Abstract
This paper describes the numerical analysis of light aircraft stability derivatives in a wide range of angles of attack, important for recovery from spin. Stability derivatives versus angle of attack and sideslip were calculated using a CFD software, based on Euler equation combined with boundary layer equations. The analysis was performed up to the 40 deg of angle of attack and up to 25 deg of sideslip.
Highlights
IntroductionCertain types of new designed aircraft are incapable to recover from some types of spin, mainly due to the empennage design, moment of inertia and aerodynamic features
Spin is known to be a very complex and still dangerous phenomenon in aviation
The computation schedule assumes that the basic aerodynamic characteristics for low angles of attack were obtained first
Summary
Certain types of new designed aircraft are incapable to recover from some types of spin, mainly due to the empennage design, moment of inertia and aerodynamic features Such a situation is unacceptable, especially for light general-aviation airplanes which by nature are flown by not very experienced pilots. A huge number of papers and reports devoted to spin technology have been published (Goraj, Baron 2002; Baron, Goraj 2001; Bowman 1971, Goraj et al 2002; Goraj 2001), but there are still a number of challenges and questions which cannot be solved and answered for an individual design project and aircraft prototype It is mainly because the spinning motion is very complicated and involves simultaneous rolling, yawing and pitching while the airplane is at high angles of attack and sideslip. This method allows making a preliminary assessment of the capabilities of aircraft recovery from spin
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