How to Calculate Dynamic pressure at wing for given yawing moment coefficient?
Dynamic pressure at wing for given yawing moment coefficient calculator uses Wing dynamic pressure = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Yawing moment coefficient) to calculate the Wing dynamic pressure, The Dynamic pressure at wing for given yawing moment coefficient is a function of the vertical tail's moment arm, lift curve slope, dynamic pressure (at vertical tail), area, sideslip angle, sidewash angle, wing's reference area, and wingspan. Wing dynamic pressure is denoted by Qw symbol.
How to calculate Dynamic pressure at wing for given yawing moment coefficient using this online calculator? To use this online calculator for Dynamic pressure at wing for given yawing moment coefficient, enter Vertical tail moment arm (πv), Vertical tail area (Sv), Vertical tail dynamic pressure (Qv), Vertical tail Lift curve slope (Cv), Sideslip angle (Ξ²), Sidewash angle (Ο), Reference Area (S), Wingspan (b) & Yawing moment coefficient (Cn) and hit the calculate button. Here is how the Dynamic pressure at wing for given yawing moment coefficient calculation can be explained with given input values -> 0.015201 = 1.2*5*11*0.7*(0.05+0.067)/(5.08*50*1.4).