Add to ORKGThe Langley 8-foot transonic pressure tunnel was used at Mach numbers from 0.80 to 1.00 to determine the effects of wing trailing-edge truncation on the aerodynamic characteristics of a 0.0625-scale model of a NASA TF-8A supercritical-wing research airplane. The effects of trailing-edge truncations of 1, 2, and 3 percent of the local streamwise chord on the longitudinal aerodynamic characteristics and the wing section characteristics are presented
Transonic wind tunnel tests for aerodynamic characteristics of wing-body configuration
An investigation was conducted in the Langley 8 foot transonic pressure tunnel to determine the effe...
An investigation was conducted in the Langley 8 foot transonic pressure tunnel and the Langley Unita...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
Transonic pressure tunnel tests at Mach numbers from 0.25 to 1.00 were performed to determine the ef...
A low-speed investigation has been made on a highly-swept wing model having a thickened leading edge...
A program for the wind tunnel development of underwing leading-edge vortex generators on an NASA sup...
In an attempt to find an aerodynamic means of counteracting the transonic trim change of a fighter a...
The longitudinal aerodynamic characteristics of a wing-body-horizontal-tail configuration designed f...
The Langley 8-foot transonic pressure tunnel to determine the wing chordwise pressure distribution f...
The influence of upper-surface nacelle exhaust flow on the aerodynamic characteristics of a superson...
An investigation has been conducted in the Langley 8 foot transonic pressure tunnel to determine the...
The static longitudinal stability characteristics of a 0.09 scale model of an airplane with a modifi...
Effect of rearward body strakes on transonic aerodynamic characteristics of unswept-wing fighter air...
A low-speed investigation was made on a highly-swept arrow-wing model to determine the effect of win...
Transonic wind tunnel tests for aerodynamic characteristics of wing-body configuration
An investigation was conducted in the Langley 8 foot transonic pressure tunnel to determine the effe...
An investigation was conducted in the Langley 8 foot transonic pressure tunnel and the Langley Unita...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
Transonic pressure tunnel tests at Mach numbers from 0.25 to 1.00 were performed to determine the ef...
A low-speed investigation has been made on a highly-swept wing model having a thickened leading edge...
A program for the wind tunnel development of underwing leading-edge vortex generators on an NASA sup...
In an attempt to find an aerodynamic means of counteracting the transonic trim change of a fighter a...
The longitudinal aerodynamic characteristics of a wing-body-horizontal-tail configuration designed f...
The Langley 8-foot transonic pressure tunnel to determine the wing chordwise pressure distribution f...
The influence of upper-surface nacelle exhaust flow on the aerodynamic characteristics of a superson...
An investigation has been conducted in the Langley 8 foot transonic pressure tunnel to determine the...
The static longitudinal stability characteristics of a 0.09 scale model of an airplane with a modifi...
Effect of rearward body strakes on transonic aerodynamic characteristics of unswept-wing fighter air...
A low-speed investigation was made on a highly-swept arrow-wing model to determine the effect of win...
Transonic wind tunnel tests for aerodynamic characteristics of wing-body configuration
An investigation was conducted in the Langley 8 foot transonic pressure tunnel to determine the effe...
An investigation was conducted in the Langley 8 foot transonic pressure tunnel and the Langley Unita...