THE EFFECT ON DRAG OF USING DISTRIBUTED GRIT FOR FIXING BOUNDARY LAYER TRANSITION ON A CONE-CYLINDER MODEL AT TRISONIC SPEEDS
Technical Report
·
OSTI ID:4039203
The drag of a cone-cylinder, swept-fin model was measured at Mach numbers of 0.6 to 3.0 in the 12-in. trisonic wind tunnel. Measurements were made with and without 5 and 10-mil distributed roughness bands (carborundum dust) on the nose cone and the leading fin edge to fix turbulent boundary layer flow over the model. Comparison of theoretical drag estimates with the measured values indicated a turbulent boundary layer on the clean (no roughness) model at most test conditions. (auth)
- Research Organization:
- Sandia Lab., Albuquerque, N. Mex.
- DOE Contract Number:
- AT(29-1)-789
- NSA Number:
- NSA-18-019473
- OSTI ID:
- 4039203
- Report Number(s):
- SC-RR-64-508
- Country of Publication:
- United States
- Language:
- English
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