Add to ORKGA 2.29 m (7.5 ft.) span high-lift research model equipped with full-span leading-edge slat and part-span double-slotted trailing-edge flap was tested in the Langley 4- by 7-Meter Tunnel to determine the low speed performance characteristics of a representative high aspect ratio suprcritical wing. These tests were performed in support of the Energy Efficient Transport (EET) program which is one element of the Aircraft Energy Efficiency (ACEE) project. Static longitudinal forces and moments and chordwise pressure distributions at three spanwise stations were measured for cruise, climb, two take-off flap, and two landing flap wing configurations. The tabulated and plotted pressure distribution data is presented without analysis or discussion
An unswept, semispan wing model equipped with full-span leading- and trailing-edge flaps was tested ...
Detailed pressure distribution measurements were made for 11 twist configurations of a unique, multi...
A low-speed investigation was conducted in the Langley V/STOL tunnel over an angle-of-attack range o...
A high-lift transport aircraft model equipped with full-span leading-edge slat and part-span double-...
A wind tunnel investigation was conducted on a generic, high-wing transport model in the Langley 14-...
An investigation was made in the 5.18 m (17 ft) test section of the Langley 300 MPH 7 by 10 foot tun...
The Ames 12-Foot Pressure Tunnel was used to determine the effects of Reynolds number on the static ...
This report describes the results of an experimental study conducted in the Langley Low-Turbulence P...
An investigation was made in the 5.18 m (17 ft) test section of the Langley 300 MPH 7 by 10 foot tun...
Wind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing t...
Wind-tunnel measurements were made of the wing-surface static-pressure distributions on a 0.237 scal...
A high Reynolds number test of a 5 percent thick low aspect ratio semispan wing was conducted in the...
A low-speed investigation was conducted over an angle-of-attack range from about -4 deg to 20 deg in...
Pressure distributions in the form of differential pressure coefficients are presented for several w...
An investigation was conducted in the Langley 4 by 7 Meter Tunnel to determine the static longitudin...
An unswept, semispan wing model equipped with full-span leading- and trailing-edge flaps was tested ...
Detailed pressure distribution measurements were made for 11 twist configurations of a unique, multi...
A low-speed investigation was conducted in the Langley V/STOL tunnel over an angle-of-attack range o...
A high-lift transport aircraft model equipped with full-span leading-edge slat and part-span double-...
A wind tunnel investigation was conducted on a generic, high-wing transport model in the Langley 14-...
An investigation was made in the 5.18 m (17 ft) test section of the Langley 300 MPH 7 by 10 foot tun...
The Ames 12-Foot Pressure Tunnel was used to determine the effects of Reynolds number on the static ...
This report describes the results of an experimental study conducted in the Langley Low-Turbulence P...
An investigation was made in the 5.18 m (17 ft) test section of the Langley 300 MPH 7 by 10 foot tun...
Wind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing t...
Wind-tunnel measurements were made of the wing-surface static-pressure distributions on a 0.237 scal...
A high Reynolds number test of a 5 percent thick low aspect ratio semispan wing was conducted in the...
A low-speed investigation was conducted over an angle-of-attack range from about -4 deg to 20 deg in...
Pressure distributions in the form of differential pressure coefficients are presented for several w...
An investigation was conducted in the Langley 4 by 7 Meter Tunnel to determine the static longitudin...
An unswept, semispan wing model equipped with full-span leading- and trailing-edge flaps was tested ...
Detailed pressure distribution measurements were made for 11 twist configurations of a unique, multi...
A low-speed investigation was conducted in the Langley V/STOL tunnel over an angle-of-attack range o...