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METHODS OF CALCULATING AERODYNAMIC LOADS ON AIRCRAFT STRUCTURES: PART II - NONLINEAR EFFECTS.
MASSACHUSETTS INST OF TECH CAMBRIDGE
A method is presented for analysis of the nonlinear aerodynamics of slender configurations with vortex separation. Primary emphasis is on the nonlinear component of the aerodynamic characteristics. The theory is intended to be mathematically tenable yet give results of acceptable accuracy. A technique for analyzing the nonlinear aeroelastic problem is given followed by a method for obtaining the nonlinear aerodynamics of wings, bodies, and their combinations. Comparisons with experiment are provided. The experimental comparisons with the wing results indicate that the theory overestimates the nonlinear forces at high angles of attack. The results indicate directions for further research. Author
Final rept. Oct 64-Apr 66,
See also Part 3, AD-804 299.