Numerical computation of aeroelastically corrected transonic loadsA numerical scheme is presented for the computation of transonic aerodynamic loads on flexible wings. The method consists of iteratively applying the loads computed by a 3D transonic aerodynamics code to a structural model to obtain elastic twist, and then recomputing the loads. Because this iteration is performed concurrently with the iterations performed in computing the aerodynamics, flexible loads are obtained in roughly the same amount of computing time as required to obtain rigid loads. Applications of this method to a flexible supercritical transonic transport wing are presented and compared with model test data.
Document ID
19790045007
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Chipman, R. (Grumman Aerospace Corp. Bethpage, NY, United States)
Waters, C. (Grumman Aerospace Corp. Bethpage, NY, United States)
Mackenzie, D. (Grumman Aerospace Corp. Bethpage, N.Y., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-0766
Meeting Information
Meeting: Structures, Structural Dynamics, and Materials Conference