Wind Tunnel Force Tests of a Mercury Redstone Configuration, Without Escape Rocket Pylon, at Supersonic Mach Numbers PDF Download
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Author: Maurice A. Sylvester
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 54
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Book Description
Wind tunnel force tests were performed on a scale model of the Mercury Redstone. The model consisted of the Redstone booster section and the Mercury capsule without the escape rocket pylon. The static stability and drag characteristics of this configuration were determined at Mach numbers from 2.00 to 5.00 and at angles of attack from -4 to 12 degrees. The results are summarized and discussed at zero angle of attack. (Author).
Author: Maurice A. Sylvester
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 54
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Book Description
Wind tunnel force tests were performed on a scale model of the Mercury Redstone. The model consisted of the Redstone booster section and the Mercury capsule without the escape rocket pylon. The static stability and drag characteristics of this configuration were determined at Mach numbers from 2.00 to 5.00 and at angles of attack from -4 to 12 degrees. The results are summarized and discussed at zero angle of attack. (Author).
Author:
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ISBN:
Category : Science
Languages : en
Pages : 92
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Author: Albin O. Pearson
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 26
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Author: William C. Moseley (Jr.)
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ISBN:
Category : Aerodynamic load
Languages : en
Pages : 76
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Author:
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Category :
Languages : en
Pages : 24
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Author: Rudolf Hermann
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ISBN:
Category : Wind tunnels
Languages : en
Pages : 90
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In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Author: Earl J. Montoya
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
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Author: William C. Moseley (Jr.)
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ISBN:
Category : Aerospace engineering
Languages : en
Pages : 84
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Author: Francis J. Capone
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Category :
Languages : en
Pages : 36
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Wind-tunnel tests have been conducted to determine the errors of 3 seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 and at angles of attack from -1.7° to 8.4°. The test Reynolds number per foot varied from 3.35 x 106 to 4.05 x 106. For three 4-vane, gimbaled probes, the static-pressure errors remained constant throughout the test angle-of-attack range for all Mach numbers except 1.02. For two single-vane, self-rotating probes having two orifices at ±37.5° from the plane of symmetry on the lower surface of the probe body, the static-pressure error varied as much as 1.5 percent of free-stream static pressure through the test angle-of-attack range for all Mach numbers. For two fixed, cone-cylinder probes of short length and large diameter, the static-pressure error varied over the test angle-of-attack range at constant Mach numbers as much as 8 to 10 percent of free-stream static pressure.
Author: T. D. Buchanan
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 52
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