Numerical Solution of a Supersonic Nozzle Afterbody Flow with Jet Exhaust
- 1 June 1979
- report
- Published by Defense Technical Information Center (DTIC)
Abstract
Numerical solutions to the compressible turbulent Navier-Stokes equations for supersonic flow at Mach number 1.5, past an axisymmetric nozzle boattail with jet exhaust were obtained using MacCormack's explicit numerical scheme. The AGARD 10 deg.-nozzle was considered and a total of five cases were computed showing the effects of boattail geometry, jet-exhaust temperature, boattail wall temperature and the differences with the corresponding two- dimensional case. It was established that the hot boattail surface reduces the pressure drag significantly as does the hot jet exhaust when compared with the cold wall, cold exhaust case. The present approach can be used directly for boattailing nozzles for minimum pressure drag, as well as for a parametric study for aircraft designers.Keywords
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