Dropped and rocket propelled models are tested. American tests give a variation in form drag with thickness at the speed of sound in accordance with the two thirds power law. British tests indicate a constant dray coefficient on frontal area. There is a tendency to reduce drag by introducing taper or reducing aspect ratio on rectangular wings. Results on swept wings are inconsistent but the reduction in drag with sweepback is very pronounced. Tunnel bulge tests indicate that the drag due to lift becomes very large at Mach numbers just below 1.
A Summary of Experimental Data on Wing Characteristics at Transonic Speeds
1948
42 pages
Report
Keine Angabe
Englisch