Add to ORKGTwo 0.085-scale full span wind-tunnel models of a Mach 1.60 design supercruiser configuration were tested at Mach numbers from 0.60 to 2.70. One model incorporated a varying dihedral (swept-up) wing to obtain the desired lateral-directional characteristics; the other incorporated more conventional twin vertical tails. The data from the wind-tunnel tests are presented without analysis
A summary and analysis have been made of the results of various investigations to determine the aero...
Longitudinal aerodynamic characteristics at Mach numbers 0.50 to 1.19 of supersonic transport model ...
Wind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing t...
An investigation was made in the Langley Unitary Plan wind tunnel at Mach numbers of 2.30, 2.96, and...
The aerodynamic characteristics of an advanced twin-engine fighter aircraft designed for supersonic ...
An investigation was made in the Langley 8-foot transonic tunnel and the Langley Unitary Plan wind t...
A wind tunnel investigation has been conducted to determine the longitudinal and lateral aerodynamic...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
Wind tunnel test of the McDonnell Douglas Supersonic Cruise Aircraft, designed for a cruise Mach num...
The tabulated results of surface pressure tests conducted on the wing and fuselage of an airplane mo...
The influence of upper-surface nacelle exhaust flow on the aerodynamic characteristics of a superson...
The static longitudinal, lateral, and directional stability characteristics of a hypersonic research...
An investigation has been made in the Mach number range from 0.50 to 2.86 to determine the longitudi...
The results of the investigation showed that the configuration exhibits a sufficiently high drag div...
Aerodynamic wind tunnel study of tailless fixed- wing supersonic transport model at transonic spee
A summary and analysis have been made of the results of various investigations to determine the aero...
Longitudinal aerodynamic characteristics at Mach numbers 0.50 to 1.19 of supersonic transport model ...
Wind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing t...
An investigation was made in the Langley Unitary Plan wind tunnel at Mach numbers of 2.30, 2.96, and...
The aerodynamic characteristics of an advanced twin-engine fighter aircraft designed for supersonic ...
An investigation was made in the Langley 8-foot transonic tunnel and the Langley Unitary Plan wind t...
A wind tunnel investigation has been conducted to determine the longitudinal and lateral aerodynamic...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
Wind tunnel test of the McDonnell Douglas Supersonic Cruise Aircraft, designed for a cruise Mach num...
The tabulated results of surface pressure tests conducted on the wing and fuselage of an airplane mo...
The influence of upper-surface nacelle exhaust flow on the aerodynamic characteristics of a superson...
The static longitudinal, lateral, and directional stability characteristics of a hypersonic research...
An investigation has been made in the Mach number range from 0.50 to 2.86 to determine the longitudi...
The results of the investigation showed that the configuration exhibits a sufficiently high drag div...
Aerodynamic wind tunnel study of tailless fixed- wing supersonic transport model at transonic spee
A summary and analysis have been made of the results of various investigations to determine the aero...
Longitudinal aerodynamic characteristics at Mach numbers 0.50 to 1.19 of supersonic transport model ...
Wind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing t...