Mathematical modeling of the aerodynamics of high-angle-of-attack maneuversThis paper is a review of the current state of aerodynamic mathematical modeling for aircraft motions at high angles of attack. The mathematical model serves to define a set of characteristic motions from whose known aerodynamic responses the aerodynamic response to an arbitrary high angle-of-attack flight maneuver can be predicted. Means are explored of obtaining stability parameter information in terms of the characteristic motions, whether by wind-tunnel experiments, computational methods, or by parameter-identification methods applied to flight-test data. A rationale is presented for selecting and verifying the aerodynamic mathematical model at the lowest necessary level of complexity. Experimental results describing the wing-rock phenomenon are shown to be accommodated within the most recent mathematical model by admitting the existence of aerodynamic hysteresis in the steady-state variation of the rolling moment with roll angle. Interpretation of the experimental results in terms of bifurcation theory reveals the general conditions under which aerodynamic hysteresis must exist.
Document ID
19800061709
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Schiff, L. B. (NASA Ames Research Center Moffett Field, CA, United States)
Tobak, M. (NASA Ames Research Center Moffett Field, CA, United States)
Malcolm, G. N. (NASA Ames Research Center Moffett Field, Calif., United States)