AERODYNAMIC EFFECTS OF SOME CONFIGURATION VARIABLES ON THE AEROELASTIC CHARACTERISTICS OF LIFTING SURFACES AT MACH NUMBERS FROM 0.7 TO 6.86
Abstract
Results are presented of tests on models having a range of airfoil thickness from 3 to 12 percent chord for single- and double-wedge airfoils and tapered planforms and from 9 to 20 percent chord for double-wedge airfoils and square planforms. The latter airfoils had leading- and trailing-edge radii of 0, 1, 3, and 6 percent chord. For the test parameters, in general, thickness effects are destabilizing at the higher Mach numbers but stabilizing at subsonic and transonic Mach numbers. Bluntness effects are stabilizing at supersonic speeds but are negligible at subsonic speeds. Double-wedge airfoils are more prone to flutter than singlewedge airfoils. Experimental results are compared with calculations using piston-theory aerodynamics.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1961
- Accession Number
- AD0266601
Entities
People
- Perry W. Hanson
Organizations
- National Aeronautics and Space Administration