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  • THERMODYNAMICS AND COMBUSTION  (1.363)
  • Animals
  • AERODYNAMICS
  • 1970-1974  (2.619)
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  • 1
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    Ablator manufacturing (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Studies are being conducted to determine how manufacturing-induced defects affect the performance of ablative heat shields. If commonly occurring defects do not affect material performance, simpler manufacturing techniques can be used, quality control requirements can be relaxed, repair and rework operations can be held to a minimum, and thus the total manufacturing cost can be reduced.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA Space Shuttle Technol. Conf.; p 475-504
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  • 2
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    Manufacturing developments in insulation application (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Manufacturing development studies have been conducted to provide information on the fabrication and handling characteristics of a number of candidate multilayer insulation systems. The application of these complex, lightweight insulation systems to large-scale, flight-type cryogenic tankage and other structures has of necessity required the development of new methods, processes, and tooling concepts. Results of some of the studies that have contributed to the advancement of cryogenic technology are presented. The insulation systems that are of primary importance for future application are those using the sliced foam spacers, the net type spacers, the glass fiber paper spacers, and the Superfloc system which consists of tufts of dacron fibers flocked on the surface of the radiation shields.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 73-92
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  • 3
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    Design for advanced insulation systems (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The design of principal multilayer insulation (MLI) systems being investigated by Marshall Space Flight Center and its contractors for application to flight-type cryogenic tankage for long-term storage in space vehicles is described. The MLI systems were designed for application to a 105 in. diameter cryogenic test tank to simulate full-scale design and installation methods representative of flight-type hardware. The MLI systems selected for design represent systems suitable for use on space vehicles such as the modular nuclear vehicles that require application of thicknesses up to 6 in. The MLI systems are lightweight and structurally efficient.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 53-72
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  • 4
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    Multilayer high performance insulation materials (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: A number of tests are required to evaluate both multilayer high performance insulation samples and the materials that comprise them. Some of the techniques and tests being employed for these evaluations and some of the results obtained from thermal conductivity tests, outgassing studies, effect of pressure on layer density tests, hypervelocity impact tests, and a multilayer high performance insulation ambient storage program at the Kennedy Space Center are presented.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Cryog. Res. At MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 93-98
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  • 5
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    Fire extinguishment in hypobaric and hyperbaric environments (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Work that has been performed to provide information on the effects of various fire extinguishing agents in special atmospheres is discussed. Data used in the development of both equipment and techniques for manned spacecraft and related equipment are discussed. The equipment includes a hypobaric chamber suitable for low pressure use and a hyperbaric chamber for high pressure operation. The effectiveness of agents in weightless environment is also discussed.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Conf. on Mater. for Improved Fire Safety; p 163-169
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  • 6
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    The combustion process (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The effect of thermodynamic, chemical, and physical properties on the combustion of materials is discussed. The mechanisms which produce and support combustion of various materials are examined. The effects of free radical reactions, convection and gravitational effects on combustion rates, and changes in flame propagation due to size and shape of surfaces are described.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Conf. on Mater. for Improved Fire Safety; p 3-7
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  • 7
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    Conditions for local thermodynamic equilibrium in uranium (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Model for calculation of parameters for local thermodynamic equilibrium in uranium
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: FLORIDA UNIV. RES. ON URANIUM PLASMAS AND THEIR TECHNOL. APPL. 1971; P 173-178
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  • 8
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    Application of advanced aerodynamics to future transport aircraft (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Applications of supercritical airfoils to transport aircraft designs
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 165-176
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  • 9
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    Aircraft response to the wing trailing vortices generated by large jet transports (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Flight tests for evaluating effect of wing-tip vortex wake generated by large jet transports on smaller aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 115-126
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  • 10
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    Progress report on wing-trailing-vortex studies (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Effect of wing-tip vortex wakes generated by large jet transport aircraft on smaller airplanes
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 101-113
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  • 11
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    Gust alleviation (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Alleviation of lateral and longitudinal gust effects on aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 505-553
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  • 12
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    Effects of aeroelasticity on static aerodynamic derivatives (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Effects of aeroelasticity on static longitudinal aerodynamic derivatives
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 375-438
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  • 13
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    Design of bodies for low drag and high performance in practical hypersonic flight (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Minimizing drag and increasing performance of optimum shapes at hypersonic flight
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 103-174
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  • 14
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    Methods of obtaining stability derivatives (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Least squares method and iteration technique for obtaining aerodynamic stability derivatives
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 71-101
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  • 15
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    Thermal design of a satellite telescope (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Thermal control techniques in designing large orbiting telescopes
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA, WASHINGTON OPT. TELESCOPE TECHNOL. 1970; P 359-379
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  • 16
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    Thermodynamics of the internal combustion engine (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Pollution aspects of internal combustion engine thermodynamics
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: ET. AND THERMODYN. IN HIGH TEMP. GASES 1970; P 31-40
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  • 17
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    Analysis of the flow field of a jet in a subsonic crosswind (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Jet induced flow field effects on V/STOL aircraft in subsonic transition flight
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 683-702
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  • 18
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    Procedures for designing supersonic bodies of revolution from prescribed surface pressure distributions (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Iterative method for designing supersonic body of revolution from surface pressure distribution
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 75-84
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  • 19
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    Rocket combustion instability suppression with cavity resonators (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Properly tuned Helmholtz resonator damping devices are an effective method for eliminating high frequency combustion instability in rocket engine thrust chambers. A program was implemented with the objective of extending Helmholtz resonator theory to thrust chamber conditions to establish a standard design procedure. By using systematic cold-flow testing and hot firings, empirical design equations were formulated. An effort is currently underway to extend the design theory to other types of acoustical damping devices such as quarter-wave tubes and slots.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Res. Achievements Rev., Vol. 4, No. 6; p 53-59
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  • 20
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    Reusable surface insulation materials research and development (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Reusable surface insulation is considered a prime candidate for heat shielding large areas of the space shuttle vehicle. The composition and fabrication of RSI materials are discussed, followed by evolution of RSI and current problems, physical and thermal properties, arc plasma test data and results, and material improvement research. Finally, a summary of RSI technology status is presented.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA Space Shuttle Technol. Conf.; p 373-433
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  • 21
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    Materials and design for ablative heat shields (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The goal of the ablation technology program is to bring ablation research and development to a high state of readiness for application to space shuttle vehicles. Some recent results and current work in the areas of materials, designs, and refurbishment for ablative TPS are reported. Future research and development needs are also presented.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA Space Shuttle Technol. Conf.; p 505-536
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  • 22
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    Thermal protection system trade studies on ablators and reuseable surface insulation (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Analytical trade studies are presented that consider passive TPS configurations using the following material categories: (1) reuseable surface insulation - surface-coated rigidized ceramic fiber; (2) low density charring ablators; and (3) carbon-carbon and high density ablators for leading edge areas. Emphasized are effects on TPS weight by variations in entry trajectories and material thermal characteristics.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA Space Shuttle Technol. Conf.; p 303-334
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  • 23
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    An assessment of radiative metallic thermal protection systems for space shuttle (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The metallic thermal protection system technology program for the space shuttle is reviewed for the areas of environmental uncertainties, materials data base, TPS design concepts and heat-shield panel configurations, testing and evaluation of materials, panels, and complete systems.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA Space Shuttle Technol. Conf.; p 267-302
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  • 24
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    Development of a silicone ablator for high-heat-flux and high-shear-rate condition (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: A silicone material was developed which gives suitable ablative protection in the high heat flux, high shear environments encountered in severe reentry applications, such as nose cones for ballistic vehicles and protection of leading edges or other critical areas of a vehicle. In addition, the ease of handling, low application cost, and room temperature cure make such a silicon material suitable nozzles for the large rockets necessary for vehicle launching. The development of this product is traced from the selection of suitable polymers through the choice of fillers and the finalization of filler loadings.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA. Goddard Space Flight Center Space Simulation; p 725-748
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  • 25
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    Space simulation and rate dependent radiation testing (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: An environmental test facility is described which allows in-situ measurements for evaluation of near real time sinergistic effects of combined space environments.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA. Goddard Space Flight Center Space Simulation; p 453-460
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  • 26
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    Multilayer insulation thermal protection systems technology (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: A summary is presented of the work performed by Marshall Space Flight Center (MSFC) and industry toward the development of flight-type multilayer insulation(MLI) systems. The MSFC MLI program is divided into three large categories: (1) the generation and compilation of MLI composite test data; (2) the analysis, design, and testing of heat flow through MLI applied to ducting, seams, electrical feedthroughs, structural supports, and the tank sidewall; and (3) the development, modification, and utilization of new testing procedures, tanks, and the test facilities. Numerous data have been generated, analyzed, and documented on different MLI composites.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Cryog. Res. at MSFC: Achievements Rev., Vol.4, No. 2; p 5-52
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  • 27
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    Nozzle exhaust plume backscatter experiment using the JPL Molsink facility (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Qualitative tests were made by injecting water through a rocket nozzle wall, and the droplet trajectories were observed photographically. These tests were conducted for nozzles in which boundary layer flow is significant. The tests indicated that both gases and particulate matter will be found in the region outside of the plume boundaries, and can be calculated using current analytical techniques. A test program is being conducted to measure the distribution of exhaust gases from small nozzles using an electron beam/photomultiplier system and a matrix of quartz crystal microbalances. Calibration tests, using simulated hydrazine exhaust product gas mixtures, were also conducted. The test program and results of the pumping calibration tests with hydrazine (simulated hydrazine exhaust products) are reported.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 89-96
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  • 28
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    Considerations on precision temperature control of a large orbiting telescope (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Precision temperature control of large orbiting telescopes
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: OPT. TELESCOPE TECHNOL. 1970; P 417-424
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  • 29
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    Rate constants from ignition studies of the H2-CO-O2 system (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Rate constant determination for ignition of hydrogen carbon monoxide oxygen system
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: ET. AND THERMODYN. IN HIGH TEMP. GASES 1970; P 105-117
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  • 30
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    Ground-wind-load considerations for space shuttle vehicles (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Ground wind loads on reusable space shuttles
    Schlagwort(e): AERODYNAMICS
    Materialart: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 143-160
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  • 31
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    Buffet and aerodynamic noise (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Space shuttle buffeting and aerodynamic noise
    Schlagwort(e): AERODYNAMICS
    Materialart: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 238-247
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  • 32
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    Theoretical investigation of ducted fan interference for transport-type aircraft (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Ducted fan interference analysis for transport aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 703-719
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  • 33
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    Time-dependent numerical method for treating complicated blunt-body flow fields (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Time-dependent numerical method for blunt body flow field solutions
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 177-195
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  • 34
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    A critical evaluation of analytic methods for predicting laminar-boundary-layer shock-wave interaction (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Prediction methods for boundary layer and flow field characteristics in shock wave-boundary layer interaction
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 515-539
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  • 35
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    A numerical method for computing three-dimensional viscous supersonic flow fields about slender bodies (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Numerical analysis of three dimensional viscous supersonic flow fields about slender bodies
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 265-321
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  • 36
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    In-flight aeroacoustic environments on prospective space shuttle vehicles (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The problem of in-flight aerodynamic noise has been studied by reliable estimates of full scale surface-pressure fluctuations from scale model tests in wind tunnels. Scaling relationships have been verified, and many details of the fluctuating pressure characteristics such as spatial correlation and convection velocities are understood. The effects of the wind tunnel environmental turbulence and noise have also been investigated sufficiently so that threshold levels of usable data are known.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA Space Shuttle Technol. Conf.; p 71-96
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  • 37
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    Oxidation protected carbon-carbon (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Pyrolized carbon-carbon has one unique advantage over other materials that makes its application to the space shuttle thermal protection system very attractive. This unique characteristic is the increase in material strength and modulus with increase in temperature up to about 2500 K (4040 F). Offsetting this unique advantage are disadvantages which include brittleness, high cost, and the tendency of the material to react with oxygen, particularly at high temperatures. The development of an oxidation inhibitor for the material and the definition of fabrication processes for selected full-scale components are considered.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA Space Shuttle Technol. Conf.; p 335-372
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  • 38
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    Development of materials screening tests for oxygen-enriched environments (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The criteria governing materials to be used in an oxygen enriched atmosphere and tests to determine suitability for fireproof considerations in spacecraft design are discussed. The nine tests applied to materials before acceptance in spacecraft construction are presented. The application of the standard tests to determine ranking of materials is included.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Conf. on Mater. for Improved Fire Safety; p 23-27
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  • 39
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    Optimization of supersonic inlets using the method of characteristics (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Method of characteristics for computerized design of optimal supersonic inlets
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 569-581
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  • 40
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    A new method for calculating near and far field pressure about arbitrary configurations (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Aerodynamic method of characteristics for pressure field calculations about wing-body combinations
    Schlagwort(e): AERODYNAMICS
    Materialart: L METHODS IN AIRCRAFT AERODYN. 1970; P 215-227
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  • 41
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    The analysis of propeller-wing flow interaction (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Numerical analysis of propeller-wing flow interaction with slipstreams
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 721-742
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  • 42
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    Heat pipes for spacecraft temperature control: Their usefulness and limitations (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Heat pipes are used in spacecraft to equalize the temperature of structures and maintain temperature control of electronic components. Information is provided for a designer on: (1) a typical mounting technique, (2) choices available in wick geometries and fluids, (3) tests involved in flight-qualifying the design, and (4) heat pipe limitations. An evaluation of several heat pipe designs showed that the behavior of heat pipes at room temperature does not necessarily correlate with the classic equations used to predict their performance. They are sensitive to such parameters as temperature, fluid inventory, orientation, and noncondensable gases.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: 6th Aerospace Mech. Symp.; p 33-41
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  • 43
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    Materials for foam type insulation (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: An internal foam fabrication is one of the concepts being considered for cryogenic insulation on the hydrogen tanks of the shuttle vehicle. The three-dimensional polyurethane used on the S-4 B tanks failed to meet the higher temperature requirements of the shuttle vehicle, however, and other foams under consideration include polyisocyanurates, polyphenylene oxides, polyimides, and polybenzimidazoles. Improved adhesive systems for attaching the foams to the interior tank wall are under study.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 179-184
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  • 44
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    A review of the Grumman orbiter wind tunnel heat transfer tests (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Tests were conducted in the NASA Langley continuous flow, variable density and Mach 20 helium tunnels. The orbiter was tested alone and with various side and tandem mounted tanks. Test conditions spanned a Reynolds number range which resulted in both laminar and turbulent flows. Experimental studies also examined the heat transfer problems associated with integration of the auxiliary propulsion system into the orbiter. Tests in the hypersonic shock tunnel investigated heating to cavities and heating from single and multiple hydrogen-oxygen plumes while tests, run as part of the configuration evaluation, examined the heating to wing pods.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 297-345
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  • 45
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    Flammability tests for Apollo command module and lunar module mockup (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The flammability test program for Apollo command module and lunar module mockups is described. The fire safety design of the modules was verified by performing deliberate ignitions at many locations while the interior atmosphere was controlled to simulate realistic flight conditions. The data obtained for each test and restrictions on various materials are discussed.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Conf. on Mater. for Improved Fire Safety; p 43-54
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  • 46
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    Manned spacecraft nonmetallic-materials flammability selection criteria and requirements (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The criteria and requirements governing the selection and use of nonmetallic materials in manned spacecraft to control potential fire hazards are reviewed. The development of flammability requirements is discussed and traced through the historical evolution. Events that dictated the changes that have taken place are discussed. The current nonmetallic material requirements are presented. Significant features of a nonmetallic materials handbook are included.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Conf. on Mater. for Improved Fire Safety; p 9-21
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  • 47
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    Wind tunnel simulation of ground wind shear and turbulence spectra with possible application to space shuttle launch problems (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Wind tunnel simulation of ground wind shear and turbulence spectra and application to space shuttle launching
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 161-175
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  • 48
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    Theoretical studies of vortex flow on slender wing-body combinations (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Lift and pressure distribution calculations for winged body with leading edge vortices
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 113-129
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  • 49
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    Finite-difference analysis of the compressible turbulent boundary layer on a blunt swept slab with leading-edge blowing (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite difference solution for compressible turbulent boundary layer equations of swept slab with leading edge blowing
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 417-472
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  • 50
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    Recent advances in research on compressible turbulent boundary layers (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Review of prediction methods for compressible turbulent boundary layers
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 355-416
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  • 51
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    An analysis of finite-difference techniques applied to equations governing convective transfer (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite difference analysis of hyperbolic partial differential equations
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 245-264
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  • 52
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    Prediction of supersonic and hypersonic inlet flow fields (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Computer programs for predicting flow field properties in supersonic and hypersonic inlets
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 583-595
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  • 53
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    Improvement of wing-body interference theory for hypersonic speeds (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Wing-body interference theory for calculating lift slope and stability at hypersonic speed
