Approximate convective heating equations for hypersonic flows

Zoby, E. V.; Moss, James N.; Sutton, Kenneth

doi:10.2514/6.1979-1078

“…Approximate expressions for the boundary-layer thickness at both laminar and turbulent conditions are also given in Ref. 17. Results using this technique have been shown to compare favorably with more detailed methods for wind tunnel and ight conditions.…”

Section: Boundary-layer Methodsmentioning

confidence: 99%

“…16 The method has been shown to calculate the inviscid ow eld about 3-D blunted noses as well as 3-D afterbodies reasonably accurately and much faster than numerical solutions of the inviscid Euler equations. 14 In this paper, the approximate inviscid technique employs the axisymmetric analog to predict laminar and turbulent surface heating rates using the approximate convective-heating equations of Zoby et al 17 Both perfect gas and equilibrium-air ows are considered. Improved surface streamlines are calculated based on both the body geometry and surface pressure distribution.…”

Section: Introductionmentioning

confidence: 99%

Engineering aerodynamic heating method for hypersonic flow

Christopher

¹

,

Fred

²

1992

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

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.

show abstract

“…In this study, a set of approximate convective-heating equations developed by Zoby et al 17 is used for the boundary-layer solution. Laminar and turbulent heating rates may be calculated from these relations for both perfect gas and equilibrium-air ows.…”

Section: Boundary-layer Methodsmentioning

confidence: 99%

An engineering aerodynamic heating method for hypersonic flow

Riley

¹

,

Dejarnette

²

1992

30th Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

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.

show abstract

“…On windward surfaces the running length is taken directly as the geometric value, on leeward surface a weighted running length is used. The process is similar to that used in reference [17]. For both laminar and turbulent flows, the weighted reference length, S w , is calculated as The integration is along a streamline.…”

Section: Smentioning

confidence: 99%