Some Effects of Heat Transfer at Mach Number 2.0 at Stagnation Temperatures Between 2,310° and 3,500° R on a Magnesium Fin with Several Leading-edge Modifications PDF Download
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Author: William M. Bland
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Abstract: Four models of a thin magnesium fin, with the leading edge swept back 35°, have been tested in the preflight high-temperature jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va., at a Mach number of 2.0 for various stagnation temperatures between 2,310° and 3,500° R. This exploratory investigation was made to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective schemes.
Author: William M. Bland
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Abstract: Four models of a thin magnesium fin, with the leading edge swept back 35°, have been tested in the preflight high-temperature jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va., at a Mach number of 2.0 for various stagnation temperatures between 2,310° and 3,500° R. This exploratory investigation was made to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective schemes.
Author: William M. Bland
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 382
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 642
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1508
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Book Description
Author: Joseph Adams Shortal
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 796
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1846
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1092
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Author: William M. Bland
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 15
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Book Description
Three un-instrumented tapered magnesium fins with the leading edges swept back 17 degrees have been tested in an ethylene-heated high-temperature jet at the Langley Pilotless Aircraft Research Station at Wallops Island, Virginia. These tests were made to investigate some effects of leading-edge diameter and leading-edge shape on the aerodynamic heating by noting the time for melting to begin on the fins. Results of these tests, which were conducted at a Mach number of 2.0 for stagnation temperatures in the neighborhood of 2,600 degrees R, indicate that increasing the diameter of the cylindrical leading edge increased the time required for melting to start. This increase was greater, probably because of conduction effects, than that predicted by relating the time to melt inversely with the square root of leading-edge diameter. Also, the model with the flat-face leading edge lasted 1.39 times as long as the model with about the same size cylindrical leading edge.
Author: Ivan E. Beckwith
Publisher:
ISBN:
Category : Hypersonic planes
Languages : en
Pages : 36
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Book Description
Design studies of hypersonic lifting vehicles have generally indicated that aerodynamic heating may be reduced by using highly swept configurations with blunted leading edges. For laminar boundary layers the effect of sweep angle A on the heat transfer at the leading edge is usually taken as cos A as shown by the data of Feller (ref. 1) who measured the average heat transfer on the front half of a swept cylinder. More recent data (refs. 2 and 3) have indicated that the effect of sweep may be more nearly cos3/2 Lambda which, at a sweep angle of 75 deg, would result in a 50-percent reduction of the heat transfer predicted by the cos A variation. The data and theory of reference 4 also indicate a cos3/2 lambda variation but the theories of references 5 and 6 indicate a variation somewhere between cos A and cos3/2 lambda for large stream Mach numbers. The data of reference 7, in contrast to the investigations just cited, showed large increases in average heat transfer to a circular leading edge with increasing A up to a lambda of about 40 deg. These increases in heat transfer were probably caused by transition to turbulent flow which apparently resulted primarily from the inherent instability of the three-dimensional boundary layer flow on a yawed cylinder. The leading-edge Reynolds numbers of reference 7 were considerably larger than the values in references 1 to 4 and were also larger than typical values for full-scale leading edges of hypersonic vehicles; hence, the main application of the high Reynolds number tests will probably be to bodies at angle of attack.
