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Inlet boundary-layer shapes on four aircraft forebodies at Mach 6 (1978)

Johnson, C. B. ; Lawing, P. L.

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Publication Date: 2011-08-17

Description: Boundary-layer shape measurements at the engine inlet on four different hypersonic aircraft forebody designs (with no engine on the forebody) are reported. The measurements provide a qualitative assessment of the effectiveness of various forebody geometries as engine inlet precompression surfaces. The designs, tested in a hypersonic tunnel at Mach 6 and a nominal freestream Reynolds number of 30,500,000, included a semiconical forebody, a configuration similar to a slab delta wing, a conical nose blended into a flat surface, and a conical, complex forebody shape. Boundary layer height as a function of forebody compression is shown for each design.

Keywords: AERODYNAMICS

Type: Journal of Aircraft; 15; Jan. 197

Format: text

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