Add to ORKGThe experimental longitudinal and lateral-directional stability characteristics of a Langley conceptual space shuttle orbiter design have been obtained for a series of inboard planform fillets in a unitary plan wind tunnel. Fillet sweep angles up to 78 deg were investigated while holding the spanwise intersection of the fillet and wing constant. The data were obtained at Mach numbers of 2.36 to 4.63 and at Reynolds numbers (depending on Mach number) of 1.5 million to 2.5 million per foot. The angle of attack was varied from about minus 2 deg to 44 deg at 0 deg and 3 deg of sideslip
A wind tunnel test is reported on an early version of the space shuttle orbiter (designated 089B-139...
Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of at...
Wind tunnel tests to determine effects of wing dihedral angle on aerodynamic characteristics of high...
The experimental aerodynamic characteristics of three basic wing planforms on a conceptual orbiter f...
An experimental and analytical aerodynamic program to develop predesign guides for irregular planfor...
The experimental longitudinal-and lateral-directional stability characteristics of a Langley concept...
An experimental and analytical aerodynamic program to develop predesign guides for irregular planfor...
A wind tunnel study to determine the supersonic aerodynamic characteristics of a 0.01925-scale model...
The model tested was a Langley-built 0.015-scale SSV Orbiter model with remote independently operate...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
An investigation was made in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.9 and 2.86 to...
Wind-tunnel tests were conducted at Mach 1.5 to 2.5 to determine the effect of modifications designe...
An investigation was conducted in the Langley low-turbulence pressure tunnel of a model of a space s...
An investigation was conducted to determine the supersonic longitudinal aerodynamic characteristics ...
A general research fighter model was tested in the Langley 7 by 10 foot high speed tunnel at a Mach ...
A wind tunnel test is reported on an early version of the space shuttle orbiter (designated 089B-139...
Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of at...
Wind tunnel tests to determine effects of wing dihedral angle on aerodynamic characteristics of high...
The experimental aerodynamic characteristics of three basic wing planforms on a conceptual orbiter f...
An experimental and analytical aerodynamic program to develop predesign guides for irregular planfor...
The experimental longitudinal-and lateral-directional stability characteristics of a Langley concept...
An experimental and analytical aerodynamic program to develop predesign guides for irregular planfor...
A wind tunnel study to determine the supersonic aerodynamic characteristics of a 0.01925-scale model...
The model tested was a Langley-built 0.015-scale SSV Orbiter model with remote independently operate...
Transonic pressure tunnel and transonic tunnel tests were performed to determine the aerodynamic cha...
An investigation was made in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.9 and 2.86 to...
Wind-tunnel tests were conducted at Mach 1.5 to 2.5 to determine the effect of modifications designe...
An investigation was conducted in the Langley low-turbulence pressure tunnel of a model of a space s...
An investigation was conducted to determine the supersonic longitudinal aerodynamic characteristics ...
A general research fighter model was tested in the Langley 7 by 10 foot high speed tunnel at a Mach ...
A wind tunnel test is reported on an early version of the space shuttle orbiter (designated 089B-139...
Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of at...
Wind tunnel tests to determine effects of wing dihedral angle on aerodynamic characteristics of high...