MEASUREMENT OF BOUNDARY-LAYER TRANSITION ON A STANDARD MODEL TO DETERMINE THE RELATIVE DISTURBANCE LEVEL IN TWO SUPERSONIC WIND TUNNELS
Abstract
The boundary-layer transition on a slender cone was observed for 1.9 less than or equal to M less than or equal to 4.2 in 2 supersonic wind tunnels. A 5 total apex angle cone, 50 cm long and 4.5 cm in diameter at the base, was used as a standard. The transition in the boundary layer was determined by a luminescent lacquer technique and by spark-schlieren photography. The investigation showed that the location of the transition is a measure of the disturbance level in the wind tunnel, and that the slender cone is a suitable model to indicate differences in disturbance level. Disturbances introduced in the subsonic portion of the tunnel appeared in measurable magnitude in the supersonic flow. A decreasing Reynolds number of transition was observed with increasing Mach number.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 19, 1953
- Accession Number
- AD0015004
Entities
People
- A. H. Lange
- L. P. Gieseler
Organizations
- Naval Ordnance Laboratory