How to Calculate Lift given Roll Rate?
Lift given Roll Rate calculator uses Lift Respect to Roll Rate = -2*int(Lift Curve Slope*((Roll Rate*x)/Reference Velocity Across X Axis)*Pitch Rate*Chord*x,x,0,Wingspan/2) to calculate the Lift Respect to Roll Rate, Lift given Roll Rate typically involves considering the change in lift coefficient with respect to the change in roll rate This relationship helps to understand how the lift generated by an aircraft's wings is affected by its rate of roll. Lift Respect to Roll Rate is denoted by L symbol.
How to calculate Lift given Roll Rate using this online calculator? To use this online calculator for Lift given Roll Rate, enter Lift Curve Slope (Cl_{α}), Roll Rate (p), Reference Velocity Across X Axis (u_{0}), Pitch Rate (Q), Chord (c) & Wingspan (b) and hit the calculate button. Here is how the Lift given Roll Rate calculation can be explained with given input values -> 770 = -2*int((-0.1)*((0.5*x)/50)*0.55*2.1*x,x,0,200/2).