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
1977-05-08
Theses
No indication
English
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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