Investigation of Reynolds Number Effects for a Series of Cone-cylinder Bodies at Mach Number of 1.62, 1.93, and 2.41 PDF Download
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Author: Carl E. Grigsby
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
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Abstract: An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having varying fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 106 to 10 x 106. The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number.
Author: Carl E. Grigsby
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 28
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Book Description
Abstract: An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having varying fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 106 to 10 x 106. The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number.
Author: P. Calvin Stainback
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82
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Author: John R. Jack
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 16
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An investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained for a cone cylinder and a parabolic-nosed cylinder at Reynolds numbers up to 12,000,000 based on body length. The results show that cooling the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2,000,000 at equilibrium to 10,600,000. For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reductions in temeprature ratio near 1.4 indicated that temperature ratios slight lower may result in a laminar boundary layer for very high Reynolds numbers. For the parabolic-nosed body, the transition Reynolds number was about twice that of the cone-cylinder model over the temperature range investigated.
Author: Jerome D. Julius
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
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Author: Julio Chu
Publisher:
ISBN:
Category : Angle of attack
Languages : en
Pages : 44
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Author: Atlee M. Cunningham
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 88
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Author:
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ISBN:
Category :
Languages : en
Pages : 0
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The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested through the speed range of the Langley 19-foot pressure tunnel at two values of air pressure. The ranges of Mach number obtained were from 0.07 to 0.34 at atmospheric pressure and from 0.08 to 0.26 at a pressure of 33 pounds per square inch absolute. The corresponding Reynolds number ranges were from 0.97 x 10(exp 6) to 4.44 x 10(exp 6) and from 2.20 x 10(exp 6) to 8.10 x 10(exp 6), respectively. The tests were made with and without partial-span and full-span split flaps deflected 60 deg. Pressure-distribution measurements were obtained for all configurations. The maximum lift coefficient was a function of the two independent variables, Mach number and Reynolds number, and both parameters had an important effect on the maximum lift coefficient in the ranges investigated. The stall-progression and, consequently, the shape of the lift-curve at the stall were influenced by variations in both Mach number and Reynolds number. Peak maximum lift coefficients were measured at Mach numbers between 0.12 and 0.20, depending on the Reynolds number range and flap configuration. There was very little influence of either Mach number or Reynolds number on the maximum lift of the wing with leading-edge roughness.
Author: Edwin J. Saltzman
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56
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Author: M. J. Goodyer
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 28
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Author: Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 516
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