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 101-111
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  • 54
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    Some recent developments in subsonic lifting-surface theory (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Numerical lifting surface theory with spanwise distribution of control points
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 1-35
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  • 55
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    Application of the method of characteristics to noncircular bodies at angle of attack (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Method of characteristics for flow field analysis on elliptical winged body
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 159-176
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  • 56
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    The use of finite element methods for predicting the aerodynamics of wing-body combinations (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite element method for predicting aerodynamic characteristics of wing-body combinations
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 37-51
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  • 57
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    Potential flow solutions for inlets of VTOL lift fans and engines (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Potential flow solution for VTOL inlets in static and crossflow operation
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 659-681
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  • 58
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    Prediction of heat-transfer characteristics for ejector exhaust nozzles (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Heat balance equation for predicting heat transfer of ejector exhaust nozzle at afterburning phase
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 623-638
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  • 59
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    Methods of analyzing propeller and rotor boundary layers with crossflow (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Analysis of secondary flow effects in propeller and rotor boundary layers
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 473-514
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  • 60
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    A new method for analysis of transonic flow (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite difference method for transonic flow solution in axial stator
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 597-621
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  • 61
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    A method for analyzing the interaction of an oblique shock wave and a boundary layer (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Method of characteristics for calculating oblique shock wave interaction with turbulent boundary layer
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 541-567
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  • 62
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    A critical evaluation of panel flutter aerodynamics (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Aerodynamic forces in supersonic panel flutter
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 335-353
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  • 63
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    An analysis of Coanda jet flows (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Static laminar Coanda jet flow around circular cylinder with external flow entrainment
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 197-214
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  • 64
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    Empirical method for estimating pressures on elliptic cones (1970)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Correlation method for estimating pressure distribution over elliptic supersonic cones
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 85-99
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  • 65
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    Calculative techniques for transonic flows (1970)
    In:  CASI
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    Publikationsdatum: 2005-11-27
    Beschreibung: Calculation methods for predicting transonic aerodynamic characteristics of wing-body combinations
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 53-73
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  • 66
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    Flutter and unsteady lift theory (1971)
    In:  CASI
    Details
    Publikationsdatum: 2009-11-16
    Beschreibung: Aeroelasticity and unsteady flow problems of aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 289-374
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  • 67
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    The relevance of recent advances in unsteady aerodynamics to the space shuttle program (1970)
    In:  CASI
    Details
    Publikationsdatum: 2009-11-17
    Beschreibung: Prediction of steady and unsteady airloads on space shuttles
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 223-237
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  • 68
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    Heat-transfer testing procedures in phase B shuttle studies with emphasis on phase change data improvement (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: The procedures used in the application of the phase change technique to the phase B shuttle configuration are discussed along with factors which may affect data accuracy. These factors include variation of thermal properties of phase change model material, sensitivity of measured heat transfer coefficients to the assumed value of the adiabatic to total temperature ratio, and wall temperature effects. These sensitivities are illustrated in sample calculations for a shuttle geometry. Factors which may affect the visual clarity and interpretation of phase change data are discussed, and a method of improving photographic data quality through the use of polarized light is presented.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 661-682
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  • 69
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    An analysis of the booster plume impingement environment during the space shuttle nominal staging maneuver (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: An experimental study of the plume impingement heating on the space shuttle booster afterbody resulting from the space shuttle orbiter engine plumes was conducted. The 1/100-scale model tests consisted of one and two orbiter engine firings on a flat plate, a flat plate with a fin, and a cylinder model. The plume impingement heating rates on these surfaces were measured using thin film heat transfer gages. Results indicate the engine simulation is a reasonable approximation to the two engine configuration, but more tests are needed to verify the plume model of the main engine configuration. For impingment, results show models experienced laminar boundary layer convective heating. Therefore, tests at higher Reynolds numbers are needed to determine impingment heating.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 607-644
