Verification of takeoff performance predictions for the XB-70 airplane
Takeoff performance predictions for XB-70 delta wing supersonic aircraft
Larson, T. J.↗
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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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Performance verification trajectories for the McDonnell-Douglas high cross-range shuttle configuration
Space shuttle trajectory performance data for east and west test range launch simulations
Etheridge, O. E.↗
Research and development of umbilical hose assembly concepts for manned space flight including design verification test report REDAR-RTR-351
Umbilical hose assembly and PLSS oxygen and water hose designs
Sylvester, W. A.↗
Experimental verification of the design of an axial injection crossed-field amplifier
Design of S band axial injection cross field amplifier for satellite borne transmitter
Mcdowell, H. L.↗
The design of an automated verification of redundant systems
Handbook describes design processes, presents design considerations and techniques, gives tutorial material on implementation and methodology, shows design aids, illustrates use of design aids and application samples, and identifies general practices to be adhered to or avoided.
Ford, F. A.↗
Improved fluid dynamics similarity, analysis and verification. Part 5: Analytical and experimental studies of thermal stratification phenomena
The stratification behavior of a contained fluid subjected to transient free convection heat transfer was studied. A rectangular vessel was employed with heat transfer from two opposite walls of the vessel to the fluid. The wall temperature was increased suddenly to initiate the process and was then maintained constant throughout the transient stratification period. Thermocouples were positioned on a post at the center of the vessel. They were adjusted so that temperatures could be measured at the fluid surface and at specific depths beneath the surface. The predicted values of the surface temperature and the stratified layer thickness were found to agree reasonably well with the experimental measurements. The experiments also provided information on the transient centerline temperature distribution and the transient flow distribution.
Winter, E. R. F.↗
Development and verification of design methods for ducts in a space nuclear shield
A practical method for computing the effectiveness of a space nuclear shield perforated by small tubing and cavities is reported. Performed calculations use solutions for a two dimensional transport code and evaluate perturbations of that solution using last flight estimates and other kernel integration techniques. In general, perturbations are viewed as a change in source strength of scattered radiation and a change in attenuation properties of the region.
Cerbone, R. J.↗
Space shuttle: Verification of transition reentry corridor at high angles of attack and determination of transition aerodynamic characteristics and subsonic aerodynamic characteristics at low angles of attack for the Boeing H-32 booster
Experimental aerodynamic investigations were made in a transonic wind tunnel on a 1/150-scale model of the Boeing H-32 space shuttle booster configuration. The purpose of the test was: (1) to verify the transonic reentry corridor at high angles of attack; (2) to determine the transonic aerodynamic characteristics; and (3) to determine the subsonic aerodynamic characteristics at low angles of attack. Test variables included configuration buildup, horizontal stabilizer settings of 0 and -20 deg, elevator deflections of 0 and -30 deg, and wing spoiler settings of 60 deg.
Houser, J.↗
Preparation, verification, and operational control of a large space-environment-simulation chamber for contamination sensitive tests
A 2-year program to prepare chamber A at the NASA Manned Spacecraft Center for Apollo telescope mount thermal-vacuum tests is discussed. This program covers modification to existing chamber systems, the development of facility and chamber operating procedures, the selection of chamber cleaning and control methods, and the development and evaluation of diagnostic instrumentation. Extensive efforts to ensure a minimum contamination environment for the Apollo telescope mount test series are illustrated. Recent thermal-vacuum tests of this chamber at progressive stages of cleanliness have demonstrated the success achieved in reducing the particulate and molecular contamination levels of the basic chamber interior.
Visentine, J. T.↗
Laboratory verification optical signal coupling. IMBLMS phase B.4, appendix C, section 12
The design of optical couplers is described for use in the IMBLMS hardwire mode. One coupler transmits data from the bio-belt to the central data system and the other coupler transmits audio frequencies in the opposite direction, from the central data system to the bio-belt. The objective is to isolate the ground system at the body worn bio-belt electronics and the main ground at the central data system, or biomedical and behavioral station. The safety of the subject wearing the bio-belt measuring electronics is the purpose in isolating the wearer from the main system ground.
