Close-coupled oscillating canard effects on post-stall lift enhancement
McBane, Douglas G.
Howard, Richard M.
Platzer, Maximillian F.
MetadataShow full item record
The effects of an oscillating close-coupled canard on the canard/wing vortex interaction for increased lift enhancement were studied. Two test conditions were studied: the first with a model angle of attack of 22 deg. and the second of 34 deg. The canard was positioned at three mean deflection angles equal to 4, 7 and 10 deg. for the model angle of attack of 22 deg. and -4, -7 and -10 deg. for the model angle of attack of 34 deg. At each of the canard mean deflection angles, the canard was oscillated with amplitudes of +/- 5 deg. and +/- 10 deg. with reduced frequencies ranging from 0.046 to 0.232. Because of the small effects noted which were of the order of accuracy of the balance, only general trends are discussed. The trends indicate that for this particular model configuration and geometry, lift was decreased slightly with increasing canard frequency and amplitude. No lift-enhancement benefits were revealed during the study.
Approved for public release; distribution is unlimited.
Showing items related by title, author, creator and subject.
Flow visualization studies of a sideslipping, canard-configured X-31A-like fighter aircraft model. Kim, Chang Ho. (Monterey, California. Naval Postgraduate School, 1991-12);A water tunnel flow visualization investigation was performed to study the vortex development and bursting phenomena on a 2.3 % scale model of a X-31A-Like fighter aircraft. The main focus of this study was two-fold : ...
Schmidt, Dean Christopher (Monterey, California. Naval Postgraduate School, 1992-09);A wind-tunnel study to investigate the effects of dynamic stall of a closecoupled canard on the canard/wing vortex interaction for increased lift enhancement was conducted. Two angles of attack of the model were studied: one ...
Kersh, John M., Jr. (Monterey, California: Naval Postgraduate School, 1990-12);A wind-tunnel study to find the lift and drag characteristics of a low-aspect-ratio wingbody configuration from an angle of attack (AOA) of -8 to 50 degrees was conducted. A further study to find the comparative lift ...