Supercritical Wing Flutter
Final technical rept. 1 Aug 1977-1 Mar 1978
DOUGLAS AIRCRAFT CO LONG BEACH CA AIRCRAFT DIV
Pagination or Media Count:
Transonic methods for correcting subsonic oscillatory aerodynamic influence coefficients AICs based on the Doublet Lattice Method for use in flutter and dynamic response analyses of supercritical wings are developed and applied to a TF-8A flutter model and the YC-15II prototype aircraft. The effects of static aeroelasticity are included and evaluated. Reynolds number effects on test results are discussed. Correlation of improved methods showed good agreement with test results. For the two applications included, the steady corrections dominated the unsteady corrections. In the process of developing transonic corrections a new transonic lifting surface theory currently two- dimensional is presented, explored and correlated using the NLR 7301 airfoil. The effects of shock wave motion are included in the theory.