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  • AERODYNAMICS  (462)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE
  • 2020-2024
  • 1990-1994  (323)
  • 1975-1979  (381)
  • 1
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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
  • 2
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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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  • 3
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    Leading-edge transition and relaminarization phenomena on a subsonic high-lift system (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Boundary-layer transition and relaminarization may have a critical effect on the flow development about multielement high-lift systems of subsonic transport aircraft with swept wings. The purpose of this paper is a study of transition phenomena in the leading-edge region of the various elements of a high-lift system. The flow phenomena studied include transition of the attachment-line flow, relaminarization, and crossflow instability. The calculations are based on pressure distributions measured in flight on the NASA Transport Systems Research Vehicle (Boeing 737-100) at a wing station where the flow approximated infinite swept wing conditions. The results indicate that significant regions of laminar flow can exist on all flap elements in flight. In future flight experiments the extent of these regions will be measured, and the transition mechanisms and the effect of laminar flow on the high-lift characteristics of the multi-element system will be further explored.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3140 , ; 15 p.|AIAA, Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
    Format: text
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  • 4
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    A spacecraft charging study on the SCEX 3 rocket (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Instruments on the SCEX 3 rocket payload were used to study charging during electron beam emissions. The data show that electrostatic analyzers can be used to measure vehicle charging and direct beam return currents in dense plasma conditions. The data also show return current dependencies on pitch angle, beam current and beam energy. It is found that if the proper care is taken, ESAs can be used to detect charging on vehicles in low altitude orbits which are contaminated with high levels of outgassing and in dense plasma regimes. These results are particularly important for the TSS-1 electrodynamic tether program where ESAs are being used to determine Shuttle charging levels during tether employment and to look for high fluxes of directly returning electrons during electron generator operations to balance the Shuttle charging.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Nuclear Science (ISSN 0018-9499); 38; 1622-162
    Format: text
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  • 5
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    Skin friction and velocity profile family for compressible turbulent boundary layers (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The paper presents a general approach to constructing mean velocity profiles for compressible turbulent boundary layers with isothermal or adiabatic walls. The theory is based on a density-weighted transformation that allows the extension of the incompressible similarity laws of the wall to the compressible regions. The velocity profile family is compared to a range of experimental data, and excellent agreement is obtained. A self-consistent skin friction law, which satisfies the proposed velocity profile family, is derived and compared with the well-known Van Driest II theory for boundary layers in zero pressure gradient. The results are found to be at least as good as those obtained by using the Van Driest II transformation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 9; p. 1600-1604.
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  • 6
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    Spacecraft charging - Progress in the study of dielectrics and plasmas (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The progress in spacecraft charging is reviewed with particular attention given to the interactions of plasma and penetrating radiation with dielectrics. Topics discussed include the charging environments, elementary charging theory, the anomalies attributed to charging or discharging phenomena, and spacecraft engineering.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Electrical Insulation (ISSN 0018-9367); 27; 5; p. 944-960.
    Format: text
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  • 7
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    Derivation of particulate directional information from analysis of elliptical impact craters on LDEF (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Long Duration Exposure Facility provided a gravity gradient stabilized platform which allowed limited directional information to be derived from particle impact experiments. The morphology of impact craters on semi-infinite materials contains information which may be used to determine the direction of impact much more accurately. We demonstrate the applicability of this technique and present preliminary results of measurements from LDEF and modelling of interplanetary dust and space debris.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center, LDEF: 69 Months in Space. Second Post-Retrieval Symposium, Part 2; p 417-429
    Format: application/pdf
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  • 8
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    ATS-6 - Flight performance of the Advanced Thermal Control Flight Experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Advanced Thermal Control Flight Experiment on ATS-6 was designed to demonstrate the thermal control capability of a thermal diode (one-way) heat pipe, a phase-change material for thermal storage, and a feedback-controlled heat pipe. Flight data for the different operational modes are compared to ground test data, and the performance of the components is evaluated on an individual basis and as an integrated temperature-control system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
    Format: text
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  • 9
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    Origin of the Shuttle glow (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: On a recent Shuttle mission four gases, NO, CO2, Xe, and Ne were released for a plasma experiment. Unintentionally, enough gas was scattered onto the surfaces of the Shuttle tail that when NO was released a much more intense version of Shuttle glow was observed. The other gases did not affect the normal Shuttle glow. Under normal conditions the adsorbed NO that causes the glow probably come either from the ambient atmosphere or from reactions in exhaust gases from the Shuttle thrusters.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Nature (ISSN 0028-0836); 354; 48-50
    Format: text
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  • 10
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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
    Format: application/pdf
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