A Wind Tunnel Captive Aircraft Testing Technique
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 3/8-scale F-15 Remotely Piloted Vehicle (RPV). Good agreement between the longitudinal and lateral/directional 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1976
- Accession Number
- ADA023690
Entities
People
- R. W. Butler
Organizations
- Arnold Engineering Development Complex