Add to ORKGA proposed wing body reusable launch vehicle was tested in the Marshall Space Flight Center (MSFC) 14 x 14 inch trisonic wind tunnel during the winter of 1994. this test resulted in the vehicle's subsonic and transonic (Mach 03 to 1.96) longitudinal and lateral aerodynamic characteristics. The effects of control surface deflections on the basic vehicle aerodynamics including a body flap, elevons, ailerons, and tip fins are presented
An investigation of the low-subsonic-speed static longitudinal stability and control characteristics...
A modified triangular wing of aspect ratio 2.53 having an airfoil section 3.7 percent thick at the r...
Experimental aerodynamic characteristics were obtained for a generic, winged, circular-body, single-...
The circular body configuration is a generic single- or multi-stage reusable Earth-to-orbit transpor...
The Advanced Manned Launch System is a proposed near-term technology, two-stage, fully reusable laun...
The Langley 8 foot transonic pressure tunnel and the Langley Unitary Plan wind tunnel used to determ...
The investigation was conducted in the Calspan 8-Ft Transonic wind tunnel at Mach numbers from 0.6 t...
The aerodynamic characteristics of some lifting reentry concepts are examined with a view to the app...
This paper examines flight-measured subsonic lift and drag characteristics of seven lifting-body and...
Wind tunnel tests were made with a scale model of the HL-20 in the Langley Unitary Plan Wind Tunnel....
An investigation was conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers from 1.6 to 4...
Subsonic stability, control, and performance of shuttle concept with blended wing-bod
Transonic wind tunnel study of aerodynamic characteristics of blunt reentry vehicles at varying angl...
Wind tunnel study of aerodynamic characteristics of three scale model multistage launch vehicles at ...
Transonic aerodynamic characteristics of two-stage fin-stabilized rocket launch vehicle in combinati...
An investigation of the low-subsonic-speed static longitudinal stability and control characteristics...
A modified triangular wing of aspect ratio 2.53 having an airfoil section 3.7 percent thick at the r...
Experimental aerodynamic characteristics were obtained for a generic, winged, circular-body, single-...
The circular body configuration is a generic single- or multi-stage reusable Earth-to-orbit transpor...
The Advanced Manned Launch System is a proposed near-term technology, two-stage, fully reusable laun...
The Langley 8 foot transonic pressure tunnel and the Langley Unitary Plan wind tunnel used to determ...
The investigation was conducted in the Calspan 8-Ft Transonic wind tunnel at Mach numbers from 0.6 t...
The aerodynamic characteristics of some lifting reentry concepts are examined with a view to the app...
This paper examines flight-measured subsonic lift and drag characteristics of seven lifting-body and...
Wind tunnel tests were made with a scale model of the HL-20 in the Langley Unitary Plan Wind Tunnel....
An investigation was conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers from 1.6 to 4...
Subsonic stability, control, and performance of shuttle concept with blended wing-bod
Transonic wind tunnel study of aerodynamic characteristics of blunt reentry vehicles at varying angl...
Wind tunnel study of aerodynamic characteristics of three scale model multistage launch vehicles at ...
Transonic aerodynamic characteristics of two-stage fin-stabilized rocket launch vehicle in combinati...
An investigation of the low-subsonic-speed static longitudinal stability and control characteristics...
A modified triangular wing of aspect ratio 2.53 having an airfoil section 3.7 percent thick at the r...
Experimental aerodynamic characteristics were obtained for a generic, winged, circular-body, single-...