Methodologies for the determination of aircraft stability of the standard dynamics model at extreme angles of attack

This study explores various approaches to establishing the Standard Dynamics Model (SDM) aircraft's stability, particularly under extreme angles of attack. The SDM stands as a reference point for other models, and is a type of standard generic aircraft, which facilitates dynamic stability comparisons through wind tunnel tests. Static tests were performed in a low-speed wind tunnel at a plane Reynolds number of 94,000 with angles of attack from 0° to 90° and coupled with various roll and yaw angles. Complementary Computational Fluid Dynamics (CFD) simulations were executed for both the scaled wind tunnel model and a full-scale free-flight aircraft at multiple Reynolds number ranges. These studies demonstrated the high impact

of asymmetric vortex shedding at extreme angles of attack, which resulted in high peak lateral forces and yawing moments in the 40° to 65° angle of attack range. Given the critical aircraft stability derivatives, an initial static and dynamic stability assessment was performed. The results show that many aerodynamic coefficients and derivatives of the SDM investigated in this study may be insensitive to changes in the Reynolds number within the range examined.

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