A precision, active, table-leveling system.
Automatic feedback table leveling system, noting tilt to simulate aerodynamic drag
Debra, D. B.↗
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Results for “aerodynamic drag”
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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Aerodynamic forces on a stationary and oscillating circular cylinder at high Reynolds numbers
Transonic wind tunnel tests of aerodynamic drag and lift forces on circular cylinder in two dimensional flow at high Reynolds number
Cincotta, J. J.↗
Experimental investigation of magnetoaerodynamic flow around blunt bodies
Aerodynamic drag effects of hypersonic magnetohydrodynamic plasma flow around blunt bodies
Cambel, A. B.↗
Satellite trajectory determination and their expected errors.
Satellite trajectory determination and expected errors for OGO 4 and Geos 1 orbits, noting geopotential, aerodynamic drag and integration contributions
Vonbun, F. O.↗
Compressible Turbulent Boundary Layers
Compressibility of turbulent boundary layers - skin friction, heat transfer, flow velocity, temperature distribution, pressure gradients, and aerodynamic drag prediction methods
Source record↗
Experimental study of the effect of roughness of a surface of a bar on the intensity and frequency of vortex sound
Surface roughness effects of bar on vortex sound and aerodynamic drag generation during move through air
Bazhenov, D. V.↗
NASA-tricot - A lightweight radar reflective, knitted fabric
Fabric knitted on conventional knitting machines uses commercially available yarns, has high aerodynamic drag capability, and is relatively inexpensive. The two yarn components used are 15-denier nylon monofilament and aluminized Mylar tape.
Matthews, F. R.↗
Inflight thrust measuring system for underwing nacelles installed on a modified F-106 aircraft
Thrust measurement system and aerodynamic drag effects of underwing J-85 engine nacelles on F-106 aircraft propulsion system performance
Blumenthal, P. Z.↗
Computer program for investigating effects of nonlinear suspension-system elastic properties on parachute inflation loads and motions
A computer program is presented by which the effects of nonlinear suspension-system elastic characteristics on parachute inflation loads and motions can be investigated. A mathematical elastic model of suspension-system geometry is coupled to the planar equations of motion of a general vehicle and canopy. Canopy geometry and aerodynamic drag characteristics and suspension-system elastic properties are tabular inputs. The equations of motion are numerically integrated by use of an equivalent fifth-order Runge-Kutta technique.
Poole, L. R.↗
Atmospheric Flight Mechanics Conference, 2nd, Palo Alto and Moffett Field, Calif., September 11-13, 1972, Informal Papers.
Limitations in the acquisition of nonlinear aerodynamic coefficients from free-oscillation data by means of the Chapman-Kirk technique, SAM-D control test vehicle trajectory plannning and flight test analysis, and determination of aerodynamic drag from radar data are among the topics covered in papers concerned with atmospheric flight mechanics. Other areas covered include fixed and rotary-wing aircraft, ordnance and reentry vehicles, and analysis and measurement techniques. Individual items are announced in this issue.
Source record↗
Integrated engine-generator for aircraft secondary power.
The integrated engine-generator concept consists of an electric generator located inside a turbojet or turbofan engine and both concentric with and driven by one of the main engine shafts. The electric power-conversion equipment and generator controls are conveniently located in the aircraft. When properly rated, the generator serves as an engine starter as well as a source of electric power. The available generating capacity permits use of electrically driven engine accessories. This reduces or eliminates the need for an external gearbox on the engine, thereby simplifying the engine and nacelle assembly and increasing aircraft design flexibility. The nacelle diameter can then be decreased, resulting in less aerodynamic drag and reduced takeoff gross weight.
Secunde, R. R.↗
An aerodynamic study of scramjet fuel injectors
The aerodynamic drag and fuel distribution patterns of injectors designed for a supersonic combustion ramjet were measured at Mach numbers of 2, 2.5, and 3. The most significant parameter effecting the drag was found to be the injector thickness ratio. A two-fold reduction in the thickness ratio caused a 65 percent decrease in drag. Changing the injector sweep angle a factor of 2 resulted in only a small change in drag. A reversal of injector sweep, from sweepback to sweepforward, did not change the measured drag. Helium gas was injected through the struts to simulate the penetration and spreading patterns of hydrogen. Sampling measurements were made at approximately 2 duct heights downstream of the combustor. The spacing required between fuel injectors was found to be about 10 jet diameters. The effect of gas injection on the measured drag was found to be minor.
