How to Calculate Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient?
Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient calculator uses Vertical Tail Dynamic Pressure = Yawing Moment Coefficient*Reference Area*Wingspan*Wing Dynamic Pressure/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)) to calculate the Vertical Tail Dynamic Pressure, Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient is a measure of the pressure exerted on the vertical tail of an aircraft, influenced by the yawing moment coefficient, reference area, wingspan, wing dynamic pressure and other factors, which affects the stability and control of the aircraft during flight. Vertical Tail Dynamic Pressure is denoted by Qv symbol.
How to calculate Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient using this online calculator? To use this online calculator for Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient, enter Yawing Moment Coefficient (Cn), Reference Area (S), Wingspan (b), Wing Dynamic Pressure (Qw), Vertical Tail Moment Arm (𝒍v), Vertical Tail Area (Sv), Vertical Tail Lift Curve Slope (Cv), Sideslip Angle (β) & Sidewash Angle (σ) and hit the calculate button. Here is how the Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient calculation can be explained with given input values -> 10.98496 = 1.4*5.08*1.15*0.66/(1.2*5*0.7*(0.05+0.067)).