Tevatron Run II combination of the effective leptonic electroweak mixing angle
Not Available
72 PHYSICS OF ELEMENTARY PARTICLES AND FIELDS↗
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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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Properties of g → b b ¯ at small opening angles in p p collisions with the ATLAS detector at s = 13 TeV
Not Available
72 PHYSICS OF ELEMENTARY PARTICLES AND FIELDS↗
Angle-Multiplexed Metasurfaces: Encoding Independent Wavefronts in a Single Metasurface under Different Illumination Angles
Not Available
74 ATOMIC AND MOLECULAR PHYSICS↗
Performance of a Grid-Forming Inverter Under Balanced and Unbalanced Voltage Phase Angle Jump Conditions .
Abstract not provided.
Darbali-Zamora, Rachid↗
Angle-resolved coherent wave mixing using a 4 fs ultra-broad bandwidth laser
Not Available
Mercer, I. P.↗
PRESSURE DISTRIBUTIONS ON TWO-DIMENSIONAL SHARP-LEADING-EDGE FLAT PLATES WITH SWEEP ANGLES OF 0 DEG, 30 DEG, AND 45 DEG AT A MACH NUMBER OF 6 AND ANGLES OF ATTACK FROM 0 DEG TO 90 DEG
Pressure distributions on two dimensional sharp leading edge flat plates
FLAT PLATE↗
CENTER-LINE PRESSURE DISTRIBUTIONS ON TWO-DIMENSIONAL BODIES WITH LEADING-EDGE ANGLES GREATER THAN THAT FOR SHOCK DETACHMENT AT MACH NUMBER 6 AND ANGLES OF ATTACK UP TO 25 DEG
Center-line pressure distribution on two- dimensional bodies
PRESSURE DISTRIBUTION↗
X/Y angle and polarization angle tracking of the ATS-B spacecraft using the Rosman 85-foot antenna no. 2 and Mojave 40-foot antenna
Orbital position and attitude tracking of ATS SPACECRAFT using parabolic ground antennas
SPACECRAFT TRACKING↗
Heat transfer and pressure distributions on spherically blunted 25 deg half-angle cone at Mach 8 and angles of attack up to 90 deg
Hypersonic heat transfer and pressure distribution on spherically blunted cone
Bushnell, D. M.↗
The use of a finite difference technique to predict cascade, stator, and rotor deviation angles and optimum angles of attack.
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Dodge, P. R.↗
Inviscid flow about blunted cones of large opening angle at angle of attack
Application of a general method for calculation of inviscid hypersonic flow fields is discussed. General considerations are analyzed along with the sonic corner and the stagnation region. It is concluded that the complications caused by the requirement for sonic flow at the rear corner and particularly by the uncertain position of the stagnation streamline lead to sufficient difficulties with convergence of iterations that a practical procedure is not likely to be found.
Maslen, S. H.↗
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 0 and -3 degree trim and with a 22 1/2 degree angle of dead rise
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Batterson, Sidney A↗
A low-speed experimental study of the directional characteristics of a sharp-nosed fuselage through a large angle-of-attack range at zero angle of sideslip
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Letko, William↗
Free-flight Skin-temperature and Surface-pressure Measurements on a Highly Polished Nose Having a 100 Degree Total-angle Cone and a 10 Degree Half-angle Conical Flare Section up to a Mach Number of 4.08
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Rashis, Bernard↗
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 6 degrees and 9 degrees trim and a 22-1/2 degree angle of dead rise
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FLOATS - IMPACT - TANK TESTS (NACA)↗
Variation of Hydrodynamic Impact Loads with Flight-path Angle for a Prismatic Float at 3 Degree Trim and with a 22 1/2 Degree Angle of Dead Rise
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LANDINGS - SEAPLANES↗
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 12 degree trim and with a 22-1/2 degree angle of dead rise
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LOADS - FLOATS↗