Accession Number:

ADA023690

Title:

A Wind Tunnel Captive Aircraft Testing Technique

Descriptive Note:

Final rept. 1 Jul 1974-30 Jun 1975

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1976-04-01

Pagination or Media Count:

37.0

Abstract:

A captive aircraft testing technique has been developed for use in the 16-ft wind tunnels at the Arnold Engineering Development Center AEDC. With the captive system, an aircraft motion study may be conducted in the wind tunnel with the tunnel acting as an analog forcing function. The large static aerodynamic data matrix normally required for a motion study has been alleviated. The system validity is established by a comparison of F-15 aircraft motion generated in the wind tunnel with flight motion of a NASA 38-scale F-15 Remotely Piloted Vehicle RPV. Good agreement between the longitudinal and lateraldirectional motions of the model was achieved in the absence of RPV unsteady aerodynamics wing buffet. The captive technique ability to efficiently define changes in aircraft flight characteristics resulting from different external store configurations is demonstrated.

Subject Categories:

  • Pilotless Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE