Experimental Investigation of the Test Flow in an Arc-heated Hypersonic Wind Tunnel PDF Download
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Author: James L. Folck
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 162
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Book Description
Author: James L. Folck
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 162
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Book Description
Author: James Thomas Van Kuren
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 410
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Book Description
Author: S. L. Petrie
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 40
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Book Description
Author: William B. Boatright
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 44
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
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Author: J. R. Nicholson
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 20
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Book Description
Various continuous flow hypersonic wind-tunnel testing facilities are discussed in general and the possibility of employing the exothermic decomposition of nitrous oxide to generate high temperature air is considered in detail. The feasibility of establishing high enthalpy air streams by mixing pre-heated nitrous oxide with a hot stream of nitrogen which was heated separately to temperatures ranging from 1033K to 1264K was investigated experimentally. The temperatures of the pre-heated nitrous oxide ranged from 875K to 1055K. After the decomposition of the nitrous oxide the gas mixture attained temperatures between 859K and 1807K. When the decomposition process was incomplete the reacted gas contained a substantial quantity of nitrogen dioxide and nitrogen tetroxide. On the other hand only about 1% of these products was formed when the reaction went to completion. The highest temperature of the reacted products amounted to 1807K which indicates that nearly 80% of the theoretical temperature rise was obtained. (Author).
Author: Roger Bell Stewart
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 40
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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This report presents the theoretical and experimental results related to flows over such simple bodies as semisphere, cone, and wedge. These were investigated in hypersonic wind tunnels of various classes at nearly equal Mach and Reynolds numbers (M from 7.0 to 8.0, Re(o) from 135 to 240) but at notably different free-stream velocities: 790, 2700 and 6000 m/s. Hypersonic resistance and arc-heating wind tunnels and a hypersonic MHD-accelerator wind tunnel, as well as their test equipment are described. A technique to determine parameters of a free stream over a model including gasdynamic ones (M, Re, Re(o), T, P, V, Ho, H) and physico-chemical ones (gamma To, Tv, Tn, Ci), as well as a verification procedure are presented. Experimental data on pressure distribution over models, shock wave positions/shapes were obtained. The experimental data are compared with respective calculated results obtained by using the VSL theory and the Navier-Stokes equations for the test conditions adopted. Interrelation of the theoretical and test data is shown not to be unambiguous, especially in what concerns locations and shapes of shock waves. The VSL theory is employed to compute local parameters of the shock layer. The influence of alkali metal seed on the rate of relaxation in the shock-layer is considered. Features of profiles of both temperature and air component concentrations in the shock layer are shown to be useful in explaining a set of phenomena revealed in experiments: a radiation offset upstream of a sphere hypervelocity shock layer, a radiation relaxation at a cone apex. The impact of the seed metal is shown to be insignificant.
Author: James L. Folck
Publisher:
ISBN:
Category :
Languages : en
Pages : 67
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Book Description
The study consisted of the experimental investigation of test flow in an arc heated hypersonic wind tunnel. These tests utilized a high voltage DC arc heater which operated at input powers in excess of 50 megawatts and provided reservoir pressures ranging from 100 to 1500 psi and bulk enthalpies from 1500 to 4000 BTU/lb. Local free stream measurements of pitot pressure, mass flux, stagnation point heat transfer rate and wall static pressures were obtained at the exit of a nominal two-foot diameter conical nozzle. Stagnation enthalpy profiles at the nozzle exit became peaked at high stagnation pressures. From these data, center line enthalpies as high as 6500 BTU/lb were indicated in the flow. Selective comparisons between one-dimensional expansion theory and experiment are presented. At a reservoir enthalpy of approximately 2500 BTU/lb and for stagnation pressure in excess of 500 psi the expanded flow data were in good agreement with equilibrium expansion theory. However, below 500 psi the data compared more closely with nonequilibrium theory with the flow frozen downstream of the nozzle throat. (Author).
Author: P.M. Sherman
Publisher:
ISBN:
Category :
Languages : en
Pages : 198
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Book Description
