Part III If the aircraft is rolled by the application of ful

Part III If the aircraft is rolled by the application of full right aileron at a speed of 150 mph at sea level, it will roll at an angular velocity of 68 o/sec. The wind tunnel test of a model of this aircraft indicate a full deflection of the ailerons to the right will introduce a yawing moment of Cn 005 How many degrees of rudder must be applied to keep the sideslip zero during this roll?

Solution

The eqn is Cn= Cnb*beta + Cndr *delta r

if this is zero, the angle of rudder is - Cnb/Cnd * beta

Cndr = -V *eta *Tau*Clav

Now Cnb = .005(W/b^2) ^.5 deg^-1

Use these eqns with the full data to get the estimate.