A propulsive wing/canard model was tested at STOL operating conditions in the NASA Langley Research Center 4 x 7 meter wind tunnel. Longitudinal and lateral/directional aerodynamic characteristics were measured for various flap deflections, angles of attack and sideslip, and blowing coefficients. Testing was conducted for several model heights to determine ground proximity effects on the aerodynamic characteristics. Flow field surveys of local flow angles and velocities were performed behind both the canard and the wing. This is volume 1 of a 2 volume report. The model, instrumentation, and test procedures are described. An analysis of the data is included
The low speed longitudinal characteristics of the jet flap STOL model were determined. The 17 percen...
The ability of current methodologies to accurately predict the aerodynamic characteristics identifie...
A wind tunnel test was conducted in the Langley V/STOL tunnel to define the aerodynamic characterist...
A propulsive wind/canard model was tested at STOL operating conditions in the NASA Langley Research ...
A full span model of a wing/canard concept representing a fighter configuration has been tested at S...
Progress on experimental program using jet flapped wing model in wind tunnel facilities for testing ...
A STOL fighter model employing the vectored-engine-over wing concept was tested at low speeds in the...
Tests were made in the Ames 40- by 80-foot wind tunnel to determine the forward speed effects on win...
Wind-tunnel tests of a model of an advanced canard configuration designed for general aviation were ...
An investigation of the effects of spanwise blowing applied to the lower surface of a trailing-edge ...
Wind tunnel tests on a finite, knee-blowing-flapped wing and on a direct jet lift configuration were...
A low speed wind tunnel test was conducted in the Langley V/STOL tunnel to determine the static long...
Feasibility of V/STOL test section in wind tunnel by using one eighth scale model of tunne
A wind tunnel test where load distributions were obtained at transonic speeds on both the canard and...
Low-speed free flight tunnel testing of swept wing fighter aircraft for determining effect of small ...
The low speed longitudinal characteristics of the jet flap STOL model were determined. The 17 percen...
The ability of current methodologies to accurately predict the aerodynamic characteristics identifie...
A wind tunnel test was conducted in the Langley V/STOL tunnel to define the aerodynamic characterist...
A propulsive wind/canard model was tested at STOL operating conditions in the NASA Langley Research ...
A full span model of a wing/canard concept representing a fighter configuration has been tested at S...
Progress on experimental program using jet flapped wing model in wind tunnel facilities for testing ...
A STOL fighter model employing the vectored-engine-over wing concept was tested at low speeds in the...
Tests were made in the Ames 40- by 80-foot wind tunnel to determine the forward speed effects on win...
Wind-tunnel tests of a model of an advanced canard configuration designed for general aviation were ...
An investigation of the effects of spanwise blowing applied to the lower surface of a trailing-edge ...
Wind tunnel tests on a finite, knee-blowing-flapped wing and on a direct jet lift configuration were...
A low speed wind tunnel test was conducted in the Langley V/STOL tunnel to determine the static long...
Feasibility of V/STOL test section in wind tunnel by using one eighth scale model of tunne
A wind tunnel test where load distributions were obtained at transonic speeds on both the canard and...
Low-speed free flight tunnel testing of swept wing fighter aircraft for determining effect of small ...
The low speed longitudinal characteristics of the jet flap STOL model were determined. The 17 percen...
The ability of current methodologies to accurately predict the aerodynamic characteristics identifie...
A wind tunnel test was conducted in the Langley V/STOL tunnel to define the aerodynamic characterist...
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