A free-flight investigation of the effects of simulated sonic turbojet exhaust on the drag of a boattail body with various jet sizes from Mach number 0.87 to 1.50 /
Ralph A. Falanga.

Description

Main Author

Falanga, Ralph A.

Related Names

Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1955.

Subjects

Charts, diagrams, etc.
Drag (Aerodynamics)
Jets > Jets / Fluid dynamics.

Summary

Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provided with simulated-turbojet-exhaust rocket motors were flight-tested to determine the jet interference effects on drag over a Mach number range from approximately 0.87 to 1.5. The results indicated that in the transonic and low-supersonic speed range the jet caused positive pressure increments on the base and boattail which appreciably reduced the configuration drag from the power-off condition. At the high supersonic speeds, the jet caused positive pressure increments only on the base and resulted in a smaller reduction in body drag from power-off conditions.

Note

NACA Research Memorandum L55F09A.
"August 18, 1955."
Title from cover.

Physical Description

23 p. : ill. ; 27 cm.

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