Estimation of Longitudinal Unsteady Aerodynamics of a Wing-Tail Combination from Wind Tunnel Data

Abstract

This paper presents an initial step toward model identification from wind tunnel data for an airliner configuration. Two approaches to modeling a transport configuration are considered and applied to both steady and large-amplitude forced-oscillation wind tunnel data taken over a wide range of angles of attack. Only limited conclusions could be drawn from this initial data set. Although model estimated time histories of normal force and pitching moment agree reasonably well with the corresponding measured values, model damping parameters did not, for some cases, have values consistent with small amplitude oscillatory data. In addition, large parameter standard errors implied poor information content for model structure determination and parameter estimation. Further investigation of the modeling problem for more general aerodynamic models is recommended with close attention to experiment design for obtaining parameters with high accuracy.

Nonlinear Unsteady Aerodynamic Modeling Using Wind-Tunnel and Computational Data

“…[26][27] provided further insights into modeling aerodynamic responses for configuration components of body-tail, bodywing, and body-wing-tail. Calculation of steady downwash and aerodynamic center change with respect to angle of attack were performed in [26] for the GTM configuration and in [28] for a model provided by the Central Aerohydrodynamic Institute (TsAGI). Ref.…”

On Problems Associated with Modeling Wing-Tail Configurations from Wind Tunnel Data

“…11 were used again in model identification and the results are summarized in Ref. 12. The identified models for different configurations mostly fit the measured data quite well.…”