M. Manshadi; A. Sharafi; M.H. Soltani
Volume 9, Issue 2 , September 2012, , Pages 15-24
Abstract
An extensive experimental investigation is conducted to study the effect of canard position relative to the fuselage reference line on the aerodynamic forces of a fighter type configuration model. Aerodynamic forces at different flight conditions are measured in a subsonic wind tunnel. The wing and the ...
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An extensive experimental investigation is conducted to study the effect of canard position relative to the fuselage reference line on the aerodynamic forces of a fighter type configuration model. Aerodynamic forces at different flight conditions are measured in a subsonic wind tunnel. The wing and the canard have triquetrous shapes. Experiments are conducted at Reynolds number of 342209 and at 0 to 40 degree angles of attack. The results show that canard increases the lift and drag forces while it decreases the static stability of the model. The canard at itandrsquo;s up position increases the aerodynamic forces and decreases the static stability i.e., superior maneuver capability. Furthermore, when the forward position of the canard is considered, both lift and drag are increased; however, the overall aerodynamic efficiency and also more static stability are improved. The canard at up and forward position respect to the wing-body is an appropriate selection for the best performance at moderate to high angles of attack among the various wing-canard-body configurations.
hamid fazeli; M.R. Soltani; alireza davari
Volume 7, Issue 1 , March 2010, , Pages 51-57
Abstract
Unsteady dynamic behavior of TTCP model with different wrap around fin sets were investigated in a trisonic wind tunne. The aerodynamic coefficient force measurement in this wind tunnel shows good agreement in comparison with that of the NASA Langley Research Center in static case. The model was sinusoidally ...
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Unsteady dynamic behavior of TTCP model with different wrap around fin sets were investigated in a trisonic wind tunne. The aerodynamic coefficient force measurement in this wind tunnel shows good agreement in comparison with that of the NASA Langley Research Center in static case. The model was sinusoidally oscillated at three different frequencies of 1, 3 and 8 Hz at M=2.0 and the effects of these frequencies on the shock angle were investigated and compared with the corresponding static case. Experimental data indicates that the static shock angle does not fall between the upstroke and down stroke dynamic shock angle at different frequencies which is different from experimental findings for flat fin configurations. This unsteady behavior could be added to the other anomalies frequently seen in the aerodynamic characteristics of wrap around fin configurations. Also shock development mechanism over the nose and several fin sets was investigated and the shock-boundary layer interaction near the fin/body juncture which leads to shock likes ? was clearly observed in this investigation.