Add to ORKGAn investigation has been made at a Mach number of 2.01 to determine the effects of a flared rudder on the aerodynamic characteristics of an ogee-wing space-shuttle orbiter configuration. Also investigated were the effects of an upper-aft fuselage fairing for the orbital maneuvering system, elevon deflections, and rudder deflection on the aerodynamic characteristics of the configuration
An experimental aerodynamic wind tunnel investigation was conducted employing a 0.00325 scale model ...
Wind-tunnel tests were conducted at Mach 1.5 to 2.5 to determine the effect of modifications designe...
The model tested was a Langley-built 0.015-scale SSV Orbiter model with remote independently operate...
An investigation was conducted in the Langley 8-foot transonic pressure tunnel to determine the infl...
A wind tunnel study to determine the supersonic aerodynamic characteristics of a 0.01925-scale model...
An investigation was conducted to determine the supersonic longitudinal aerodynamic characteristics ...
An investigation has been made in a low-turbulence pressure tunnel to determine the low-subsonic aer...
An investigation was conducted in the Langley low-turbulence pressure tunnel of a model of a space s...
An investigation has been conducted in the Langley Unitary Plan wind tunnel to determine the static ...
Longitudinal, directional, and lateral stability and control characteristics of orbiter stage of spa...
An investigation has been made in a low-turbulence pressure tunnel to determine the subsonic aerodyn...
Aerodynamic studies have been directed to investigating the design requirements associated with the...
The Advanced Manned Launch System is a proposed near-term technology, two-stage, fully reusable laun...
The major aerodynamic design challenge at the beginning of the United States Space Transportation Sy...
A wind-tunnel investigation was conducted to determine the static longitudinal and lateral-direction...
An experimental aerodynamic wind tunnel investigation was conducted employing a 0.00325 scale model ...
Wind-tunnel tests were conducted at Mach 1.5 to 2.5 to determine the effect of modifications designe...
The model tested was a Langley-built 0.015-scale SSV Orbiter model with remote independently operate...
An investigation was conducted in the Langley 8-foot transonic pressure tunnel to determine the infl...
A wind tunnel study to determine the supersonic aerodynamic characteristics of a 0.01925-scale model...
An investigation was conducted to determine the supersonic longitudinal aerodynamic characteristics ...
An investigation has been made in a low-turbulence pressure tunnel to determine the low-subsonic aer...
An investigation was conducted in the Langley low-turbulence pressure tunnel of a model of a space s...
An investigation has been conducted in the Langley Unitary Plan wind tunnel to determine the static ...
Longitudinal, directional, and lateral stability and control characteristics of orbiter stage of spa...
An investigation has been made in a low-turbulence pressure tunnel to determine the subsonic aerodyn...
Aerodynamic studies have been directed to investigating the design requirements associated with the...
The Advanced Manned Launch System is a proposed near-term technology, two-stage, fully reusable laun...
The major aerodynamic design challenge at the beginning of the United States Space Transportation Sy...
A wind-tunnel investigation was conducted to determine the static longitudinal and lateral-direction...
An experimental aerodynamic wind tunnel investigation was conducted employing a 0.00325 scale model ...
Wind-tunnel tests were conducted at Mach 1.5 to 2.5 to determine the effect of modifications designe...
The model tested was a Langley-built 0.015-scale SSV Orbiter model with remote independently operate...