Source record↗
Laboratory verification respiratory measurements. IMBLMS phase B.4, appendix C, section 13
The B-4 IMBLMS preliminary design of the respiratory measurement element includes certain techniques and apparatus which are quite different from those included in the B-3 version previously delivered to NASA-MSC. A working model was constructed in the laboratory to prove the feasibility of certain key features. The most critical of these is the capability of switching sample gases into the mass spectrometer from two different sources during a single breath cycle. Results proved the feasibility of all of the concepts which were tested, and certain refinements and improvements were included, as well.
Source record↗
Experimental verification of low sonic boom configuration
A configuration designed to produce near field signature has been tested at M = 2.71 and the results are analyzed, by taking in account three-dimensional and second order effects. The configuration has an equivalent total area distribution that corresponds to an airplane flying at 60,000 ft. having a weight of 460,000 lbs, and 300 ft. length. A maximum overpressure of 0.95 lb/square foot has been obtained experimentally. The experimental results agree well with the analysis. The investigation indicates that the three-dimensional effects are very important when the measurements in wind tunnels are taken at small distances from the airplane.
Ferri, A.↗
Verification of theory on weak turbulence relating to the sequence of diffuse plasma resonances in space.
An interpretation of the sequence of diffuse plasma resonances observed by space probes (Alouette 2 and ISIS-1 satellites) is developed in terms of wave-particle nonlinear interaction in a weakly turbulent plasma including the electrostatic electron cyclotron harmonic wave instability. The longest time duration of the center frequency of the diffuse plasma resonance is found to coincide with the most favorable condition for the electrostatic electron cyclotron harmonic wave instability which is obtained by solving the dispersion equation obtained for a linear approximation of the kinetic wave equation for the warm magnetoactive plasma. The electrostatic field due to the transmission of the intense rf pulse produces plasma turbulence involving nonlinear wave-wave interaction and temperature anisotropy which leads to instability. This instability supplies energy to the turbulence. The process can be thought of as a feedback system.
Oya, H.↗
Thermal design verification testing for the ATS-F and -G spacecraft.
There is a wide fluctuation in the internal power dissipation from the components within the earth viewing module (EVM). The electronic component functional reliability required for a two-to-five year mission is the most significant factor for the thermal design criteria. A mathematical thermal model of the EVM and the orbital environment is used to predict the performance of the thermal control system. Comparisons of the results obtained in chamber thermal balance tests with the data computed on the basis of the theoretical model provide the means for validating the thermal design.
Coyle, M.↗
Global oceanic microwave anemometry - A planned space verification experiment.
Recent observations of the wind sensitivity of oceanic backscatter and temperature measurements are shown to have made it possible to design an experiment for verifying the potential use of an operational global satellite anemometer. The experiment is to be conducted with the Skylab in 1973, and its success may lead to the design and flight of an operational microwave scatterometer-radiometer instrument on a small satellite flying in a polar orbit sometime in the late 1970's.
Moore, R. K.↗
Experimental verification of computer spray-combustion models
Analytical model formulation, representing performance of spray-combustion device, is based on understanding of atomization, mixing, vaporization, and combustion which occurs in device. Report lists results of correlations of computed values with values obtained from experiments with rocket combustor. Technique offers excellent method for evaluating validity and ranges of applicability of combustion models.
Nurick, W. H.↗
Handbook of cleaning requirements, procedures, and verification techniques for oxygen systems
Oxygen system cleaning specifications have been drawn from twenty-three government and industrial sources. Cleaning processes for meeting these specifications and recommended postcleaning inspection procedures are compiled in handbook. Microfiche supplement of pertinent pages of listed references is included.
Bankaitis, H.↗
Skylab program CSM verification analysis report
The application of the SINDA computer program for the transient thermodynamic simulation of the Apollo fuel cell/radiator system for the limit condition of the proposed Skylab mission is described. Results are included for the thermal constraints imposed upon the Pratt and Whitney fuel cell power capability by the Block 2 EPS radiator system operating under the Skylab fixed attitude orbits.
Schaefer, J. L.↗