Measurements of pressures on the tail and aft fuselage of an airplane model during rotary motions at spin attitudes

The NASA-Langley Spin Tunnel was used to determine the empennage and aft fuselage surfaces of an aircraft model while it was rotated at spinning-event attitudes, in order to ascertain stern flow conditions and the effects of horizontal tail, as well as the wings, on the vertical tail. A substantial horizontal tail influence is noted on both sides of the vertical tail; the removal of the horizontal tail was found to change the propelling or damping moment characteristics of the vertical tail. The wing was also found to have a large influence on the magnitude of the pressures measured on both the empennage and the aft-fuselage areas.