Add to ORKGA V/STOL tunnel study was performed to determine the effects of spanwise blowing on longitudinal aerodynamic characteristics of a model using a vectored-over-wing powered lift concept. The effects of spanwise nozzle throat area, internal and external nozzle geometry, and vertical and axial location were investigated. These effects were studied at a Mach number of 0.186 over an angle-of-attack range from 14 deg to 40 deg. A high pressure air system was used to provide jet-exhaust simulation. Engine nozzle pressure ratio was varied from 1.0 (jet off) to approximately 3.75
Aircraft with supersonic, short takeoff, and vertical landing capability were proposed to replace so...
Results of NASA Langley has conducted wind-tunnel investigations of several fighter configurations c...
Many conceptual designs for advanced short-takeoff, vertical landing (ASTOVL) aircraft need exhaust ...
The Langley V/STOL tunnel was used to determine the effects of vectoring exhaust flow on the longitu...
A wind-tunnel investigation incorporating both static and wind-on testing was conducted in the Langl...
Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of at...
An investigation was conducted in the Langley 4 by 7 Meter Tunnel of the thrust induced effects on t...
The effects of spanwise blowing on two configurations representative of current fighter airplanes we...
The aerodynamic effects of spanwise blowing on the trailing edge flap of an advanced fighter aircraf...
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the induced lift...
The effects of nozzle geometry and wing size on the aerodynamic performance of several 5:1 aspect ra...
A comprehensive set of experimental and analytical investigations have been conducted to assess the ...
Water tunnel studies were performed to define the changes that occur in vortex flow fields above the...
The induced lift characteristics are studied for a vectored-thrust concept in which jet-exhaust nozz...
Spanwise blowing was used to test a generalized wind-tunnel model to investigate component concepts ...
Aircraft with supersonic, short takeoff, and vertical landing capability were proposed to replace so...
Results of NASA Langley has conducted wind-tunnel investigations of several fighter configurations c...
Many conceptual designs for advanced short-takeoff, vertical landing (ASTOVL) aircraft need exhaust ...
The Langley V/STOL tunnel was used to determine the effects of vectoring exhaust flow on the longitu...
A wind-tunnel investigation incorporating both static and wind-on testing was conducted in the Langl...
Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of at...
An investigation was conducted in the Langley 4 by 7 Meter Tunnel of the thrust induced effects on t...
The effects of spanwise blowing on two configurations representative of current fighter airplanes we...
The aerodynamic effects of spanwise blowing on the trailing edge flap of an advanced fighter aircraf...
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the induced lift...
The effects of nozzle geometry and wing size on the aerodynamic performance of several 5:1 aspect ra...
A comprehensive set of experimental and analytical investigations have been conducted to assess the ...
Water tunnel studies were performed to define the changes that occur in vortex flow fields above the...
The induced lift characteristics are studied for a vectored-thrust concept in which jet-exhaust nozz...
Spanwise blowing was used to test a generalized wind-tunnel model to investigate component concepts ...
Aircraft with supersonic, short takeoff, and vertical landing capability were proposed to replace so...
Results of NASA Langley has conducted wind-tunnel investigations of several fighter configurations c...
Many conceptual designs for advanced short-takeoff, vertical landing (ASTOVL) aircraft need exhaust ...