Add to ORKGAn investigation was conducted in the NASA Langley 8-foot transonic pressure tunnel at Mach numbers from 0.60 to 0.975 with a variable-wing-sweep airplane model in order to evaluate a series of wings designed to demonstrate the maneuver potential of the supercritical airfoil concept. Both conventional and supercritical wing designs for several planform configurations were investigated with wing sweep angles from 16.0 deg to 72.5 deg, depending on Mach number and wing configuration. The supercritical wing configuration showed significant improvements over the conventional configurations in drag-divergence Mach number and in drag level at transonic maneuver conditions
The aerodynamic characteristics of an 11 percent thick symmetrical supercritical airfoil were determ...
Refinements in a 10 percent thick supercritical airfoil produced improvements in the overall drag ch...
A TF-8A airplane was equipped with a transport type supercritical wing and fuselage fairings to eval...
Two dimensional wind tunnel test results obtained for supercritical airfoils indicated that substant...
An investigation was conducted in the Langley 8 foot transonic pressure tunnel and the Langley Unita...
A wind tunnel investigation was conducted to study the application of supercritical technology to hi...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
Supercritical airfoils and their applications to wings for various types of aircraft are studied. Th...
The Transonic Aircraft Technology (TACT) research program provided data necessary to verify aerodyna...
A theoretical and experimental program in which a wing concept for supersonic maneuvering was develo...
Wind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing t...
A flight research program was conducted to investigate the improvements in maneuverability of an F-1...
A procedure was developed for the design of transonic wings by the iterative use of three dimensiona...
Wind tunnel tests were conducted to examine the use of wing leading-edge devices for improved subson...
A number of high aspect ratio supercritical wings in combination with a representative wide body typ...
The aerodynamic characteristics of an 11 percent thick symmetrical supercritical airfoil were determ...
Refinements in a 10 percent thick supercritical airfoil produced improvements in the overall drag ch...
A TF-8A airplane was equipped with a transport type supercritical wing and fuselage fairings to eval...
Two dimensional wind tunnel test results obtained for supercritical airfoils indicated that substant...
An investigation was conducted in the Langley 8 foot transonic pressure tunnel and the Langley Unita...
A wind tunnel investigation was conducted to study the application of supercritical technology to hi...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
Supercritical airfoils and their applications to wings for various types of aircraft are studied. Th...
The Transonic Aircraft Technology (TACT) research program provided data necessary to verify aerodyna...
A theoretical and experimental program in which a wing concept for supersonic maneuvering was develo...
Wind tunnel tests have been conducted on a research airplane model with an NASA supercritical wing t...
A flight research program was conducted to investigate the improvements in maneuverability of an F-1...
A procedure was developed for the design of transonic wings by the iterative use of three dimensiona...
Wind tunnel tests were conducted to examine the use of wing leading-edge devices for improved subson...
A number of high aspect ratio supercritical wings in combination with a representative wide body typ...
The aerodynamic characteristics of an 11 percent thick symmetrical supercritical airfoil were determ...
Refinements in a 10 percent thick supercritical airfoil produced improvements in the overall drag ch...
A TF-8A airplane was equipped with a transport type supercritical wing and fuselage fairings to eval...