How to Calculate Aileron Section lift Coefficient given Aileron Deflection?
Aileron Section lift Coefficient given Aileron Deflection calculator uses Lift Coefficient Roll Control = Lift Coefficient Slope Roll Control*(Rate of change of Angle of Attack/Rate of change of Deflection of Aileron)*Deflection of Aileron to calculate the Lift Coefficient Roll Control, Aileron Section lift Coefficient given Aileron Deflection is a measure of the lift generated by the aileron of an aircraft at a given deflection angle. It is defined as the ratio of the lift force generated by the aileron to the dynamic pressure and the reference area. Lift Coefficient Roll Control is denoted by Cl symbol.
How to calculate Aileron Section lift Coefficient given Aileron Deflection using this online calculator? To use this online calculator for Aileron Section lift Coefficient given Aileron Deflection, enter Lift Coefficient Slope Roll Control (Clα), Rate of change of Angle of Attack (dα), Rate of change of Deflection of Aileron (dδa) & Deflection of Aileron (δa) and hit the calculate button. Here is how the Aileron Section lift Coefficient given Aileron Deflection calculation can be explained with given input values -> 0.06 = 0.02*(3/4.5)*5.5.