Unsteady Pressures Due to Control Surface Rotation at Low Supersonic Speeds - Comparison between Theory and Experiment
Abstract
This paper was presented during the 42nd Meeting of the Structures and Materials Panel in Ottawa in April 1976. It deals with a serious difficulty in unsteady aerodynamics, that is the prediction of the pressure field induced by the rotation of a control surface. Much work has already been done on this subject in subsonic flow, but this is one of the first approaches to the supersonic problem. Predictions have been made by two methods developed separately by British Aircraft Corporation and Messerschmitt-Bolkow-Blohm. They have been compared with windtunnel tests made at NLR using more than 80 pressure tubes. Pressure distributions, hinge moments and lift have been measured for different sections of the wing. As the two theories that have been used are linearised, the agreement between theory and experiments is not perfect but appears to be adequate for flutter speed prediction.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1976
- Accession Number
- ADA030966
Entities
People
- C. G. Lodge
- Heinz Schmid
Organizations
- AGARD