EFFECTS OF CROSS-SECTION SHAPE ON THE LOW-SPEED AERODYNAMIC CHARACTERISTICS OF A LOW-WAVE-DRAG HYPERSONIC BODY
Effect of cross section shape on low speed aero- dynamic characteristics of low-wave drag hyper- sonic body
HYPERSONIC VEHICLE↗
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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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Drag measurements at low lift of a four- nacelle airplane configuration having a longitudinal distribution of cross-sectional area conductive to low transonic drag rise
Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise
NACELLE↗
Low-power, low level analog-to-digital converter for space vehicle applications
Low power, low level analog-to-digital converter for space vehicle applications
ANALOG-TO-DIGITAL CONVERTER↗
Effects of low level, low frequency electric fields on human reaction time
Low level, low frequency electric field effects on human reaction time
Hamer, J. R.↗
Multiloop distributed RC active networks for low parameter sensitivity with low amplifier gain.
Multiloop feedback in active distributed RC networks for low parameter sensitivity with low amplifier gain compared to single loop circuits
Kerwin, W. J.↗
Effect of low-level, low-frequency electric fields on EEG and behavior in Macaca nemestrina
Effect of low level, low frequency electric fields on EEG and behavior of Macaca nemestrina
Adey, W. R.↗
Silicon solar cell development for low temperature and low illumination intensity operation, volume 1 Analysis report, 30 Jun. 1969 - 30 Apr. 1970
Operational performance of solar cell at low temperatures and under low illumination intensity
Bartels, F. T. C.↗
Research and development of silicon solar cells for low solar intensity and low temperature applications
Research and development of silicon solar cells for low solar intensity and low temperature operation on Jupiter mission
Payne, P.↗
A low-loss N-way optical power divider for a Ku-band low sidelobe phased array
Low loss low sidelobe N-way microwave optical power divider for single plane electronically steerable Ku band phased array antenna
Profera, C. E., Jr.↗
Low- and high-altitude tests of parachutes designed for use in low-density atmospheres
Parachutes for low density atmospheres, describing low and high altitude test results
Eckstrom, C. V.↗
Research and development of silicon solar cells for low solar intensity and low temperature applications Quarterly progress report
Research and development of silicon solar cells for low solar intensity and low temperature applications
Payne, P.↗
Low temperature and low solar intensity characteristics of silicon solar cells
Si solar cells low temperature and solar intensity performance optimization by identifying and eliminating low output problems
Payne, P. A.↗
Solar cell low temperature, low solar intensity operation
Si solar cell low temperature low solar illumination intensity I-V performance deficiencies, considering corrective design modifications
Bartels, F. T. C.↗
Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration with a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers from 1.2 to 2.1
A full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose has been flight tested by the Langley Pilotless Aircraft Research Division. Static and dynamic longitudinal stability and control derivatives of this interdigitated canard-wing missile configuration were determined by using the pulsed-control technique at low angles of attack and for a Mach number range of 1.2 to 2.1. The lift-curve slope showed only small nonlinearities with changes in control deflection or angle of attack but indicated a difference in lift-curve slope of approximately 7 percent for the two control deflections of delta = 3.0 deg and delta = -0.3 deg. The large tail length of the missile tested was effective in producing damping in pitch throughout the Mach number range tested. The aerodynamic-center location was nearly constant with Mach number for the two control deflections but was shown to be less stable with the larger control deflection. The increment of lift produced by the controls was small and positive throughout the Mach number range tested, whereas the pitching moment produced by the controls exhibited a normal trend of reduced effectiveness with increasing Mach number. The effectiveness of the controls in producing angle of attack, lift, and pitching moment was good at all Mach numbers tested.
Brown, C. A., Jr.↗
Performance of low-pressure-ratio low-tip-speed fan stage with blade tip solidity of 0.65
The overall and blade-element performance of a low pressure ratio, low tip speed fan stage is presented over the stable operating range at rotative speeds from 90 to 120 percent of design speed. Stage peak efficiency of 0.927 was obtained at a weight flow of 32.4 kg/sec (190.31 kg/sec/sq m of annulus area) and a pressure ratio of 1.134. The stall margin at design speed and peak efficiency was 15.3 percent.
Kovich, G.↗
Effects of wing leading-edge deflection on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration
Wing leading-edge deflection effects on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration were determined. Static force tests were conducted in a V/STOL tunnel at a Reynolds number of about 2.5 x 1 million for an angle-of-attack range from -10 deg to 17 deg and an angle-of-sideslip range from -5 deg to 5 deg. Limited flow visualization studies were also conducted in order to provide a qualitative assessment of leading-edge upwash characteristics.
Coe, P. L., Jr.↗
Influence of optimized leading-edge deflection and geometric anhedral on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration
An investigation conducted in the Langley 7 by 10 foot tunnel to determine the influence of an optimized leading-edge deflection on the low speed aerodynamic performance of a configuration with a low aspect ratio, highly swept wing. The sensitivity of the lateral stability derivative to geometric anhedral was also studied. The optimized leading edge deflection was developed by aligning the leading edge with the incoming flow along the entire span. Owing to spanwise variation of unwash, the resulting optimized leading edge was a smooth, continuously warped surface for which the deflection varied from 16 deg at the side of body to 50 deg at the wing tip. For the particular configuration studied, levels of leading-edge suction on the order of 90 percent were achieved. The results of tests conducted to determine the sensitivity of the lateral stability derivative to geometric anhedral indicate values which are in reasonable agreement with estimates provided by simple vortex-lattice theories.
Coe, P. L., Jr.↗
Low sidelobe level low-cost earth station antennas for the 12 GHz broadcasting satellite service
An experimental investigation of the performance of 1.22 m and 1.83 m diameter paraboloid antennas with an f/D ratio of 0.38 and using a feed developed by Kumar is reported. It is found that sidelobes below 30 dB can be obtained only if the paraboloids are relatively free of surface errors. A theoretical analysis of clam shell distortion shows that this is a limiting factor in achieving low sidelobe levels with many commercially available low cost paraboloids. The use of absorbing pads and small reflecting plates for sidelobe reduction is also considered.
Collin, R. E.↗