practical implications
With this approach, heating rates can be predicted on general three‐dimensional configurations at hypersonic speeds in an accurate and fast scheme.
Originality/value
In order to calculate the heating rates at any specific point on the surface, a technique is developed to calculate the inviscid surface streamlines in a backward manner using the inviscid velocity components. The metric coefficients are also calculated using a new simple technique.
Keywords
Citation
Parhizkar, H. and Karimian, S.M.H. (2009), "Application of axisymmetric analog to unstructured grid for aeroheating prediction of hypersonic vehicles", International Journal of Numerical Methods for Heat & Fluid Flow, Vol. 19 No. 3/4, pp. 501-520. https://doi.org/10.1108/09615530910938407
Publisher
:Emerald Group Publishing Limited
Copyright © 2009, Emerald Group Publishing Limited