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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.
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Airloads investigation of an 0.30-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 5
Pressure data are presented in tabular form on the lower wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 6
Pressure data are presented in tabular form on the upper wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030 scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 7
Pressure data are presented in tabular form on the left and right vertical tail surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the arc 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 8
Pressure data are presented in tabular form on the SRM booster of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 9
Pressure data are presented in tabular form on the external tank and the SRM nozzle of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the Space Shuttle Vehicle 140 A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for MACH range 0.6 to 1.4 (IA14A), volume 10
Pressure data are presented in tabular form on the external tank base and SRM booster base of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 11
Pressure data are presented in tabular form on the external tank attach points and the external tank base rake of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Results of tests on a Rockwell International space shuttle orbiter (-139 configuration) 0.0175-scale model (no. 29-0) in AEDC tunnel B to determine boundary layer characteristics
Results of wind tunnel tests were conducted to determine boundary layer characteristics on the lower surface of a space shuttle orbiter. Total pressure and temperature profile data at various model stations were obtained using a movable, four-degree-of-freedom probe mechanism and static pressure taps on the model surface. During a typical run, the probe was located over a preselected model location, then driven down through the bondary layer until contact was made with the model surface.
Heat transfer phase change paint tests of 0.0175-scale models (nos. 21-0 and 46-0) of the Rockwell International space shuttle orbiter in the AEDC tunnel B hypersonic wind tunnel (test OH25A)
Tests were conducted in a hypersonic wind tunnel using various truncated space shuttle orbiter configurations in an attempt to establish the optimum model size for other tests examining body shock-wing leading edge interference effects. The tests were conducted at Mach number 8 using the phase change paint technique. A test description, tabulated data, and tracings of isotherms made from photographs taken during the test are presented.
Aerodynamic results of a separation effects test (IA87) on a 0.01-scale model (52-OTS) of the integrated SSV in the AEDC/VKF 40-by-40 inch supersonic wind tunnel A, volume 2
Data tables, model figures, and tabulated source data are given for aerodynamic investigations of separation effects in the integrated space shuttle vehicle. For Volume 1, see N75-28101.
Aeroacoustic performance of scale model sonic inlets
Various means can be used to vary engine inlet throat areas in order to reduce noise generated at takeoff and approach. Low-speed wind-tunnel tests were performed to evaluate the aeroacoustic performance of two takeoff geometries (cylindrical centerbody and bulb-shaped centerbody) and four approach geometries (bulb-shaped centerbody, annular ring, radial vanes, and step diffuser). The effects of inlet internal lip shape and diffuser length on sonic inlet performance were also investigated. It was found that the single-passage geometries, in particular a cylindrical centerbody takeoff geometry and a bulb-shaped centerbody approach geometry, provide the highest level of aeroacoustic performance. Increasing the inlet lip contraction ratio extends the maximum incidence angle for attached lip flow, while increasing the inlet diffuser length increases total pressure recovery for a given amount of noise suppression.
Investigation of Ejection Releases of an MB-1 Rocket from a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59
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An investigation in MSFC 14-inch TWT to determine the static stability characteristics of 0.004-scale model (74-OTS) space shuttle vehicle 5 configuration (IA33), volume 1
Wind tunnel tests were conducted to: (1) determine the static stability characteristics of the Shuttle Vehicle 5 configuration; (2) determine the effect on the Vehicle 5 aerodynamic characteristics of External Tank (ET) and Solid Rocket Booster (SRB) nose shape, SRB nozzle shroud flare angle, orbiter to tank fairing, and sting location; (3) provide flow visualization using thin film oil paint; and (4) determine rudder, body flap, and inboard and outboard elevon hinge moments. The mated vehicle model was mounted in three different ways: (1) the orbiter mounted on the balance with the SRB's attached to the tank and the tank in turn attached to the orbiter; (2) the tank mounted on the balance (with the sting protruding through the tank base) with the SRB's and orbiter attached to the tank, and (3) with the tank mounted on the balance and the balance in turn supported by a forked sting entering the nozzle of each SRB, extending forward into the SRB's then crossing over to the tank to provide a balance socket. Data were obtained for Mach numbers from 0.6 through 4.96 at angles-of-attack and -sideslip from -10 to 10 degrees.