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  • AERODYNAMICS
  • 1970-1974  (1,256)
  • 1
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    An experimental investigation of base heating on typical Mars entry body shapes. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hypersonic experiments on wire supported high angle blunt cones were conducted to determine the base heating characteristics. Heating distributions were obtained for several base configurations with variations in free stream Reynolds Number and gas composition. The dependence of the heating in the base region on angle of attack was also investigated. It was found that gas composition effects can be accounted for by comparison at equal Reynolds Number. Angle of attack effects can result in either increasing or decreasing base heating depending upon the location in the base region.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 72-317 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Wind tunnel tests of a wing installed model VTOL lift fan with coaxial drive turbine (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Cross flow wind tunnel performance tests of 15 in. wing installed lift fan with coaxial drive turbine for VTOL transport aircraft
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-67854 , E-6359
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Steady inviscid transonic flows over planar airfoils: A search for a simplified procedure (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A finite difference procedure based upon a system of unsteady equations in proper conservation form with either exact or small disturbance steady terms is used to calculate the steady flows over several classes of airfoils. The airfoil condition is fulfilled on a slab whose upstream extremity is a semi-circle overlaying the airfoil leading edge circle. The limitations of the small disturbance equations are demonstrated in an extreme example of a blunt-nosed, aft-cambered airfoil. The necessity of using the equations in proper conservation form to capture the shock properly is stressed. Ability of the steady relaxation procedures to capture the shock is briefly examined.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2186
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Downwash-velocity potential method for oscillating surfaces. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The application of the downwash-velocity potential method to the case of oscillating surfaces is developed, and calculated forces are given on rectangular airfoils of aspect ratio two rotating about midchord in subsonic flows. These are compared with other results published in the literature for reduced frequencies up to nine-tenths, and for Mach numbers up to nine-tenths. The concept of 'aerodynamic elements' is presented, the computed results representing three possible types of rectangular element.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; May 1973
    Format: text
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  • 5
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    Flutter and unsteady lift theory (1971)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: Aeroelasticity and unsteady flow problems of aircraft
    Keywords: AERODYNAMICS
    Type: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 289-374
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    User's Manual for Computer Program ROTOR (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed description of a computer program to calculate tilt-rotor aircraft dynamic characteristics is presented. This program consists of two parts: (1) the natural frequencies and corresponding mode shapes of the rotor blade and wing are developed from structural data (mass distribution and stiffness distribution); and (2) the frequency response (to gust and blade pitch control inputs) and eigenvalues of the tilt-rotor dynamic system, based on the natural frequencies and mode shapes, are derived. Sample problems are included to assist the user.
    Keywords: AERODYNAMICS
    Type: NASA-CR-137553 , ASRL-TR-174-2
    Format: application/pdf
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  • 7
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    Inverse problem approach to the design of short two-dimensional diffusers. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: ASME PAPER 72-WA/GT-6 , Winter Annual Meeting of the American Society of Mechanical Engineers; Nov 26, 1972 - Nov 30, 1972; New York, NY
    Format: text
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  • 8
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    The design and performance of axially symmetrical contoured wall diffusers employing suction boundary layer control (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a procedure for the design and the performance prediction of axially symmetrical contoured wall diffusers employing suction boundary layer control. An inverse problem approach was used in the potential flow design of the diffuser wall contours. The experimentally observed flow characteristics and the stability of flows within the diffuser are also described. Guidelines for the design of low suction (less than 10 percent of the inlet flow) and thus high effectiveness contoured wall diffusers are also provided based on the results of the experimental program.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 74-GT-152 , Gas Turbine Conference and Products Show; Mar 30, 1974 - Apr 04, 1974; Zurich; Switzerland
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental investigation of circular, flat, grooved and plain steel diaphragms bursting into a 30.5-centimeter-square section (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Limited data on the bursting of circular, initially flat, grooved and plain steel diaphragms opening into a 30.5-cm-square section are presented in tabular form. In addition, these data were used to determine values of an empirical constant to be used in a design equation for predicting diaphragm bursting pressures and opening times.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2549 , L-4645
    Format: application/pdf
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  • 10
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    Unsteady transonic flow analysis for low aspect ratio, pointed wings. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Oswatitsch and Keune's parabolic method for steady transonic flow is applied and extended to thin slender wings oscillating in the sonic flow field. The parabolic constant for the wing was determined from the equivalent body of revolution. Laplace transform methods were used to derive the asymptotic equations for pressure coefficient, and the Adams-Sears iterative procedure was employed to solve the equations. A computer program was developed to find the pressure distributions, generalized force coefficients, and stability derivatives for delta, convex, and concave wing planforms.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 73-122 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
    Format: text
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