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  • 1
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    A closed-form solution to oblique shock-wave properties. (1969)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Oblique shock wave properties with free stream Mach number and flow deflection angle as independent variables, noting explicit solution
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Assessment of the effects of inlet spillage, bypass, and bleed air on the performance of supersonic cruise airplanes (1966)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Aircraft Aerodynamics; p 139-155
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Charts of additive drag coefficient and mass-flow ratio for inlets utilizing right circular cones at zero angle of attack (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Charts of additive drag coefficient and mass flow ratio for inlets utilizing right circular cones at zero angle of attack
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3434
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A preliminary study of the performance and characteristics of a supersonic executive aircraft (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The impact of advanced supersonic technologies on the performance and characteristics of a supersonic executive aircraft was studied in four configurations with different engine locations and wing/body blending and an advanced nonafterburning turbojet or variable cycle engine. An M 2.2 design Douglas scaled arrow-wing was used with Learjet 35 accommodations. All four configurations with turbojet engines meet the performance goals of 5926 km (3200 n.mi.) range, 1981 meters (6500 feet) takeoff field length, and 77 meters per second (150 knots) approach speed. The noise levels of of turbojet configurations studied are excessive. However, a turbojet with mechanical suppressor was not studied. The variable cycle engine configuration is deficient in range by 555 km (300 n.mi) but nearly meets subsonic noise rules (FAR 36 1977 edition), if coannular noise relief is assumed. All configurations are in the 33566 to 36287 kg (74,000 to 80,000 lbm) takeoff gross weight class when incorporating current titanium manufacturing technology.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-74055
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A rapid numerical solution to subsonic flow over planar and axisymmetric profiles at an angle of attack of 0 deg (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A numerical solution is presented for the incompressible flow over thin planar and axisymmetric profiles at an angle of attack of 0 degrees. The method uses a finite-difference field solution to the governing equation with a Gauss-Seidel successive overrelaxation scheme. However, the use of a simple Cartesian grid system restricts this method to slender profiles. Results are presented for a cambered airfoil, airfoil in wall effect (two-dimensional flowthrough inlet), body of revolution, and flowthrough nacelle. A computer program is presented which can be used for any of the previously mentioned cases with simple input changes. Results for compressible flow are available with the use of the appropriate two-dimensional or axisymmetric compressibility corrections. Computational time for a typical field calculation of 3000 grid points and 200 cycles through the field is less than 1 minute with less than 50,000 octal storage on the Control Data Corporation 6600 computing system.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7410 , L-8904
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Calculation of linearized supersonic flow over slender cones of arbitrary cross section (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Supersonic linearized conical-flow theory is used to determine the flow over slender pointed cones having horizontal and vertical planes of symmetry. The geometry of the cone cross sections and surface velocities are expanded in Fourier series. The symmetry condition permits the uncoupling of lifting and nonlifting solutions. The present method reduces to Ward's theory for flow over a cone of elliptic cross section. Results are also presented for other shapes. Results by this method diverge for cross-sectional shapes where the maximum thickness is large compared with the minimum thickness. However, even for these slender-body shapes, lower order solutions are good approximations to the complete solution.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6818 , L-8192
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Aerodynamic Performance Studies for Supersonic Cruise Aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technical progress made in each of the disciplinary research areas affecting the design of supersonic cruise aircraft is discussed. The NASA Supersonic Cruise Aircraft Research program has supported an expanded research program in aerodynamics including an ever growing experimental data base, methodology development across the Mach number range, and sonic boom. Progress in the aerodynamics area could facilitate the choice of the highly swept subsonic leading edge, arrow wing, known for superior supersonic cruise efficiency.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-73915
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Systems integration studies for supersonic cruise aircraft (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technical progress in each of the disciplinary research areas affecting the design of supersonic cruise aircraft is discussed. The NASA AST/SCAR Program supported the integration of these technical advances into supersonic cruise aircraft configuration concepts. While the baseline concepts reflect differing design philosophy, all reflect a level of economic performance considerably above the current foreign aircraft as well as the former U.S. SST. Range-payload characteristics of the study configurating show significant improvement, while meeting environmental goals such as takeoff and landing noise and upper atmospheric pollution.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-72781
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Noise and performance calibration study of a Mach 2.2 supersonic cruise aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The baseline configuration of a Mach 2.2 supersonic cruise concept employing a 1980 - 1985 technology level, dry turbojet, mechanically suppressed engine, was calibrated to identify differences in noise levels and performance as determined by the methodology and ground rules used. In addition, economic and noise information is provided consistent with a previous study based on an advanced technology Mach 2.7 configuration, reported separately. Results indicate that the difference between NASA and manufacturer performance methodology is small. Resizing the aircraft to NASA groundrules results in negligible changes in takeoff noise levels (less than 1 EPNdB) but approach noise is reduced by 5.3 EPNdB as a result of increasing approach speed. For the power setting chosen, engine oversizing resulted in no reduction in traded noise. In terms of summated noise level, a 6 EPNdB reduction is realized for a 5% increase in total operating costs.
    Keywords: ACOUSTICS
    Type: NASA-TM-80043
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Preliminary noise tradeoff study of a Mach 2.7 cruise aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: NASA computer codes in the areas of preliminary sizing and enroute performance, takeoff and landing performance, aircraft noise prediction, and economics were used in a preliminary noise tradeoff study for a Mach 2.7 design supersonic cruise concept. Aerodynamic configuration data were based on wind-tunnel model tests and related analyses. Aircraft structural characteristics and weight were based on advanced structural design methodologies, assuming conventional titanium technology. The most advanced noise prediction techniques available were used, and aircraft operating costs were estimated using accepted industry methods. The 4-engines cycles included in the study were based on assumed 1985 technology levels. Propulsion data was provided by aircraft manufacturers. Additional empirical data is needed to define both noise reduction features and other operating characteristics of all engine cycles under study. Data on VCE design parameters, coannular nozzle inverted flow noise reduction and advanced mechanical suppressors are urgently needed to reduce the present uncertainties in studies of this type.
    Keywords: ACOUSTICS
    Type: NASA-TM-78732
    Format: application/pdf
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