How to Calculate Lift Coefficient with respect to Roll Rate?
Lift Coefficient with respect to Roll Rate calculator uses Lift Coefficient Respect to Roll Rate = -((2*Roll Rate)/(Wing Reference Area*Wingspan*Reference Velocity Across X Axis))*int(Lift Curve Slope*Chord*x^2,x,0,Wingspan/2) to calculate the Lift Coefficient Respect to Roll Rate, Lift Coefficient with respect to Roll Rate refers to a parameter in aerodynamics that describes the change in lift coefficient with respect to the rate of roll of an aircraft. It quantifies how the lift generated by the wings of an aircraft changes as the aircraft rolls or banks to one side. Lift Coefficient Respect to Roll Rate is denoted by Cl symbol.
How to calculate Lift Coefficient with respect to Roll Rate using this online calculator? To use this online calculator for Lift Coefficient with respect to Roll Rate, enter Roll Rate (p), Wing Reference Area (S_{r}), Wingspan (b), Reference Velocity Across X Axis (u_{0}), Lift Curve Slope (Cl_{α}) & Chord (c) and hit the calculate button. Here is how the Lift Coefficient with respect to Roll Rate calculation can be explained with given input values -> 0.038043 = -((2*0.5)/(184*200*50))*int((-0.1)*2.1*x^2,x,0,200/2).