Abstract:
The results show that for longitudinal stability at M = 0.3 and C L = 0.45, the centre of gravity of an actual aircraft could be located only forward of 45% c (66% Co). The centre of pressure of the wing with basic nose and no fin is at 53% c (71% Co) at the cruise attitude, M = 2.2 and C L = 0.075, so that the camber used is insufficient to trim the wing. Measured values of the drag increments due to control deflection show fair agreement with linear-theory estimates. The control effectiveness can be predicted with fair accuracy. The canopy nose is slightly de-stabilizing in yaw, and it has a drag penalty which is probably larger than could be tolerated (30% of basic wing wave drag). At supersonic speeds slenderbody theory is generally inadequate for predicting the lateral derivatives of the wing. The fin effectiveness (except on lv) can be estimated with good accuracy.
