The results of an experimental investigation of the downwash and wake characteristics behind a rectangular plan-form wing of aspect ratio 3.5 are presented. The airfoil section was a 5-percent-thick, symmetrical double wedge. The tests were made at a Mach number of 1.53 and a Reynolds number of 1.25 million. A comparison between experimental and theoretical values of the downwash angles is made
Extensive experimental measurements have been made of the downwash angles and the wake characteristi...
A method is developed consistent with the assumptions of small perturbation theory which provides a ...
Data obtained from wind tunnel investigations of two series of 11 triangular wings conducted at Mach...
Results of an experimental investigation to determine downwash and wake characteristics in region of...
An investigation of the nature of the flow field behind a rectangular wing of circular arc cross sec...
The new downwash measurements behind a tapered wing with parallel center section described in the pr...
Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been ...
Results of an experimental investigation to determine downwash and wake characteristics in region of...
A systematic study has been made, experimentally and theoretically, of the effects of a vortical wak...
Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings ...
As part of a transonic research program the sensitivity of downwash at the tail plane to fairly syst...
At the present date, very little information exists as to the downwash and sidewash in the wake of l...
It was found that at positie angles of attack the vortex sheet assumed a shape which was initially b...
This report contains the results of an investigation to determine from linearized theory, which has ...
The effects of Mach nu&er in the ranges between 0.50 and 0.95 and between 1.09 and 1.29 on the c...
Extensive experimental measurements have been made of the downwash angles and the wake characteristi...
A method is developed consistent with the assumptions of small perturbation theory which provides a ...
Data obtained from wind tunnel investigations of two series of 11 triangular wings conducted at Mach...
Results of an experimental investigation to determine downwash and wake characteristics in region of...
An investigation of the nature of the flow field behind a rectangular wing of circular arc cross sec...
The new downwash measurements behind a tapered wing with parallel center section described in the pr...
Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been ...
Results of an experimental investigation to determine downwash and wake characteristics in region of...
A systematic study has been made, experimentally and theoretically, of the effects of a vortical wak...
Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings ...
As part of a transonic research program the sensitivity of downwash at the tail plane to fairly syst...
At the present date, very little information exists as to the downwash and sidewash in the wake of l...
It was found that at positie angles of attack the vortex sheet assumed a shape which was initially b...
This report contains the results of an investigation to determine from linearized theory, which has ...
The effects of Mach nu&er in the ranges between 0.50 and 0.95 and between 1.09 and 1.29 on the c...
Extensive experimental measurements have been made of the downwash angles and the wake characteristi...
A method is developed consistent with the assumptions of small perturbation theory which provides a ...
Data obtained from wind tunnel investigations of two series of 11 triangular wings conducted at Mach...
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