Within these expression we need to evaluate A0, A1, A2, and dz/dxĤ CENTER OF PRESSURE AND AERODYNAMIC CENTERĬenter of Pressure: It is that point on an airfoil (or body) about which the aerodynamic moment is zero Thin Airfoil Theory: Symmetric Airfoil: Cambered Airfoil: Aerodynamic Center: It is that point on an airfoil (or body) about which the aerodynamically generated moment is independent of angle of attack KirkĢ KEY EQUATIONS FOR cl, aL=0, cm,c/4, and xcp Summary of Incompressible Flow Over Airfoils Summary of Thin Airfoil Theory Example Airfoil Calculation Mechanical and Aerospace Engineering Department Florida Institute of Technology D.
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