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  • AERODYNAMICS  (6)
  • THERMODYNAMICS AND COMBUSTION  (5)
  • ASTROPHYSICS
  • 1970-1974  (11)
  • 1
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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
    Publication Date: 2006-03-27
    Description: 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.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 143-156
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight-determined characteristics of an air intake system on an F-111A airplane (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flow phenomena of the F-111A air intake system were investigated over a large range of Mach number, altitude, and angle of attack. Boundary-layer variations are shown for the fuselage splitter plate and inlet entrance stations. Inlet performance is shown in terms of pressure recovery, airflow, mass-flow ratio, turbulence factor, distortion factor, and power spectral density. The fuselage boundary layer was found to be not completely removed from the upper portion of the splitter plate at all Mach numbers investigated. Inlet boundary-layer ingestion started at approximately Mach 1.6 near the translating spike and cone. Pressure-recovery distribution at the compressor face showed increasing distortion with increasing angle of attack and increasing Mach number. The time-averaged distortion-factor value approached 1300, which is near the distortion tolerance of the engine at Mach numbers above 2.1.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6679 , H-661
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Subsonic and transonic hinge moment and wing bending/torsion characteristics of .015 scale space shuttle models 49-0 and 67-TS in the Rockwell International trisonic wind tunnel (IA70), volume 3 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N75-13822.
    Keywords: AERODYNAMICS
    Type: NASA-CR-134433 , DMS-DR-2175-VOL-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Subsonic and transonic hinge moment and wing bending/torsion characteristics of .015 scale space shuttle models 49-0 and 67-TS in the Rockwell International trisonic wind tunnel (IA70), volume 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N75-13822.
    Keywords: AERODYNAMICS
    Type: NASA-CR-134432 , DMS-DR-2175-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    High temperature insulation materials for reradiative Thermal Protection Systems (TPS) (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: High temperature insulation materials for use under radiative thermal protection systems of shuttle orbiter vehicle
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-119950 , MDC-E0449
    Format: application/pdf
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  • 6
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    Radiative contribution to the thermal conductivity of fibrous insulations (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An approach is shown for using a simple two-flux model to interpret infrared transmission data for a variety of reuseable surface insulations materials and to calculate the radiation transmission. A description is given of preliminary experiments on mullite and silica-based materials. The calculated parameters are compared with the measured values of the total thermal conductivity, as determined on guarded hot plate equipment. It is pointed out that for many samples the newly developed four-flux model must be utilized because the scattering properties of the fibers are often dependent on the wavelength of the radiation.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Symposium on Heat transmission measurements in thermal insulations; Apr 16, 1973 - Apr 17, 1973; Philadelphia, PA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    The infrared properties of reusable surface insulations. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The total infrared scattering and absorption cross sections of both flexible and rigidized high temperature fibrous insulations have been measured. The methods for accomplishing these measurements are described. Infrared reflection and transmission spectra were obtained to study the dependence of the total cross sections on the spectral characteristics of the transported radiation. These results are applied to steady-state effective thermal conductivity measurements via a four-flux model of radiative heat transfer to separate the radiative component and to calculate the effective thermal conductivity under transient heating conditions. Data for both silica and mullite fibers are presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 73-745 , Thermophysics Conference; Jul 16, 1973 - Jul 18, 1973; Palm Springs, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    High temperature insulation materials for reradiative thermal protection systems (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results are presented of a two year program to evaluate packaged thermal insulations for use under a metallic radiative TPS of a shuttle orbiter vehicle. Evaluations demonstrated their survival for up to 100 mission reuse cycles under shuttle acoustic and thermal loads with peak temperatures of 1000 F, 1800 F, 2000 F, 2200 F and 2500 F. The specimens were composed of low density refractory fiber felts, packaged in thin gage metal foils. In addition, studies were conducted on the venting requirements of the packages, salt spray resistance of the metal foils, and the thermal conductivity of many of the insulations as a function of temperature and ambient air pressure. Data is also presented on the radiant energy transport through insulations, and back-scattering coefficients were experimentally determined as a function of source temperature.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-123945 , MDC-E0666
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Subsonic and transonic hinge moment and wing bending/torsion characteristics of .015 scale space shuttle models 49-0 and 67-TS in the Rockwell International trisonic wind tunnel (IA70), volume 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted on an 0.015-scale representation of the integrated space shuttle launch vehicle in the trisonic wind tunnel. The primary test objective was to obtain subsonic and transonic elevon and bodyflap hinge moments and wing bending-torsion moments in the presence of the launch vehicle. Wing pressures were also recorded for the upper and lower right wing surfaces at two spanwise stations. The hinge moment, wing bending/torsion moments and wing pressure data were recorded over an angle-of-attack (alpha) range from -8 deg to +8 deg, and angle-of-sideslip (beta) range from -8 deg to +8 deg and at Mach numbers of 0.90, 1.12, 1.24 and 1.50. Tests were also conducted to determine the effects of the orbiter rear attach cross beam and the forward attach wedge and strut diameter. The orbiter alone was tested at 0.90 and 1.24 Mach number only.
    Keywords: AERODYNAMICS
    Type: NASA-CR-134431 , DMS-DR-2175-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Pressures and temperatures on the lower surfaces of an externally blown flap system during full-scale ground tests (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: 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 levels and engine/wing positions. The test were made with no airflow over the wing. The wing sweep angle was fixed at e6 deg; and the angle of incidence between the engine and the wing was fixed at 3 deg; and the flap was in the retracted, deflected 35 deg, and deflected 60 deg positions. The pressure load obtained by integrating the local pressures on the undersurface of the flap, F sub p was approximately three times greater at the 60 deg flap position than at the 35 deg flap position. At the 60 deg flap position, F sub p was between 40 percent and 55 percent of the engine thrust over the measured range of thrust. More than 90 percent of F sub p was contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline with both nozzle configurations. Maximum temperatures recorded on the flaps were 218 C (424 F) and 180 C (356 F) for the conical and daisy nozzles, repectively,
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7138 , H-729
    Format: application/pdf
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