Study on design characteristics of airfoil pressure distribution for low Mach number general aircraft

This paper studies several problems that may exist in the aerodynamic design of low Mach number general aircraft, and discusses characteristics pressure distribution some related airfoils while part is verified by a multi-point laminar airfoil case. Firstly, issues which such as relatively large zero-lift drag coefficient, high stall performance requirements, variation range Reynolds number, are discussed analyzed. Then, to address these issues, extracts useful features beneficial from study on turbulent flow designed for aircraft. Finally, considering typical conditions light multi-purpose single-turboprop-engine including cruise, climb conditions, optimization offered using GAW-1 baseline. The optimized foil has 9.6 improvement lift-to-drag ratio cruise condition, 16.3 condition but 0.115 decrease maximum lift coefficient condition. results show requirements contradictory degree case, designers should deal with this trade-off carefully based