Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel
Abstract
An investigation at Mach 3.5 into the effects of nozzle wall roughness on free stream pressure fluctuations and cone transition Reynolds numbers was conducted in the pilot low disturbance tunnel at the Langley Research Center. Nozzle wall roughness caused by either particle deposits or imperfections in surface finish increased free stream noise levels and reduced the transition Reynolds numbers on a cone mounted in the test rhombus.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- September 1985
- Bibcode:
- 1985STIN...8534355C
- Keywords:
-
- Aerodynamic Noise;
- Boundary Layer Transition;
- Conical Nozzles;
- Free Flow;
- Nozzle Flow;
- Transition Flow;
- Aerodynamic Characteristics;
- Mach Number;
- Reynolds Number;
- Supersonic Wind Tunnels;
- Wind Tunnel Tests;
- Fluid Mechanics and Heat Transfer