SEARCH · Search NASA
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Horizontal-tail height, wing height, and dihedral effects on longitudinal and lateral stability characteristics of 76 deg swept arrow wing aircraft model
An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces.
This lecture concerns the combining effects in airplane wings so as to save some of the dead weight.
Tabulation of wind tunnel pressure data and section aerodynamic characteristics for a reflex cambered wing
Wind tunnel stability tests of pinch of modified half ring wing body and swept wing body combinations at supersonic speeds
Simulated wing damage effects on aerodynamic characteristics of swept-wing airplane model
Wind tunnel investigation of tip vortex structure of semispan wing for several wing-tip modifications
Wind tunnel tests to determine effects of wing dihedral angle on aerodynamic characteristics of highly swept fixed-wing configuration
Second order slender wing theory for calculating supersonic flow over low aspect ratio wings with subsonic leading edges and leading edge separation
Trisonic wind tunnel static stability tests on straight wing and delta wing space shuttle models
Three dimensional inviscid supersonic flow fields with primary and embedded shock and expansion waves determined over and behind wings and wing-body configurations
Comparisons of hinge moments for simple delta wing and delta wing orbiter concept at Mach 6
Experimental aerodynamic investigations have been made on a .0035 scale model North American Rockwell/General Dynamics version of the space shuttle. Static stability and control data were obtained on the delta wing booster alone (B-20) and with the delta wing orbiter (134D) mounted in various positions on the booster. Six component aerodynamic force and moment data were recorded over an angle of attack range from -10 deg to 24 deg at 0 deg and 6 deg sideslip angles and from -10 deg to +10 deg sideslip at 0 deg angle of attack. Mach number ranged from 0.6 to 4.96.
An investigation has been conducted in the Langley Unitary Plan wind tunnel to determine the static aerodynamic characteristics of a two-staged space-shuttle system consisting of a delta-wing orbiter mated atop a winged booster. The tests were performed at Mach numbers from 2.30 to 4.60 at a Reynolds number of one million per foot.
Experimental aerodynamic investigations have been made on a .0035 scale model North American Rockwell/General Dynamics version of the space shuttle in the NASA/MSFC 14 x 14 Inch Trisonic Wind Tunnel. Static stability and control data were obtained on the delta wing booster alone (B-20) and with the delta wing orbiter (134D) mounted in various positions on the booster. Six component aerodynamic force and moment data were recorded over an angle of attack range from -10 to 24 deg at 0 and 6 deg sideslip angles and from -10 to +10 deg sideslip at 0 deg angle of attack. Mach number ranged from 0.6 to 4.96.
Wind tunnel tests to determine the pressure distribution on a space shuttle launch configuration consisting of a delta wing orbiter and a swept wing booster with canard and tip fins were conducted. Pressure data were obtained for the combined orbiter and booster and for the booster alone at Mach numbers from 0.6 to 1.3, angles of attack from minus 8 degrees to plus 10 degrees, and sideslip angles from minus 6 degrees to plus 6 degrees. Pressure data were also obtained for the booster alone without canard at Mach numbers of 0.9 and 1.1. The pressure taps were distributed primarily over the booster upper surface and the orbiter lower surface.
The low-speed flying qualities of an experimental STOL configuration were evaluated by using a fixed-base six-degree-of-freedom simulation. The configuration had either an externally blown flap (EBF) wing or an augmentor wing (AW). The AW configuration was investigated with two tails, one sized for the AW configuration and a larger one sized for the EBF configuration. The emphasis of the study was on the 70-knot approach task. The stability and control characteristics were compared with existing criteria. Several control systems were investigated for the normal four-engine condition and for the engine-out transient condition. Minimum control and stall speeds were determined for both the three- and four-engine operation.
The Langley 1/8-scale V/STOL model tunnel was used to qualitatively determine the flow fields associated with semi-span close coupled canard wing and strake wing models. Small helium filled bubbles were injected upstream of the models to make the flow visible. Photographs were taken over the angle-of-attack ranges of -10 deg to 40 deg.