Accession Number : ADB029329

Title :   Supercritical Wing Flutter.

Descriptive Note : Final technical rept. 1 Aug 77-1 Mar 78,

Corporate Author : DOUGLAS AIRCRAFT CO LONG BEACH CA AIRCRAFT DIV

Personal Author(s) : McGrew, J. A. ; Giesing, J. P. ; Pearson, R. M. ; Zuhuruddin, K. ; Schmidt, M. E.

Report Date : MAR 1978

Pagination or Media Count : 238

Abstract : Transonic methods for correcting subsonic oscillatory aerodynamic influence coefficients (AIC's) 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. (Author)

Descriptors :   *SUPERCRITICAL WINGS, *FLUTTER, AEROELASTICITY, LIFTING SURFACES, TRANSONIC FLOW, DYNAMIC RESPONSE, OSCILLATION, REYNOLDS NUMBER, NONUNIFORM FLOW, SHOCK WAVES.

Subject Categories : Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE