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  • 1
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    A review of preflight estimates of real-gas effects on space shuttle aerodynamic characteristics (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Preflight estimates of the hypersonic aerodynamic characteristics of the Shuttle orbiter were based on a diverse series of research studies using state of the art techniques developed by basic research in the 60's and 70's. Real-gas viscous calculations on simple shapes that were used to evaluate correlation parameters indicated that real-gas effects reduce aerodynamic forces and moments. Inviscid calculations on winged lifting shapes indicated reduced forces and a slight nose-up pitch resulted because of real-gas effects. Analysis of the extensive wind tunnel data base indicated viscous correlation parameters provided the most appropriate extrapolation technique for estimating flight aerodynamics. Variations because of changes in the ratio of specific heats, which was the only available experimental tool for evaluating real-gas effects, indicated that reduced loads and nose-up pitching moments would occur at high altitudes and Mach numbers but that the values would not exceed the tolerances and variations established about the aerodynamic design data book values derived from viscous correlations. During STS-1, nose-up pitching moments exceeded the established variations.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Part 1; p 309-346
    Format: text
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  • 2
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    Hypersonic aerodynamics and entry-maneuver: Aerothermodynamic interactions for two lifting entry vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The longitudinal, directional, and lateral static stability and control characteristics of a delta lifting body and a delta-wing body were obtained at a Mach number of 20 in helium for operational Reynolds numbers over an angle-of-attack range of -4 deg to 55 deg. The aerodynamic characteristics of the wing body were then evaluated in an entry study to examine the effects of vehicle performance on the aerothermodynamic parameters associated with constant and variable angle-of-attack modes for a 1500-n. mi. cross range. The experimental results indicated that the vehicles were stable, except for neutral directional stability for the wing-body shape, and could be trimmed over the operational angle-of-attack range; however, the wing-body vehicle had adverse yaw due to roll control. This roll-yaw coupling was not examined for the lifting body. The trajectory analysis indicated that a 17-percent decrease in performance required little change in the constant angle-of-attack entry mode and, in turn, resulted in a small decrease in the total heat load. For the pitch-modulated entry, the performance decrease required the pitch maneuver to begin earlier during entry and to last longer in order to meet the 1500-n. mi. cross range without a major heating penalty. The performance reduction also had little effect on the maximum laminar radiation equilibrium temperature over a major portion of the lower surface of the wing-body vehicle regardless of the entry mode.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-6753 , L-8072
    Format: application/pdf
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  • 3
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    Electron-beam flow visualization - Applications in the definition of configuration aerothermal characteristics. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Comparisons between flow visualization systems using electron-beam fluorescence, schlieren, and shadowgraph techniques illustrate the advantages associated with the electron beam. Specific applications of this method as an aid in defining the origin of erosion on a heat-transfer model are cited. Results of combined electron-beam oil-flow studies on configurations illustrate that the simultaneous definition of the external flow field and its surface flow can be obtained. Comparisons between the electron-beam oil-flow visualization method and phase-change coating heat-transfer tests on a shuttle ascent configuration indicate the complementary nature of these two testing techniques. Potential methods for improving the electron-beam technique are included.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 72-1016 , American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference; Sept. 13-15, 1972; Palo Alto, CA
    Format: text
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  • 4
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    Recent studies of factors affecting high lift- drag ratios at M equals 19 in helium. (1967)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic performance characteristics of three entry vehicles designed for maximum L/D ratio of three and two at Mach 19 and Reynolds number 3,200,000 tested in 22-inch Langley helium tunnel
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 67-138
    Format: text
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  • 5
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    Some topics in hypersonic body shaping. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hypersonic body shaping for minimum drag and improved performance from view of flight regimes, discussing implications of pressure laws
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 69-181 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING; Jan 20, 1969 - Jan 22, 1969; NEW YORK, NY
    Format: text
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  • 6
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    Recent studies of factors affecting high lift- drag ratios at Mach 19 in helium. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic performance characteristics of three entry vehicles designed for maximum L/D ratio of three and two at Mach 19 and Reynolds number 3,200,000 tested in 22-inch Langley helium tunnel
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 67-138 , AEROSPACE SCIENCES MEETING; Jan 23, 1967 - Jan 26, 1967; NEW YORK, NY
    Format: text
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  • 7
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    A study of density measurements in hypersonic helium tunnels using an electron beam fluorescence technique (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A series of experiments have been conducted at Langley Research Center to determine the feasibility of using electron-beam fluorescence to measure the free-stream static density of gaseous helium flow over a wide range of conditions. These experiments were conducted in the Langley hypersonic helium tunnel facility and its 3-inch prototype. Measurements were made for a range of stagnation pressures and temperatures and produced free-stream number densities of 1.53 x 10 to the 23rd to 1.25 x 10 to the 24th molecules/cu m and static temperatures from 2 K to 80 K. The results showed the collision quenching cross section to be 4.4 x 10 to the -15th sq cm at 1 K and to have a weak temperature dependence of T to the 1/6. With knowledge of these two values, the free-stream number density can be measured quite accurately.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 79-1085 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; Jun 04, 1979 - Jun 06, 1979; Orlando, FL
    Format: text
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  • 8
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    Investigation of real-gas and viscous effects on the aerodynamic characteristics of a 40 deg half-cone with suggested correlations for the shuttle orbiter (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Parameters were evaluated that might be used to correlate shuttle orbiter aerodynamic data to be used in extrapolating from wind-tunnel to flight conditions. Preliminary calculations indicate that the lee-side forces will have an insignificant influence on the aerodynamic characteristics of the orbiter for moderate angle-of-attack entries; therefore, this work is focused on phenomena which have an overriding influence on windward forces, namely, real-gas (equilibrium and nonequilibrium) and viscous-interaction effects. Analytically determined flow fields previously obtained on 40 deg blunted cones were used as a data source to evaluate various correlation parameters. Inviscid effects were found to be the dominant contributor to the aerodynamic coefficients in the altitude range of 64 to 76.2 km. The most suitable correlation of the aerodynamic forces on these cones is based on local dynamic pressure and local Mach number.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8418 , L-10807
    Format: application/pdf
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  • 9
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    Hyper-X Stage Separation Wind Tunnel Test Program (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA's Hyper-X research program was developed primarily to flight demonstrate a supersonic combustion ramjet engine, fully integrated with a forebody designed to tailor inlet flow conditions and a free expansion nozzle/afterbody to produce positive thrust at design flight conditions. With a point-designed propulsion system, the vehicle must depend upon some other means for boost to its design flight condition. Clean separation from this initial propulsion system stage within less than a second is critical to the success of the flight. This paper discusses the early planning activity, background, and chronology that developed the series of wind tunnel tests to support multi degree of freedom simulation of the separation process. Representative results from each series of tests are presented and issues and concerns during the process and current status will be highlighted.
    Keywords: Aerodynamics
    Type: AIAA Paper 2000-4008 , 18th Applied Aerodynamics Conference; Aug 14, 2000 - Aug 17, 2000; Denver, CO; United States
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  • 10
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    Air/helium ground-test simulation pertinent to the definition of slender body hypersonic aerodynamics (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The capability of air/helium simulations pertinent to the definition of slender body hypersonic aerodynamics is tested, using exact inviscid analytical comparisons to characterize the Mach number and bluntness effects. Comparisons are made with experiments conducted from the 1960s through the 1980s. The results indicate no general rule for air/helium simulation. A feasibility for obtaining sufficient simulation for many types of aero/fluid dynamic studies is demonstrated.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0318 , ; 16 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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