Description of tests carried out at Rolls Royce (1971) LTD Bristol engine division
Abstract
Three nozzle afterbody models were tested in the Rolls-Royce (1971) Ltd. transonic wind tunnel at Bristol using a model support sting which provided means for boundary layer thickness variation by blowing. The tests covered the Mach number range 0.75 to 0.95 and nozzle pressure ratios were in the range 1.7 to 4.7:1. The model surface static pressure distributions were measured and integrated to obtain pressure drag coefficients. Measurements are also presented of model internal pressures, boundary layer profiles and tunnel wall static pressure distributions.
- Publication:
-
In AGARD Improved Nozzle Testing Tech. in Transonic Flow 22 p (SEE N76-16357 07-34
- Pub Date:
- October 1975
- Bibcode:
- 1975intt.agarQ....H
- Keywords:
-
- Afterbodies;
- Boundary Layers;
- Nozzle Geometry;
- Pressure Distribution;
- Wind Tunnel Tests;
- Pressure Drag;
- Static Pressure;
- Transonic Flow;
- Fluid Mechanics and Heat Transfer