Results are presented on models having range of airfoil thickness from 3 to 12% chord for single and double wedge airfoils and tapered planforms and from 9 to 20% chord for double wedge airfoils and square planforms; for test parameters, in general, thickness effects are destabilizing at higher Mach but stabilizing at subsonic and transonic Mach numbers.
Aerodynamic effects of some configuration variables on aero-elastic characteristics of lifting surfaces at Mach numbers from 0.7 to 6.86
NASA -- Tech Note
1961
51 pages
Report
English
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