Mass injection and jet flow simulation effects on transonic afterbody drag /
Wladimiro Calarese, Ronald E. Walterick.

Description

Main Author

Calarese, Wladimiro

Related Names

Walterick, Ronald E., author.
United States. Air Force.
Air Force Flight Dynamics Laboratory (U.S.)

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1978.

Subjects

Angle of attack (Aerodynamics)
Body of revolution.
Aerodynamics, Transonic.
Drag (Aerodynamics)

Summary

An experimental investigation has been performed to determine the effects of boattail injection and jet flow simulation on the afterbody drag of a slender body of revolution in the transonic regime at zero angle of attack, such as engine nacelles and boattailed afterbodies with isolated engines. A correlation between sting and jet diameter has been established. The jet plume and the nozzle pressure ratio simulators have been found appropriate and useful as a testing technique. Boattail mass injection usually produces a drag coefficient reduction and is more effective at high nozzle pressure ratios. Boattail injection is more effective if used in regions of separated flow. (Author).

Note

"Final report for period February 1977 - September 1977."
"June 1978."

Physical Description

xi, 170 pages : illustrations ; 28 cm.

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