Engineering aerodynamic heating method for hypersonic flow

Abstract

A capability to calculate surface heating rates has been incorporated in an approximate three-dimensional inviscid technique. Surface streamlines are calculated from the inviscid solution, and the axisymmetric analog is then used along with a set of approximate convectiveheating equations to compute the surface heat transfer. The method is applied to blunted axisymmetric and three-dimensional ellipsoidal cones at angle of attack for the laminar ow of a perfect gas. The method is also applicable to turbulent and equilibrium-air conditions. The present technique predicts surface heating rates that compare favorably with experimental ground-test and ight data and numerical solutions of the Navier-Stokes NS and viscous shock-layer VSL equations.

Application of an engineering inviscid-boundary layer method to slender three-dimensional vehicle forebodies

“…Solutions have been obtained for axisymmetric shapes paraboloids, sphere-cones and simple 3-D shapes blunted elliptic cones at angle of attack. 1 Comparisons with experimental data and NS solutions have shown good agreement. This engineering method provides a unique capability for approximate ow eld solutions over 3-D blunted noses as well as 3-D afterbodies.…”

“…All variables are nondimensionalized as follows: pressure by 1 This geometry models the planform view of the slender 3-D con guration in Fig. 1, and the con guration cannot be described adequately by a conic section.…”

“…This engineering method provides a unique capability for approximate ow eld solutions over 3-D blunted noses as well as 3-D afterbodies. 1 The next step in the development of the THINBL code is to apply it to a realistic vehicle geometry. One such geometry is the slender 3-D forebody characteristic of a transatmospheric vehicle see Fig.…”

Mathematical Modeling of Aerodynamic Heating and Pressure Distribution on a 5-Inch Hemispherical Concave Nose in Supersonic Flow

“…Computational mechanics simulations approach the problem mainly through inviscid-viscous methods thus promising reduced computational time. AEROHEAT and INCHES are two of the simpler methods to approach the phenomenon of aerodynamic heating [2]. Both methods use the axisymmetric analog concept that allows axisymmetric boundary layer techniques to be applied to three-dimensional flows, provided that the surface streamlines are known.…”

“…Another method introduced by Georgia Tech Research Institute [9] named GTSIG (Georgia Tech Signature Inviscid Model) involves the calculation of temperature distribution by creating thermal meshes and partial differential equations. Finally, Christopher J. Riley et al, in their study [2], developed a 3D technique without viscous calculations that has the ability to calculate the degree of surface heating. Surface streamlines are calculated from the inviscid solution and the axisymmetric analog.…”