Application of the NASA Kernel-Function Procedures to Generally Deforming Wings

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Report Number: ASD TDR 62-409
Author(s): None Given
Corporate Author(s): Aerojet-General Corporation
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1962-10
Pages: 44
Contract: AF 33(616)-7420
DoD Project: 1370
DoD Task: 137003
Identifier: AD0289882

A method is described for obtaining generalized aerodynamic forces by utilizing the NASA KernelFunction Procedures. An evaluation of the generalized aerodynamic forces and the consequent flutter conditions is made for the particular case of a uniform, cantilevered, 70 degree delta wing. The supersonic Kernel-Function Procedure was found to be inadequate for treating the elastic modes on this low-aspect-ratio wing; the subsonic procedure, however, appears to work satisfactorily. The theoretical flutter predictions are compared with the experimental results of NASA Report TM X-53 (AD-222 902). The Kernel-Function predictions for quasi-steady flow (k approaches O) appear to be superior to those for the complete unsteady case k = omega sub fc sub r/2V sub f. Based on this limited comparison, it appears that for this low-aspect-ratio wing the large transient effects predicted by linearized theory in the transonic regime may not actually exist.

Provenance: Lockheed Martin Missiles & Fire Control

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