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| Author | : Frank W. Spaid |
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| Total Pages | : 116 |
| Release | : 1995 |
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| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 116 |
| Release | : 2018-07-17 |
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| ISBN | : 9781723048968 |
This study was conducted to experimentally characterize the flow field created by the interaction of a single-expansion ramp-nozzle (SERN) flow with a hypersonic external stream. Data were obtained from a generic nozzle/afterbody model in the 3.5 Foot Hypersonic Wind Tunnel at the NASA Ames Research Center, in a cooperative experimental program involving Ames and McDonnell Douglas Aerospace. The model design and test planning were performed in close cooperation with members of the Ames computational fluid dynamics (CFD) team for the National Aerospace Plane (NASP) program. This paper presents experimental results consisting of oil-flow and shadow graph flow-visualization photographs, afterbody surface-pressure distributions, rake boundary-layer measurements, Preston-tube skin-friction measurements, and flow field surveys with five-hole and thermocouple probes. The probe data consist of impact pressure, flow direction, and total temperature profiles in the interaction flow field. Spaid, Frank W. and Keener, Earl R. and Hui, Frank C. L. Ames Research Center AFTERBODIES; FLOW DISTRIBUTION; FLOW VISUALIZATION; GAS STREAMS; HYPERSONIC FLOW; NOZZLE FLOW; WIND TUNNEL TESTS; COMPUTATIONAL FLUID DYNAMICS; EXHAUST GASES; NATIONAL AEROSPACE PLANE PROGRAM; PRESSURE DISTRIBUTION; SHADOWGRAPH PHOTOGRAPHY; SKIN FRICTION; TEMPERATURE PROFILES...
| Author | : Frank W. Spaid |
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| Release | : 1992 |
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| Author | : Frank W. Spaid |
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| Release | : 1995 |
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| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 64 |
| Release | : 2018-07-06 |
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| ISBN | : 9781722401399 |
This report summarizes the methods developed for the aerodynamic analysis and the shape optimization of the nozzle-afterbody section of a hypersonic vehicle. Initially, exhaust gases were assumed to be air. Internal-external flows around a single scramjet module were analyzed by solving the three dimensional Navier-Stokes equations. Then, exhaust gases were simulated by a cold mixture of Freon and Argon. Two different models were used to compute these multispecies flows as they mixed with the hypersonic airflow. Surface and off-surface properties were successfully compared with the experimental data. In the second phase of this project, the Aerodynamic Design Optimization with Sensitivity analysis (ADOS) was developed. Pre and post optimization sensitivity coefficients were derived and used in this quasi-analytical method. These coefficients were also used to predict inexpensively the flow field around a changed shape when the flow field of an unchanged shape was given. Starting with totally arbitrary initial afterbody shapes, independent computations were converged to the same optimum shape, which rendered the maximum axial thrust. Baysal, Oktay Unspecified Center...
| Author | : John V. Rakich |
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| Total Pages | : 60 |
| Release | : 1966 |
| Genre | : Aerodynamics, Hypersonic |
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| Author | : William F. Hinson |
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| Total Pages | : 50 |
| Release | : 1970 |
| Genre | : Aerodynamics, Hypersonic |
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| Author | : Vernon Van Hise |
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| Total Pages | : 24 |
| Release | : 1960 |
| Genre | : Aerodynamics |
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A systematic study of induced pressures on a series of bodies of revolution with varying nose bluntness has been made by using the method of characteristics for a perfect gas. The fluid mediums investigated were air and helium and the Mach number range was from 5 to 40. A study of representative shock shapes was also made. Flow parameters obtained from the blast-wave analogy gave good correlations of induced pressures and shock shapes. The induced-pressure correlations yielded empirical equations for air and helium which cover the complete range of nose bluntness considered. (Nose fineness ratios varied from 0.4 to 4.) Available experimental results were in good agreement with the characteristics solutions. Properties connected with the concept of hypersonic similitude enabled correlations of the calculations to be made with respect to nose shape, Mach number, and ratio of specific heats.
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 46 |
| Release | : 2018-07-12 |
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| ISBN | : 9781722830243 |
An experimental investigation was conducted in the NASA Lewis 10 x 10 ft supersonic Wind Tunnel to determine the performance characteristics of 2D hypersonic exhaust nozzles/afterbodies at low supersonic conditions. Generally, this type of application requires a single expansion ramp nozzle (SERN) that is highly integrated with the airframe of the hypersonic vehicle. At design conditions (hypersonic speeds), the nozzle generally exhibits acceptable performance. At off-design conditions (transonic to mid-supersonic speeds), nozzle performance of a fixed geometry configuration is generally poor. Various 2-D nozzle configurations were tested at off-design conditions from Mach 2.0 to 3.5. Performance data is presented at nozzle pressure ratios from 1 to 35. Jet exhaust was simulated with high-pressure air. To study performance of different geometries, nozzle configurations were varied by interchanging the following model parts: internal upstream contour, expansion ramp, sidewalls, and cowl. Carboni, Jeanne D. and Shyne, Rickey J. and Leavitt, Laurence D. and Taylor, John G. and Lamb, Milton Glenn Research Center; Langley Research Center RTOP 763-01-21...
