An investigation of the half-model reflection-plane technique for dynamic stability testing at transonic Mach numbers /
T.O. Shadow.

Description

Main Author

Shadow, T. O.

Related Names

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

Language(s)

English

Published

Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1977.

Subjects

Aerodynamics, Transonic.
Stability of airplanes.
Aerodynamic heating.

Summary

An experimental investigation was made to determine the feasibility of the half-model reflection-plane technique for measuring dynamic stability derivatives in the transonic speed range. Three model configurations simulating an aircraft, a missile, and a bluff body were investigated both full and half span at Mach numbers from 0.6 to 1.2 and angles of attack from -2 to 90 deg. The half-model reflection-plane technique fully duplicated the full-span results only at subsonic subcritical speeds and angles of attack up to 20 deg. In tests at higher Mach numbers in the transonic range and higher angles of attack up to 90 deg, it was not demonstrated that the half-model technique can provide better than qualitative, order of magnitude results.

Note

"January 1977."
"Final Report: January 16, 1973 -- March 31, 1976."

Physical Description

93 pages : illustrations ; 28 cm

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