Acoustic environment on the surface of a large-scale powered model of a vectored-engine-over-the-wing STOL configuration
Abstract
The results of an acoustic measurement program on a large, powered, highly maneuverable, supersonic STOL fighter model. The model incorporated vectored engine over the wing (VEO) concept including spanwise blowing to provide lift augmentation. This concept exposes portions of the wing and flap structure to high fluctuating pressure levels. Twelve microphones were installed on the surface of the model to define this environment. Six of these were specially developed high temperature transducers capable of withstanding up to 1093 C. Test parameters included engine pressure ratio, wind tunnel dynamic pressure, angle of attack, yaw angle, flap angle, and canard angle. The effect of each of these parameters on the fluctuating pressure environment was defined. The results show that levels as high as 167 kB exist on the upper surface of the flap. Levels resulting from a prediction method in the literature agreed with the measured values for only very limited conditions.
- Publication:
-
Shock Vibration Information Center Shock Vibration Bulletin
- Pub Date:
- May 1981
- Bibcode:
- 1981SVICB......225S
- Keywords:
-
- Acoustic Measurement;
- Aircraft Models;
- Pressure Oscillations;
- Short Takeoff Aircraft;
- Wing Nacelle Configurations;
- Angle Of Attack;
- Lift Augmentation;
- Microphones;
- Spanwise Blowing;
- Wind Tunnel Tests;
- Acoustics