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  • AERODYNAMICS  (262)
  • INSTRUMENTATION AND PHOTOGRAPHY  (148)
  • 2020-2024
  • 1975-1979  (399)
  • 1955-1959  (11)
  • 1
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    Measurements on the development of cascades in a tungsten-scintillator ionization spectrometer (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The response of a tungsten-scintillator ionization spectrometer to accelerated particle beams has been investigated. Results obtained from exposure of the approx. 1000 g/sq cm apparatus to 5, 10, and 15 GeV/c electrons and pions as well as to 2.1 GeV/nucleon C-12 and O-16 ions are presented. These results include cascade-development curves, fractions of the primary energy measured by the spectrometer, and resolutions of the apparatus for measuring the primary energies. For 15 GeV/c electrons, an average of about 82% of the incident energy is measured by the apparatus with resolution (normal standard deviation) of about 6%. For 15 GeV/c pions, an average of about 65% of the incident energy is measured with resolution of about 18%. The energy resolution improves with increasing energy and with increasing depth of the spectrometer.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 126; 1975
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Correction factory techniques for improving aerodynamic prediction methods (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method for correcting discrete element lifting surface theory to reflect given experimental data is presented. Theoretical pressures are modified such that imposed constraints are satisfied while minimizing the changes to the pressures. Several types of correction procedures are presented and correlated; (1) scaling of pressures; (2) scaling of downwash values; and (3) addition of an increment to the downwash that is proportioned to pressure. Some special features are included in these methods and they include: (1) consideration of experimental data from multiple deflection modes, (2) limitation of the amplitudes of the correction factors, and (3) the use of correction factor mode shapes. These methods are correlated for cases involving all three Mach Number ranges using a FORTRAN IV computer program. Subsonically, a wing with an oscillating partial span control surface and a wing with a leading edge droop are presented. Transonically a two-dimensional airfoil with an oscillating flap is considered. Supersonically an arrow wing with and without camber is analyzed. In addition to correction factor methods an investigation is presented dealing with a new simplified transonic modification of the two-dimensional subsonic lifting surface theory. Correlations are presented for an airfoil with an oscillating flap.
    Keywords: AERODYNAMICS
    Type: NASA-CR-144967
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Low-speed wind tunnel investigation of an advanced supersonic cruise arrow-wing configuration (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary assessment of possible means for improving the low speed aerodynamic characteristics of advanced supersonic cruise arrow wing configurations and to extend the existing data base of such configurations has been made. Principle configuration variables included wing-leading and trailing-edge flap deflection, fuselage nose strakes, and engine exhaust nozzle deflection. Results showed that deflecting the wing leading edge apex flaps downward provided improved longitudinal stability but resulted in reduced directional stability. The model exhibited relatively low values of directional stability over the operational angle of attack range and experienced large asymmetric yawing moments at high angles of attack. The use of nose strakes was found to be effective in increasing the directional stability and eliminating the asymmetric yawing moment.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74043
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Spark calorimeter: An instrument for determining particle energy of cosmic radiation (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: In 1964 a spark calorimeter was installed at the NOR-Amberd Station (2000 m above sea level). The advantages of this calorimeter over the ionization calorimeter are illustrated.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 349-354
    Format: text
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  • 5
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    The Apollo 15 and 16 X-ray fluorescence experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An X-ray fluorescence spectrometer was flown aboard the Apollo 15 and 16 spacecrafts orbiting the moon. The X-ray instrument was used to produce a chemical map of that portion of the moon covered by the projected ground tracks and illuminated by the sun during the period of flight. The instrument includes three thin windowed proportional counters, two of which have selected X-ray filters. The field of view of the surface is determined by a collimator, while a detector on the opposite side of the spacecraft provides a continuous monitoring of the solar X-ray output. While the number of chemical elements determined was limited to Mg, Al, and Si, these proved to be very important diagnostic elements.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Space Science Instrumentation; 1; Aug. 197
    Format: text
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  • 6
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    Distributed upper-surface blowing concept (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A low speed investigation was conducted in the Langley V/STOL tunnel to determine the powered lift aerodynamic performance of a distributed upper surface blown propulsive lift transport model. The model used blowing slots across the span of the wing to produce a thin jet efflux near the leading edge and at the knee of the trailing edge flap (internally blown jet flap). Results indicate that these concepts have both good propulsive related lift and low drag due to lift characteristics because of uniform spanwise propulsive thrust. The leading edge blowing concept provides low speed lift characteristics which are competitive with the flap-hinge-line blowing concept and does not require additional leading edge treatment for prevention of abrupt stall.