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  • 70
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    Determination of aerothermodynamic environment uncertainties with application to space shuttle vehicles (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: In an effort to minimize the cost of the thermal protection system (TPS) for space shuttles, an analysis is made of environmental uncertainties. The basic categories of these uncertainties include aerodynamic heating, trajectory dispersions, atmospheric variations, and vehicle attitude variations. Also discussed are TPS design sensitivity to environmental uncertainties, and uncertainty profiles. Preliminary results indicate moderate TPS cost for a high confidence level environment may be obtained.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 503-518
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  • 71
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    Aerothermodynamic measurements for space shuttle configuration in hypersonic wind tunnels (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: The effect of shuttle configuration geometry, angle of attack, and free stream flow conditions on the heat-transfer distribution as influenced by three-dimensional effects, the wing-fuselage shock-interaction, and resultant wing-impingement phenomena are examined. In addition, the data provided information regarding the flow field in the vicinity of the nose and boundary layer transition in the plane of symmetry of the fuselage. The data included measurements of the surface pressure, the heat transfer rate distributions, (using models instrumented with thermocouples and models painted with thermographic phosphor) and schlieren and shadowgraph photographs. Posttest photographs of the painted models supplemented the heat transfer data.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 469-501
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  • 72
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    Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 2: Studies of lee-surface heating at hypersonic Mach numbers (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: Lee surface heating data, obtained at relatively low unit Reynolds numbers at Mach 6 and 19, are discussed with emphasis on the peak heating behavior. Surface pressures measured along the lee meridian of the delta-wing orbiter are presented and analyzed in conjunction with the heating. The effects of nose bluntness and lee surface geometry on the heating are discussed and general guidelines are presented for modifying the lee surface geometry of the shuttle to reduce vortex-induced heating. The application of the wind tunnel results to realistic shuttle flight conditions is discussed.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 451-467
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  • 73
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    Effects of roughness on heating and boundary-layer transition. Part 2: effects of discrete roughness on heating (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: A preliminary investigation on the effects of roughness on heating in delta wing orbiters was conducted on the windward surface of the vehicle. The purpose of the experiment was to determine the feasibility of using parametric relationships obtained from discrete roughness effects on heating in flat plates and cones, to complex shuttle configurations. An attempt was also made to characterize what parameters were needed to influence roughness. Experimental results show that effective roughness Reynolds numbers are less than or equal to those of flat plates at the same edge Mach number, but, the roughness correlations for plates and cones cannot be applied to the shuttle configuration.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 395-411
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  • 74
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    Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 1: Flow separation and flow field viscous phenomena of a delta-wing shuttle orbiter configuration (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: Results of a pitot pressure investigation of the flow field on the lee side of a delta wing shuttle orbiter are presented. The results delineate the extent of the lee side separated flow and give a tentative cross sectional definition to the shock wave structure for angles of attack of 15 deg and 30 deg. It is shown that while, in general, the effects of Reynolds number on the flow field are not large, detailed effects are observed that may have significant bearing on the heating estimate. Two examples are cited for an angle of attack of 15 deg; these are: (1) The scope of the vertical tail exposed to the unseparated flow increases with increasing Reynolds number and (2) the depth of the separated flow adjacent ot where the bow wave crosses the wing appears to decrease with increasing Reynolds number. In addition, it is shown that at a spanwise station outboard of the wing-fuselage juncture, increasing Reynolds number decreased the pitot pressure in the unseparated flow. This defect of pitot pressure appears associated with the flow over the wing-fillet-fuselage juncture.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 413-449
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  • 75
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    Effects of roughness on heating and boundary-layer transition. Part 1: Effects of simulated panel joints on boundary-layer transition (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: The effects of distributed roughness, arising from space shuttle orbiter panel joints, on boundary layer transition are investigated. The North American Rockwell 134B delta wing shuttle configuration was used for the study. Results show: (1) Premature boundary layer transition occurred in models having simulated heat shield panels with rased joints. (2) Laminar flow was maintained with slot type panel joint models to a Reynolds number twice that at which transition occurred in raised joints. (3) Significant increases in peak surface temperature and the time during which turbulent flow occurs may result from distributed roughness of heat shield panel joints. (4) Laminar and turbulent heating levels were predicted within available theories. (5) A complex interference between the wing and fuselage flow was observed in the delta wing model.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 375-394
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  • 76
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    High Reynolds number turbulent heating to two simplified shuttle configurations (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: Turbulent heating and transition data, taken from three test facilities, for two space shuttle configurations are presented. Major efforts were on: (1) the effect of the two geometries having different amounts of cross flow and how the different cross flows affect heating and transition, (2) the experimental level of turbulent heating and the ability to predict the level of turbulent heating, and (3) a comparison of the transitional and turbulent heating in three facilities with two model scale sizes to investigate the facility effects and scale-size effect on transition and turbulent heating. The three facilities in which the configurations were tested are the Langley Mach 8 variable-density hypersonic tunnel and the Arnold Engineering Development Center tunnel B and tunnel F at Mach numbers of 8 and 10.5, respectively.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 347-373
