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  • AERODYNAMICS  (43)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (38)
  • 2020-2024
  • 1975-1979  (81)
  • 1945-1949
  • 1975  (81)
  • 1
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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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    NASA TECHNICAL REPORTS
  • 2
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    A Three-Dimensional Solution of Flows over Wings with Leading-Edge Vortex Separation. Part 1: Engineering Document (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method of predicting forces, moments, and detailed surface pressures on thin, sharp-edged wings with leading-edge vortex separation in incompressible flow is presented. The method employs an inviscid flow model in which the wing and the rolled-up vortex sheets are represented by piecewise, continuous quadratic doublet sheet distributions. The Kutta condition is imposed on all wing edges. Computed results are compared with experimental data and with the predictions of the leading-edge suction analogy for a selected number of wing planforms over a wide range of angle of attack. These comparisons show the method to be very promising, capable of producing not only force predictions, but also accurate predictions of detailed surface pressure distributions, loads, and moments.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132709 , D6-41789-PT-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Cold-air experimental investigation of a turbine with blade trailing edge coolant ejection. 1: Single-stage turbine (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were made on a 0.762-meter-tip-diameter research turbine to determine the effect of blade coolant flow on its aerodynamic performance. Both stator and rotor blades had trailing-edge slots for coolant ejection. The turbine was tested over a range of speed and pressure ratio. High primary efficiencies, calculated on the basis of primary air only, were obtained. The efficiency attained was identical to that reported for the turbine from a previous investigation were only slotted stator blades where incorporated in the turbine and tested. And it also compares with results for the turbine with solid blading. Independently varying the rotor coolant flow showed that rotor cooling imposed a severe penalty on turbine efficiency. The thermodynamic efficiency, which accounts for the ideal energies of both blade coolant flows, decreased linearly with rotor coolant at a rate of about 0.7 percent per percent rotor coolant fraction.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3214 , E8158
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Simulation verification techniques study: Simulation performance validation techniques document (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques and support software for the efficient performance of simulation validation are discussed. Overall validation software structure, the performance of validation at various levels of simulation integration, guidelines for check case formulation, methods for real time acquisition and formatting of data from an all up operational simulator, and methods and criteria for comparison and evaluation of simulation data are included. Vehicle subsystems modules, module integration, special test requirements, and reference data formats are also described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-150933 , MDC-E1136
    Format: application/pdf
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  • 5
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    SENS-5D trajectory and wind-sensitivity calculations for unguided rockets (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computational procedure is described which numerically integrates the equations of motion of an unguided rocket. Three translational and two angular (roll discarded) degrees of freedom are integrated through the final burnout; and then, through impact, only three translational motions are considered. Input to the routine is: initial time, altitude and velocity, vehicle characteristics, and other defined options. Input format has a wide range of flexibility for special calculations. Output is geared mainly to the wind-weighting procedure, and includes summary of trajectory at burnout, apogee and impact, summary of spent-stage trajectories, detailed position and vehicle data, unit-wind effects for head, tail and cross winds, coriolis deflections, range derivative, and the sensitivity curves (the so called F(Z) and DF(Z) curves). The numerical integration procedure is a fourth-order, modified Adams-Bashforth Predictor-Corrector method. This method is supplemented by a fourth-order Runge-Kutta method to start the integration at t=0 and whenever error criteria demand a change in step size.
    Keywords: AERODYNAMICS
    Type: NASA-CR-141402
    Format: application/pdf
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  • 6
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    Effects of upper-surface blowing and thrust vectoring on low-speed aerodynamic characteristics of a large-scale supersonic transport model (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in the Langley full-scale tunnel to determine the low-speed aerodynamic characteristics of a large-scale arrow-wing supersonic transport configured with engines mounted above the wing for upper surface blowing, and conventional lower surface engines with provisions for thrust vectoring. A limited number of tests were conducted for the upper surface engine configuration in the high lift condition for beta = 10 in order to evaluate lateral directional characteristics, and with the right engine inoperative to evaluate the engine out condition.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72792
    Format: application/pdf
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  • 7
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    A three-dimensional solution of flows over wings with leading-edge vortex separation (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The application of a new, general, potential flow computational technique to the solution of the subsonic, three-dimensional flow over wings with leading-edge vortex separation is presented. The present method is capable of predicting forces, moments, and detailed surface pressures on thin, sharp-edged wings of rather arbitrary planform. The wing geometry is arbitrary in the sense that leading and trailing edges may be curved or kinked and the wing may have arbitrary camber and twist. The method employs an inviscid flow model in which the wing, the rolled-up vortex sheets, and the wake are represented by piecewise continuous quadratic doublet sheet distributions. The Kutta condition is imposed along all wing edges. Strengths of the doublet distributions as well as shape and position of the free fortex sheet spirals are computed in iterative fashion starting with an assumed initial sheet geometry. The method is verified by numerous computed results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-866 , American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference; Jun 16, 1975 - Jun 18, 1975; Hartford, CT
    Format: text
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  • 8
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    Attitude control requirements for an earth-orbital solar electric propulsion stage (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Solar Electric Propulsion Stage (SEPS) application in earth orbit requires considerably more maneuvering for thrust vector steering and solar array pointing than planetary missions. Attitude maneuver requirements for geosynchronous and low earth-orbital missions are presented. Situations which result in optimum steering torque requirements exceeding the capability of current SEPS configurations are defined. Sub-optimal steering techniques are defined which reduce the geosynchronous mission torque requirements to acceptable levels with negligible performance penalties. Some low earth-orbital flight regimes with earth shadowing are found to result in much larger torque requirements and impose significant mechanization penalties if serious performance losses are to be avoided. Alternative attitude control mechanization techniques are defined for these cases.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-353 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Mar 19, 1975 - Mar 21, 1975; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A potential flow model for calculation of jet noise (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The development of the large-scale eddy structure of a circular jet is calculated from a potential flow model which includes the vorticity distribution. The model exhibits all the observed general features of high Reynolds number jet flows although it is constrained to remain axisymmetric. The far acoustic field is calculated from the predicted unsteady vorticity distribution.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-441 , American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference; Mar 24, 1975 - Mar 26, 1975; Hampton, VA
    Format: text
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  • 10
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    Bringing wings of change - NASA's airfoil research program (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A review is presented of progress in attaining technical objectives in three areas of semiautomatic airfoil development: software, hardware, and applications. Software objectives seek improved mathematical models and computer codes for flow analysis and design optimization for a variety of conditions. The 17-step iterative computer model used in designing the GA (W)-1 airfoil is effective but not yet fully automated; with present methods only single-point computer optimization is possible. Hardware objectives calling for improvement in test facilities and techniques are met in part by the introduction of the Langley (F-3C) wind tunnel for independent evaluation of transonic Mach number and Reynolds effects up to 12-16 million, and by a two-dimensional test section for the Langley 1/3 transonic cryogenic tunnel which will extend the Reynolds number to 50 million. The current status of low-speed, thin, and rotorcraft airfoil development programs is discussed.
    Keywords: AERODYNAMICS
    Type: Astronautics and Aeronautics; 13; Oct. 197
    Format: text
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