Title: Stability Analysis of Full Geometry Aircraft through CFD and Response Surface Method
Abstract: Aircraft stability derivatives have traditionally been analyzed by wind tunnel tests or low fidelity models. The experimental method should be the most accurate but it requires a long lead time. On the other hand, the low fidelity approach is the fastest method but it has an accuracy issue. To overcome these difficulties, a high fidelity numerical approach using computational fluid dynamics analysis combined with response surface method is proposed to estimate static stability characteristics of a low speed aircraft in this paper. A set of aerodynamic coefficients and static stability derivatives of the wing-body-tail model at low Mach number of 0.16 have been computed using Reynold’s Averaged Navier-Stokes CFD analyses and compared with the available wind tunnel data. A set of aerodynamic coefficients with respect to a minimal number of angles of attack and angles of sideslip have been calculated using the CFD code at first. Then the complete set of aerodynamic coefficients and static derivatives, which cover a whole angle-of-attack and angle-of-sideslip range, have been generated using the response surface method. The predicted results demonstrate the utility of the present approach by showing good agreement with the experiment. Finally, in order to predict stability derivatives of subsonic aircraft in the operating condition, proposed techniques are applied to Mach number 0.5.
Publication Year: 2010
Publication Date: 2010-01-04
Language: en
Type: article
Indexed In: ['crossref']
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Cited By Count: 4
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