Wind tunnel investigation of aerodynamic loads on weapons separated from carriage under the wing of a tactical fighter aircraft at supersonic speeds /
J.C. Donaldson.

Description

Main Author

Donaldson, J. C.

Related Names

ARO, Inc.
Arnold Engineering Development Center
United States. Air Force.

Language(s)

English

Published

Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973.

Subjects

Aerodynamic load.
Jet fighter planes > Jet fighter planes / Wind tunnel testing.

Summary

Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).

Note

Report was prepared by ARO, Inc., a subsidiary of Sverdrup & Parcel and Associates, Inc.
"Final Report for Period January 23 to February 20, 1973."
"June 1973."

Physical Description

viii, 41 pages : illustrations, 28 cm

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