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At least 415 records · Page 23

All sources NASA NTRS DOE OSTI

DOE OSTI2022

Pacific Marine Energy Center Laser Doppler Velocimetry Commissioning

First commissioning data for the new laser doppler velocimetry (LDV) system that will be used at the Tyler Flume at the University of Washington. The LDV system can measure three components of velocity at a point. For this dataset the three components were operated in non-coincident mode and data were acquired at the center of the empty facility. Comparisons of freestream turbulence were made with a Vectrino slightly upstream of the LDV measurement location.

16 TIDAL AND WAVE POWER↗

NASA NTRS1964

Saturn monthly progress report /january 16, 1964 - february 16, 1964/

Saturn I, IB, and V launch vehicle progress - second stage launching, static test failure, fabrication progress, and fuel tank hydrostatic pressure test

SECOND STAGE↗

NASA NTRS1966

Orthopedic stretcher with average-sized person can pass through 18-inch opening

Modified Robinson stretcher for vertical lifting and carrying, will pass through an opening 18 inches in diameter, while containing a person of average height and weight. A subject 6 feet tall and weighing 200 pounds was lowered and raised out of an 18 inch diameter opening in a tank to test the stretcher.

Lothschuetz, F. X.↗

NASA NTRS1971

Cycle testing of boron filament wound tanks

Filament tensile strengths and pressure-strain characteristics of high modulus, high-strength, boron-filament-wound/resin-composite pressure vessel at ambient and cryogenic temperatures

Alfring, R. J.↗

NASA NTRS1972

Aerodynamic characteristics of several launch configurations utilizing the Titan 3 L booster and MMC DTO-7 Orbiter

The .00429 scale model Titan 3 booster was mated with the DTO-7 space shuttle orbiter with drop tanks and tested for aerodynamic performance in a 14 x 14 inch trisonic wind tunnel. Six component aerodynamic force and moment data were measured on several variations of the above component in a launch configuration over a Mach number range from 0.6 to 3.48. Angle of attack ranged from -12 deg to 12 deg at 0 deg and -6 deg sideslip angle and sideslip angle ranged from -12 deg to 12 deg at 0 deg angle of attack. Date are presented in plotted form in both the stability and body axis system.

Michna, D. J.↗

NASA NTRS1975

Development of thermal stratification and destratification scaling concepts. Volume 2: Stratification

Temperature and pressure data obtained from the saturated Freon 113 PCA closed-tank stratification tests are presented. The data presented in tabular form are the test conditions, sensible heat values, and Freon 113 PCA liquid and ullage (vapor) properties. Also included, are graphical representations of the liquid bulk temperature and pressure histories, and dimensionless liquid-ullage delta-temperature profiles. Modified Grashof numbers and Fourier number-history data are also presented graphically.

Lovrich, T. N.↗

NASA NTRS1975

Surface recession characteristics of a cryogenic insulation subjected to arc-tunnel heating

Specimens of a cryogenic insulation, proposed for use on the space shuttle external tank, were tested in an arc tunnel over a range of heating rates, pressures, and enthalpies corresponding to the shuttle ascent environment. A regression analysis was used to correlate the test data. Correlation equations involving surface recession rate as a function of heating rate, pressure, and enthalpy were developed. These equations can be used to make total surface recession predictions for shuttle ascent flight environments.

Pittman, C. M.↗

NASA NTRS1980

Detection of tanker defects with infrared thermography

Infrared scanning technique for finding defects in secondary barrier of liquid natural gas (LNG) tank has been successfully tested on ship under construction at Newport News Shipbuilding and Dry Dock Company. Technique determines defects with minimal expenditure of time and manpower. Tests could be repeated during life of tanker and make more complicated testing unnecessary. Tests also confirmed that tank did not have any major defects, and tank was certified.

Kantsios, A. G.↗

NASA NTRS1986

Development of a reusable, flight-weight cryogenic foam insulation system

Attention is given to a light weight foam insulation system applicable to reusable cryogenic propellant tankage for hypersonic aircraft and space launch vehicles. The insulation system consists of nominally sized blocks of a high temperature-resistant polymethacrylimide foam that is wrapped with a vapor-impermeable membrane of Kapton-aluminum-Kapton laminate, which is adhesively bonded to the outer propellant tank wall. Test results are presented which indicate that this insulation system is capable of enduring a Mach 5 service environment without structural cracking, deterioration, or loss of performance.

Mcauliffe, P. S.↗

NASA NTRS1993

Mixing and transient interface condensation of a liquid hydrogen tank

Experiments were conducted to investigate the effect of axial jet-induced mixing on the pressure reduction of a thermally stratified liquid hydrogen tank. The tank was nearly cylindrical, having a volume of about 0.144 cu m with 0.559 m in diameter and 0.711 m length. A mixer/pump unit, which had a jet nozzle outlet of 0.0221 m in diameter was located 0.178 m from the tank bottom and was installed inside the tank to generate the axial jet mixing and tank fluid circulation. Mixing tests began with the tank pressures at which the thermal stratification results in 4.9-6.2 K liquid subcooling. The mixing time and transient vapor condensation rate at the liquid-vapor interface are determined. Two mixing time correlations, based on the thermal equilibrium and pressure equilibrium, are developed and expressed as functions of system and buoyancy parameters. The limited liquid hydrogen data of the present study shows that the modified steady state condensation rate correlation may be used to predict the transient condensation rate in a mixing process if the instantaneous values of jet sub cooling and turbulence intensity at the interface are employed.

Lin, C. S.↗

NASA NTRS1948