A basic delta-wing aircraft was modified to an Ogee plan form and tested in flight following full-scale wind-tunnel tests. The modified wing had a sharp leading edge compared to the original large-radius, slatted leading edge. The modification produced strong leading-edge vortices which were easily observed and photographed as condensation trails. The stability of the vortices was examined in flight to 25 degrees angle of attack and 8 degrees sideslip and no detachment of the vortices or other discontinuous characteristics were indicated. A significant improvement in lateral-directional stability over that of the basic airplane was obtained at high angles of attack, which allowed a reduction in the minimum instrument approach speed. The improved lateral-directional characteristics made it possible to extend to lower speeds the study of other piloting factors which might determine the minimum approach speed. The effects of a range of static margins from -0.02 to +0.02 were examined. Also, the effect of a change in the slope of the power-required curve, which was obtained by making landing approaches over a range of airspeeds, was investigated. Poor static longitudinal stability and reduced flight-path-angle control became the limiting factors. (Author)
Flight Experience with the Ogee Wing at Low Speed
1966
26 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Varying sweep wings , Flight testing , Leading edge , Vortices , Roll , Lift , Drag , Pitch(Motion) , Handling , Ground effect , Velocity , Aircraft landings , Approach , Flight paths , Delta wings
Flight experience with the OGEE wing at low speed
AIAA | 1965
|Flight experience with the Ogee wing at low speed
NTRS | 1966
|Flight Experience with the Ogee Wing at Low Speed
NTIS | 1966
|Flight experience with the OGEE wing at low speed.
NTRS | 1965
|