C.M. Denegri, J.A. Dubben

An F-16 limit cycle oscillation (LCO) test case is examined using a medium-fidelity inviscid transonic small-disturbance aerodynamic model. The LCO stability boundary is computed for a range of Mach number and altitude variations and is compared to in-flight-measured LCO behavior. For the computational model, the wing-tip launcher aerodynamics were found to have a significant influence on the aeroelastic instability speed. A simplified F-16 computational aerodynamic model consisting of the full-span wing and tip launchers was used for this study and was validated with data from a wind tunnel test and a computational fluid dynamics model. The computed frequency and deflection characteristics show good correlation to flight test results. The computational stability boundary is similar in shape to the flight-measured ±2g LCO contour line but the onset of LCO occurs at a slightly higher Mach number and velocity than seen in flight test. The matched-condition LCO amplitude variations with respect to Mach number were not fully explored in this work. Deficiencies in the aerodynamic model and the absence of underwing store aerodynamics may be the primary causes of the observed differences between the computational and flight test results.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-11; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

aeroelasticity, nonlinearity

Bibliothek

2005