Povinelli, L. A.↗
Interactive design of large end rings on stiffened conical shells using composites
Design study methods and results for a composite reinforced base ring for the conical aeroshell structure of the planetary lander vehicle for Project Viking, an unmanned mission to Mars, are presented. The aeroshell is a ring and stringer-stiffened conical shell structure having a half angle of 70 degrees with a large base ring mounted at the outer edge of the cone and a large pay-load ring in the interior with many smaller rings spaced along the inside shell surface. The purpose of the structure is to develop the aerodynamic drag required to decelerate the lander in the Mars atmosphere to facilitiate a soft landing. The design of a shell structure of this complexity requires the use of the latest technology available in a large general-purpose shell buckling program. The large general-purpose non-linear shell buckling program (BOSOR 2) which was used for this purpose is described.
Davis, R. C.↗
An aerodynamic study of scramjet fuel injectors
The aerodynamic drag and fuel distribution patterns of injectors designed for a supersonic combustion ramjet were measured at Mach numbers of 2, 2.5, and 3. The most significant parameter effecting the drag was found to be the injector thickness ratio. A twofold reduction in the thickness ratio caused a 65% decrease in drag. Changing the injector sweep angle by a factor of 2 resulted in only a small change in drag. A reversal of injector sweep, from sweepback to sweepforward, did not change the measured drag. Helium gas was injected through the struts to simulate the penetration and spreading patterns of hydrogen. Sampling measurements were made at approximately two duct heights downstream of the combustor. The spacing required between fuel injectors was found to be about 10 jet diameters. The effect of gas injection on the measured drag was found to be minor.
Povinelli, L. A.↗
Accelerations experienced during low-G flight of Black Brant VC (NAS 21.015) on 4 October 1974
This investigation was to determine whether a Black Brant VC (BBVC) sounding rocket equipped with the Goddard Space Flight Center (GSFC) rate control system (RCS) would produce g-levels which are satisfactory for space processing. Accelerations measured by the Marshall Space Flight Center (MSFC) low-g accelerometer system (LGAS) were compared with accelerations calculated from measured payload RCS gyro data during a low-g flight of BBVC NAS 21.015 at White Sands Missile Range, N.M., on October 4, 1974. Accelerations of up to 0.0002 g existed at the LGAS accelerometers from 70 through 420 sec (5.8 min), with the exception of a spike at 101 sec of 0.0004 g which occurred when the RCS was activated the second time. Accelerations of 0.0001 g existed from 140 through 400 sec (4.3 min). Accelerations of 0.0002 g along the roll axis up to 150 sec and of 0.0015 g in the lateral plane at about 135 sec are being investigated by GSFC. They may be associated with leaking thruster valves or a leak in one of the heat pipe experiments. The vehicle rate buildup each time after the RCS nulls out are also being investigated by GSFC. This rate caused most of the 0.0001 g acceleration experienced after 150 sec into the flight. Aerodynamic drag produced no significant accelerations after about 80 sec. The principal conclusion was that the BBVC with the GSFC RCS produces g-levels satisfactory for space processing.
Kissel, R.↗
Atmosphere Explorer orbit adjust propulsion system
The Atmosphere Explorer-C (AE-C) spacecraft was launched into a highly elliptical orbit by a two-stage Delta 1900 vehicle on December 15, 1973. Its mission is to observe and study phenomena in the earth's atmosphere at altitudes between 150 and 4000 kilometers with several excursions down to 130 kilometers. An Orbit Adjust Propulsion System (OAPS) is included on the spacecraft in order (1) to perform low perigee maneuvers at 130 to 150 kilometers; (2) to periodically restore apogee in order to offset the effect of aerodynamic drag at perigee; and (3) to provide the capability for occasional large attitude maneuvers. This paper describes the configuration of the OAPS and the design characteristics of its individual components. Special emphasis is placed on the valving arrangement, which provides a means of adjusting the center-of-mass of the spacecraft through control of the distribution and usage of the propellant within the system.
Woodruff, W. L.↗
The science of the Viking missions
The Viking missions involve the launching of two identical spacecraft in the summer of 1975. Each spacecraft consists of a Lander and an Orbiter combination. The initial deceleration of the Lander during its descent to the Martian surface will be caused by aerodynamic drag. At about 5 km above the surface, a parachute is deployed. At 2 km three retrorockets are fired. The investigations to be conducted are discussed, giving attention to studies of the Martian surface with the aid of TV cameras, water mapping with an IR spectrometer, a thermal mapping experiment, studies of the Martian atmosphere, investigations conducted with a surface sampler, the search for life, and studies of the Martian surface composition.
Soffen, G. A.↗
A study of design trade (OFFS) using a computer model
The interaction between the efficiency of the structural design and the cost of the structure used was studied. It is shown that future effort is best directed at producing a low cost structure of medium efficiency, but with the ability to withstand normal service wear. The trade-off between aerodynamic drag and structure weight in selecting a length to diameter ratio for the hull is evaluated along with the implications of power plan type and fuel cost on the economics of the airship. The choice of lifting gas is considered.
Coughlin, S.↗