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  • AIRCRAFT  (270)
  • THERMODYNAMICS AND COMBUSTION
  • 1970-1974  (424)
  • 1974  (424)
  • 1
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    Heat Transfer and Thermodynamics: a Compilation (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A compilation is presented for the dissemination of information on technological developments which have potential utility outside the aerospace and nuclear communities. Studies include theories and mechanical considerations in the transfer of heat and the thermodynamic properties of matter and the causes and effects of certain interactions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-SP-5959(01)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal-Structural Evaluation of TD Ni-20Cr Thermal Protection System Panels (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The results of a thermal-structural test program to verify the performance of a metallic/radiative Thermal Protection System (TPS) under reentry conditions are presented. This TPS panel is suitable for multiple reentry, high L/D space vehicles, such as the NASA space shuttle, having surface temperatures up to 1200 C (2200 F). The TPS panel tested consists of a corrugation-stiffened, beaded-skin TD Ni-20Cr metallic heat shield backed by a flexible fibrous quartz and radiative shield insulative system. Test conditions simulated the critical heating and aerodynamic pressure environments expected during 100 repeated missions of a reentry vehicle. Temperatures were measured during each reentry cycle; heat-shield flatness surveys to measure permanent set of the metallic components were made every 10 cycles. The TPS panel, in spite of localized surface failures, performed its designated function.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132487
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    NASA general aviation research overview (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Review of current NASA research programs directly focused on general aviation. Significant accomplishments are cited in the areas of airfoil research, stall/spin technology, crashworthiness, and propulsion noise and efficiency. Highlights of recent NASA organizational developments affecting general aviation research are outlined.
    Keywords: AIRCRAFT
    Type: SAE PAPER 740352 , Business Aircraft Meeting; Apr 02, 1974 - Apr 05, 1974; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Conformal mapping technique for two-dimensional porous media and jet impingement heat transfer (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Transpiration cooling and liquid metals both provide highly effective heat transfer. Using Darcy's law in porous media and the inviscid approximation for liquid metals, the local fluid velocity in these flows equals the gradient of a potential. The energy equation and flow region are simplified when transformed into potential plane coordinates. In these coordinates, the present problems are reduced to heat conduction solutions which are mapped into the physical geometry. Results are obtained for a porous region with simultaneously prescribed surface temperature and heat flux, heat transfer in a two-dimensional porous bed, and heat transfer for two liquid metal slot jets impinging on a heated plate.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Heat Transfer Conference; Sept. 3-7, 1974; Tokyo; Japan
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Determination of stability derivatives of isolated rigid tail assemblies in sideslip and steady roll (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Keywords: AIRCRAFT
    Type: AIAA PAPER 74-1038 , International Symposium on the Technology and Science of Low Speed and Motorless Flight; Sept. 11-13, 1974; Cambridge, MA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Analysis and experimental studies of the control of hang gliders (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A theoretical analysis of the longitudinal and lateral characteristics of hang gliders in straight flight, pullups, and turns is presented. Some examples of the characteristics of a straight-wing configuration and a Rogallo-wing configuration are given. A means for improving the control of hang gliders while retaining the same basic control feel is proposed.
    Keywords: AIRCRAFT
    Type: AIAA PAPER 74-1030 , International Symposium on the Technology and Science of Low Speed and Motorless Flight; Sept. 11-13, 1974; Cambridge, MA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    An exact solution of a simplified two-phase plume model (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An exact solution of a simplified two-phase, gas-particle, rocket exhaust plume model is presented. It may be used to make the upper-bound estimation of the heat flux and pressure loads due to particle impingement on the objects existing in the rocket exhaust plume. By including the correction factors to be determined experimentally, the present technique will provide realistic data concerning the heat and aerodynamic loads on these objects for design purposes. Excellent agreement in trend between the best available computer solution and the present exact solution is shown.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Southeastern Conference on Theoretical and Applied Mechanics; Mar 21, 1974 - Mar 22, 1974; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Cryogenic and low temperature heat pipe/cooler studies for spacecraft application (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The prime purpose of the present work is to examine cryogenic heat pipe/cooler feasibility in the 80 to 100 K temperature range and in the regimes of operation required for NASA spacecraft. Present requirements within these regimes are (1) cooling load of less than 1 to 2 watt per cooler, (2) small detector/heat pipe interface area, and (3) high system reliability and long lifetime operations. The cooling capacity of practical radiant coolers is very low in this temperature range, and very temperature sensitive. Detector performance is also strongly dependent on temperatures in this regime. It is, therefore important to understand the interplay of the heat pipe and its effects on overall system performance.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-753 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Weight estimates for Quiet/STOL aircraft (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Attention is drawn to the dependence of Q/STOL weight estimation relationships on design acoustic level, engine selection, high-lift concept, design criteria such as field lengths, range, speed and payload, aircraft geometry, and design constraints such as vehicle cost and fuel prices. Weight estimate considerations with associated configuration and design details are presented. Typical weight estimating relationships being used in a NASA study contract are also included. Some representative future applications of Q/STOL concepts are visualized as (1) fuel conservative configurations utilizing STOL high-life concepts for obtaining relatively higher wing loadings during cruise, and (2) low-wing loading aircraft configurations with short-range, low-passenger capacity, and low fan-passenger-ratio turbo-fan engines for a future interurban air transportation market.
    Keywords: AIRCRAFT
    Type: SAWE PAPER 1001 , Annual conference of the Society of Allied Weight Engineers; May 06, 1974 - May 08, 1974; Fort Worth, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Atmospheric effects on the inlet system of the YF-12 aircraft (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flights of a YF-12 airplane were performed over a wide range of operating conditions so that detailed comparisons could be made with data from tests on scale models in NASA ground facilities. Extensive flight instrumentation for inlet performance comparisons provided flight data that also lend insight into supersonic inlet operation during atmospheric turbulence. Pressure and flow direction measurements near the inlet gave results different from conventional accelerometer data normally used for flight determination of turbulence severity. A nonturbulent atmospheric temperature excursion during an XB-70 flight caused inlet duct pressure variations as extreme as those experienced during heavy turbulence on the YF-12 airplane.
    Keywords: AIRCRAFT
    Type: National Conference on Environmental Effects on Aircraft and Propulsion Systems; May 21, 1974 - May 23, 1974; Trenton, NJ
    Format: text
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    NASA TECHNICAL REPORTS
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