    Keywords: AERODYNAMICS
    Type: Powered-Lift Aerodyn. and Acoustics; p 159-164
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    NASA TECHNICAL REPORTS
  • 7
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    Application of powered-lift concepts for improved cruise efficiency of long-range aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of studies conducted to explore the use of powered lift concepts for improved low speed performance of long range subsonic and supersonic cruise vehicles are summarized. It is indicated that powered lift can provide significant improvements in low speed performance, as well as substantial increases in cruise efficiency and range for both subsonic and supersonic cruise configurations.
    Keywords: AERODYNAMICS
    Type: Powered-Lift Aerodyn. and Acoustics; p 89-101
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    NASA TECHNICAL REPORTS
  • 8
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    Comparison of aerodynamic theory and experiment for jet-flap wings (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Aerodynamic theory predictions made for a jet flapped wing were compared with experimental data obtained in a fairly extensive series of tests in the Langley V/STOL tunnel. The tests were made on a straight, rectangular wing and investigated two types of jet flap concepts: a pure jet flap with high jet deflection and a wing with blowing at the knee of a plain trailing edge flap. The tests investigated full and partial span blowing for wing aspect ratios of 8.0 and 5.5 and momentum coefficients from 0 to about 4. The total lift, drag, and pitching moment coefficients predicted by the theory were in excellent agreement with experimental values for the pure jet flap, even with the high jet deflection. The pressure coefficients on the wing, and hence the circulation lift coefficients, were underpredicted, however, because of the linearizing assumptions of the planar theory. The lift, drag, and pitching moment coefficients, as well as pressure coefficients, were underpredicted for the wing with blowing over the flap because of the failure of the theory to account for the interaction effect of the high velocity jet passing over the flap.
    Keywords: AERODYNAMICS
    Type: Powered-Lift Aerodyn. and Acoustics; p 103-118
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    NASA TECHNICAL REPORTS
  • 9
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    Effects of fuselage forebody geometry on low-speed lateral-directional characteristics of twin-tail fighter model at high angles of attack (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Low-speed, static wind-tunnel tests were conducted to explore the effects of fighter fuselage forebody geometry on lateral-directional characteristics at high angles of attack and to provide data for general design procedures. Effects of eight different forebody configurations and several add-on devices (e.g., nose strakes, boundary-layer trip wires, and nose booms) were investigated. Tests showed that forebody design features such as fineness ratio, cross-sectional shape, and add-on devices can have a significant influence on both lateral-directional and longitudinal aerodynamic stability. Several of the forebodies produced both lateral-directional symmetry and strong favorable changes in lateral-directional stability. However, the same results also indicated that such forebody designs can produce significant reductions in longitudinal stability near maximum lift and can significantly change the influence of other configuration variables. The addition of devices to highly tailored forebody designs also can significantly degrade the stability improvements provided by the clean forebody.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1592 , L-13270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Effects of wing leading-edge deflection on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wing leading-edge deflection effects on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration were determined. Static force tests were conducted in a V/STOL tunnel at a Reynolds number of about 2.5 x 1 million for an angle-of-attack range from -10 deg to 17 deg and an angle-of-sideslip range from -5 deg to 5 deg. Limited flow visualization studies were also conducted in order to provide a qualitative assessment of leading-edge upwash characteristics.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78787
    Format: application/pdf
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