Stall Buffet Modeling using Swept Wing Flight Test Data

Master thesis (2019)

Authors

S. Marschalk Aerospace Engineering

Contributors

C.C. de Visser (supervisor 1)
D.M. Pool (supervisor 2)
Q. P. Chu (supervisor 2)
J. Sodja Aerospace Structures & Computational Mechanics - Aerospace Engineering (supervisor 2)
D. van Os GKN Aerospace (supervisor 2)
Faculty
Aerospace Engineering
Copyright: © 2019 Sven Marschalk
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Published Date

2019

Language

English

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Faculty

Aerospace Engineering

Abstract

As of April 2019, upset prevention and recovery training in flight simulation training devices is a mandatory practice for commercial and civil aircraft pilots. Aircraft stalls are a well-known upset type, therefore simulation of aircraft stall behavior is required. A key characteristic of stalls is the buffeting component, which in current stall models is still insufficiently modeled. In this research, a new methodology to more accurately model stall buffet behavior using swept
wing flight test data is presented. Buffet effects occur after exceeding the critical angle of attack, with an aircraft type-specific buffet onset duration to fully develop maximum buffet intensity. The buffet transient behavior is modeled with a frequency response fit and a multivariate second-order polynomial to capture aircraft eigenmode-shape frequencies and buffet intensity respectively. Aircraft recovery and thus receding buffet effects occur at an increasing angle
of attack, which is used as buffet offset. Generalization of the results was shown with the validation of data set of a straight wing aircraft, which indicates a step towards a more generic stall buffet model methodology.