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  • 1
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    Further shock tunnel studies of scramjet phenomena (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Scramjet phenomena were studied using the shock tunnel T3 at the Australian National University. Simple two dimensional models were used with a combination of wall and central injectors. Silane as an additive to hydrogen fuel was studied over a range of temperatures and pressures to evaluate its effect as an ignition aid. The film cooling effect of surface injected hydrogen was measured over a wide range of equivalence. Heat transfer measurements without injection were repeated to confirm previous indications of heating rates lower than simple flat plate predictions for laminar boundary layers in equilibrium flow. The previous results were reproduced and the discrepancies are discussed in terms of the model geometry and departures of the flow from equilibrium. In the thrust producing mode, attempts were made to increase specific impulse with wall injection. Some preliminary tests were also performed on shock induced ignition, to investigate the possibility in flight of injecting fuel upstream of the combustion chamber, where it could mix but not burn.
    Keywords: AERODYNAMICS
    Type: NASA-CR-179937 , NAS 1.26:179937 , RR-10-86
    Format: application/pdf
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  • 2
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    Thermodynamics and wave processes in high Mach number propulsive ducts (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Analysis of the flow in a propulsive duct indicates that, at high Mach numbers, the thermodynamic energy of the fluid is delivered directly into compression and expansion waves. The importance of the resulting wave phenomena is explored by considering the net thrust delivered by a two dimensional convergent-divergent duct with a simplified, planar heat addition zone. It is found that net thrust is reduced when operating at other than the design Mach number, an effect which is most severe for Mach numbers exceeding the design value. An idealized model is developed, involving a self-induced heat injection cycle, and it is seen that the waves produced by this cycle can be the dominant agency in producing thrust.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0261
    Format: text
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  • 3
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    Measurements of scramjet thrust in shock tunnels (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: By using results obtained in tests on supersonic combustion of hydrogen in air, the conditions governing model size and operating pressure levels for shock tunnel experiments on models of flight vehicles with scramjet propulsion are established. It is seen that large models are required. The development of the stress wave force balance is then described, and its use as a method of measuring thrust/drag on such models is discussed. Test results on a simple, fully integrated scramjet model, with intakes, combustion chambers, thrust surfaces and exterior surfaces, using a 13 percent silane 87 percent hydrogen fuel mixture, showed that a steady state with thrust generation could be achieved within the shock tunnel test time, and the thrust could be measured. Results are presented for a range of stagnation enthalpies, and show that the scramjet model produces net positive thrust at velocities up to 2.4 km/sec.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 94-2516 , AIAA Aerospace Ground Testing Conference; Jun 20, 1994 - Jun 23, 1994; Colorado Springs, CO; United States|Shock Tunnel Studies of Scramjet Phenomena 1994; 11 p
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  • 4
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    Mach 4 and Mach 8 axisymmetric nozzles for a high-enthalpy shock tunnel (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The performance of two axisymmetric nozzles which were designed to produce uniform, parallel flow with nominal Mach numbers of 4 and 8 is examined. A free-piston-driven shock tube was used to supply the nozzle with high-temperature, high-pressure test gas. The inviscid design procedure treated the nozzle expansion in two stages. Close to the nozzle throat, the nozzle wall was specified as conical and the gas flow was treated as a quasi-one-dimensional chemically-reacting flow. At the end of the conical expansion, the gas was assumed to be calorically perfect, and a contoured wall was designed (using method of characteristics) to convert the source flow into a uniform and parallel flow at the end of the nozzle. Performance was assessed by measuring Pitot pressures across the exit plane of the nozzles and, over the range of operating conditions examined, the nozzles produced satisfactory test flows. However, there were flow disturbances in the Mach 8 nozzle flow that persisted for significant times after flow initiation.
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal (ISSN 0001-9240); 95; 324-334
    Format: text
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  • 5
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    Scramjet thrust measurement in a shock tunnel (1995)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: This note reports tests in a shock tunnel in which a fully integrated scamjet configuration produced net thrust. The experiments not only showed that impluse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/s, and shock tunnels offer a means of generating high Mach number flows at such speeds.
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal (ISSN 0001-9240); 99; 984; p. 161-163
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  • 6
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    Waves and thermodynamics in high Mach number propulsive ducts (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The propulsive effects of waves in ducts, especially at high Mach numbers, are investigated, focusing on drag and thrust and on the conversion of heat into waves which produce thrust. It is shown that essentially all of the work done by an expanding fluid passing through a duct at high Mach number is delivered in the form of waves, and that duct surface angles exist that are optimum for the production of thrust from a wave. The effects of wave phenomena on drag and thrust are considered by extending the concept of a Busemann biplane into that of a 'Busemann scramjet, taking 'off-design' performance into account. An idealized model of a streamtube with heat addition is developed, and flow mechanisms involved in generating thrust by the expansion of this streamtube in an exhaust nozzle are examined.
    Keywords: AERODYNAMICS
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  • 7
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    Hypervelocity flow in axisymmetric nozzles (1989)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A simple procedure for the design of axisymmetric supersonic nozzles for use in reflected-mode shock tunnels is described. This method has been used to design a moderate Mach number (M = 4) nozzle and a high Mach number (M = 10) nozzle. Both nozzles have been calibrated by measuring the pitot profiles near the nozzle exit planes and, although the M = 4 nozzle performs well, the M = 10 appears to have reached a Mach number - pressure limit in which the unsteady nozzle boundary layers significantly affect the test flow.
    Keywords: AERODYNAMICS
    Type: Australasian Fluid Mechanics Conference; Dec 11, 1989 - Dec 15, 1989; Melbourne; Australia
    Format: text
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  • 8
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    High enthalpy, hypervelocity flows of air and argon in an expansion tube (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: An expansion tube with a free piston driver has been used to generate quasi-steady hypersonic flows in argon and air at flow velocities in excess of 9 km/s. Irregular test flow unsteadiness has limited the performance of previous expansion tubes, and it has been found that this can be avoided by attention to the interaction between the test gas accelerating expansion and the contact surface in the primary shock tube. Test section measurements of pitot pressure, static pressure and flat plate heat transfer are reported. An approximate analytical theory has been developed for predicting the velocities achieved in the unsteady expansion of the ionizing or dissociating test gas.
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal (ISSN 0001-9240); 95; 175-186
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