The phenomenon of separated flow on a series of circular-arc afterbodies was investigated using the Langley 16-foot transonic tunnel at free-stream Mach numbers from 0.40 to 0.95 at 0 deg angle of attack. Both high-pressure air and solid circular cylinders with a diameter equal to the nozzle exit diameter were used to simulate jet exhausts. A detailed data base of boundary layer separation locations was obtained using oil-flow techniques. The results indicate that boundary layer separation is most extensive on steep boattails at high Mach numbers.
Boundary layer separation on isolated boattail nozzles
08.05.1977
Hochschulschrift
Keine Angabe
Englisch
Boundary-layer separation on isolated boattail nozzles
TIBKAT | 1978
|Separation region on boattail nozzles
NTRS | 1980
|Boundary layer thickness effect on boattail drag
AIAA | 1976
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