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  • 77
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    Experimental and theoretical aerodynamic heating and flow field analysis of a space shuttle orbiter (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-07-18
    Beschreibung: The results of work on the McDonnell Douglas delta wing orbiter are summarized and compared to other data and theories where applicable. The tests were conducted in the continuous hypersonic Tunnel B at Mach 8 and in the hypervelocity hotshot Tunnel F at Mach 10.5. Photographic data are used to illustrate the regions of peak heating on the lee-side and to show the vortical nature of the flow. Windward centerline data include measurements of shock angle, surface pressure, flow field pitot pressure and total temperature, and heat transfer rate coefficient distributions. Shock angles, surface pressures, and local Mach number distributions are compared with tangent cone theory over an angle of attack range from 10 to 60 deg. The measured heat transfer rate coefficient distributions are compared to both laminar and turbulent theories and boundary layer transition data are compared to the McDonnell Douglas criteria.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 261-296
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  • 78
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    Summary and future plans (1972)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 121-133
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  • 79
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    Piloting and operational aspets of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 97-110
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  • 80
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    Status of the F-8 supercritical wing program (1972)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 49-58
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  • 81
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    F-8 supercritical wing pressure distribution evaluation (1972)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 71-84
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  • 82
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    Buffet characteristics of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 85-96
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  • 83
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    The NASA supercritical airfoil and its application to swept wings (1972)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 1-12
    Format: text
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  • 84
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    Evolution of the F-8 supercritical wing configuration (1972)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 35-48
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  • 85
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    Preliminary lift and drag characteristics of the F-8 supercritical wing airplane (1973)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: its Supercritical Wing Technol.: A Report on Flight Evaluation; p 59-70
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  • 86
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    A new look at AP/composite propellant combustion (1973)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: Some theoretical studies on the time-independent and oscillatory combustion of nonmetallized ammonium perchlorate (AP)/composite propellants are presented. A coherent and unified interpretation was made of the voluminous data available from experiments related to propellant combustion. Three fundamental hypotheses are introduced: the extent of propellant degradation at the vaporization step has to be specified through a scientific criterion; the condensed-phase degradation reaction of ammonium perchlorate to a vaporizable state is the overall rate-limiting step; gas-phase combustion rate is controlled by the mixing rate of fuel and oxidizer vapors. In the treatment of oscillatory combustion, the assumption of quasi-steady fluctuations in the gas phase is used to supplement these hypotheses.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: JPL JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-77
    Format: text
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  • 87
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    Small rocket exhaust plume data (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: During recent cryodeposit tests with an 0.18-N thruster, the mass flux in the plume back field was measured for the first time for nitrogen, carbon dioxide, and a mixture of nitrogen, hydrogen, and ammonia at various inlet pressures. This mixture simulated gases that would be generated by a hydrazine plenum attitude propulsion system. The measurements furnish a base upon which to build a mathematical model of plume back flow that will be used in predicting the mass distribution in the boundary region of other plumes. The results are analyzed and compared with existing analytical predictions.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: JPL Quart. Tech. Rev., Vol. 2, No. 2; p 90-99
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  • 88
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    A space application of a cryogenic heat pipe (1970)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-25
    Beschreibung: Feasibility of cryogenic heat pipe for cooling isotopic spacecraft power supply cycle
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: NIFICANT ACCOMPLISHMENTS IN SCI. AND TECHNOL. AT GODDARD SPACE FLIGHT CENTER 1970; P 244-248
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  • 89
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    Method of calculating gas dynamics and heat transfer in single stage refrigeration units (1974)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-11
    Beschreibung: A generalized mathematical model of gas-dynamic and heat transfer processes in single-stage regenerative installations operating in Stirling, MacMahon, Gifford-MacMahon, and pulsating tube cycles is proposed. A numerical method os solving initial equations on a digital computer is given. This makes it possible to calculate the change in the thermodynamic parameters in the working cycle in different machine components, as well as the dependence of cold productivity on the temperature level in the steady regime.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Space Res. in the Ukraine, No. 3 (NASA-TT-F-15537); p 124-138
    Format: text
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  • 90
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    Inflight thermodynamic properties (1973)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-02
    Beschreibung: The inflight thermodynamic parameters (temperature, pressure, and density) of the atmosphere are presented. Mean and extreme values of the thermodynamic parameters given here can be used in application of many aerospace problems, such as: (1) research and planning and engineering design of remote earth sensing systems; (2) vehicle design and development; and (3) vehicle trajectory analysis, dealing with vehicle thrust, dynamic pressure, aerodynamic drag, aerodynamic heating, vibration, structural and guidance limitations, and reentry analysis. Atmospheric density plays a very important role in most of the above problems. A subsection on reentry is presented, giving atmospheric models to be used for reentry heating, trajectory, etc., analysis.
