Accession Number:

AD0749154

Title:

Wind Tunnel Design for Testing V/STOL Aircraft in Transition Flight.

Descriptive Note:

Final rept.,

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN

Personal Author(s):

Report Date:

1972-09-01

Pagination or Media Count:

103.0

Abstract:

Wind tunnels have afforded the best potential for studying regions of aerodynamic uniqueness of VSTOL aircraft, but they have been of limited value because of the magnitude of the flow interference they introduce. A new wind tunnel concept is described for covering the spectrum of transition testing from hover throughout wing sustained flight. The wall interference corrections are physically produced by the structure of the wall. A small scale tunnel was designed, constructed, and tested employing this concept. Data from a small rotor model were obtained in the new tunnel and a large conventional one as a basis for comparative evaluation. Author

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE