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- W2007456163 abstract "Numerical solutions for supersonic flow at Mach number 1.5 past the AGARD 10 deg axisymmetric nozzle boattail with jet exhaust are obtained using the Navier-Stokes equations. The major objective is to show that such a complex flow can be computed successfully, rather than emphasizing accuracy or computational efficiency. MacCormack's explicit second-order accurate scheme is used together with surface-oriented coordinates obtained through a numerical mapping procedure. Five cases were computed showing the effects of boattail geometry, jet exhaust temperature, boattail temperature, and the differences from the corresponding two-dimensional nozzle geometry. It was found that the hot exhaust and the hot boattail surface both result in lower pressure drag. The surface pressure coefficient distribution and contours of other variables are provided. Comparison with the limited available experimental results is made with the possible interpretation for the deviation being discussed. Several recommendations for improving accuracy are suggested." @default.
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- W2007456163 date "1980-08-01" @default.
- W2007456163 modified "2023-09-26" @default.
- W2007456163 title "Computation of a Supersonic Flow Past an Axisymmetric Nozzle Boattail with Jet Exhaust" @default.
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- W2007456163 doi "https://doi.org/10.2514/3.50828" @default.
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