    Schlagwort(e): THERMODYNAMICS AND COMBUSTION
    Materialart: Terrest. Environ. (Climatic) Criteria Guidelines for Use in Aerospace Vehicle Develop., 1973 Rev.; 34 p
    Format: text
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  • 91
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    EBF noise tests with engine under-the-wing and over-the-wing configurations (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: Noise tests of externally blown flaps with the engine under the wing and engine over the wing configurations were conducted. Flap noise data obtained on a TF-34 aircraft are discussed. Noise data obtained during a free-jet forward-speed-effect analysis are presented. Noise sources associated with upper surface flap blowing are described. Results of a small scale configuration screening study and some large scale model test data are analyzed. The noise data for the engine over wing configurations are compared with the engine under the wing configurations.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 455-473
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  • 92
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    Flap noise generation and control (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated-powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 413-426
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  • 93
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    Acoustic characteristics of large-scale STOL models at forward speed (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 443-454
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  • 94
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    Externally blown flap impingement noise (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: Tests of the noise produced by the impingement of the jet exhaust on the wing and flap for an externally blown flap system were conducted with a CF700 turbofan engine and an F-111B wing panel. The noise produced with a daisy nozzle installed on the engine was greater than that produced by a conical nozzle at the same thrust. The presence of the wing next to the test nozzles increased the noise, as did increasing the flap deflection angle. Compared with the conical nozzle, the daisy nozzle produced slightly less noise at a flap deflection of 60 deg but produced more noise at the lower flap deflections tested. Tests showed that the single-slotted flap deflected 60 deg, produced less noise than the double-slotted flaps. Also, maintaining the maximum distance between the exit nozzle and flap system resulted in a minor reduction in noise.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 427-441
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  • 95
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    Externally blown flap dynamic loads (1973)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: Some of the principal results obtained in three series of measurements of fluctuating surface pressures induced on externally blown flaps by jet impingment are presented. Large- and small-scale models and hot- and cold-flow tests are considered. The discussion sets forth scaling parameters and consistent features of the root-mean-square values and spectra of the loading. Implications of these results with regard to sonic fatigue are indicated.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 131-142
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  • 96
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    Survey of wing and flap lower-surface temperatures and pressures during full-scale ground tests of an externally blown flap system (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg, the angle of incidence between the engine and the wing was fixed at 3 deg, and the tests were conducted with the flap retracted, extended and deflected 35 deg, and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 143-156
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  • 97
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    Simulator evaluation of the flying qualities of externally blown flap and augmentor wing transport configurations (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 157-800
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  • 98
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    Aerodynamics of the upper surface blow flap (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: The results of some preliminary wind-tunnel investigations made to provide fundamental aerodynamic information on the upper surface blown jet-flap concept incorporating high-bypass-ratio turbofan engines are summarized. The results of the investigation have shown the concept to have aerodynamic performance generally similar to that of other externally blown high-lift systems. A few of the more critical problems associated with this concept have been identified and preliminary solutions to some of these problems have been found. These results have proven to be sufficiently encouraging to warrant continuation of fundamental research efforts on the concept.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center STOL Technol.; p 97-110
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  • 99
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    Advanced augmentor-wing research (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: Results of research on advanced augmentors are discussed. Research concerned with performance has indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles, (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest, and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data has shown that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 87-96
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  • 100
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    Aerodynamic characteristics of a swept augmentor wing (1972)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-27
    Beschreibung: A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 71-86
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