Measurements of the effects of Thickness Ration and aspect ratio on the Drag of Rectangular-Plan-Form Airfoils at Transonic Speeds
Abstract
Free-fall tests were conducted on several airfoils to determine effect of airfoil parameters on drag at transonic and supersonic speeds. For airfoils with thickness ratios of from 0.06 to 0.12, reduction of aspect ratio delayed occurrence of drag rise by about of 0.02 Mach; it decreased drag at higher speeds. Pressure-drag coefficient ratio at sonic and low supersonic speeds varied in proportion to square of thickness ratio of 0.09 and 0.12; between ratio of 0.06 and 0.09, exponent was slightly less than 2.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1947
- Accession Number
- ADB813751
Entities
People
- C. W. Mathews
- J. R. Thompson
Organizations
- National Aeronautics and Space Administration