Pressure Distribution and Some Effects of Viscosity on Slender Inclined Bodies of Revolution PDF Download
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Author: H. Julian Allen
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 26
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Book Description
The simplified solution for the pressure distribution of slender inclined bodies of revolution is developed. The solution should be suitable for bodies of high fineness ratio even at low supersonic speeds, provided the angle of attack is small. Comparison with low-speed experimental results indicates that the observed flow separation phenomena can be explained in terms of the calculated pressure distributions together with the theory of oblique viscous flows.
Author: H. Julian Allen
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 26
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Book Description
The simplified solution for the pressure distribution of slender inclined bodies of revolution is developed. The solution should be suitable for bodies of high fineness ratio even at low supersonic speeds, provided the angle of attack is small. Comparison with low-speed experimental results indicates that the observed flow separation phenomena can be explained in terms of the calculated pressure distributions together with the theory of oblique viscous flows.
Author: Edward W. Perkins
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
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Book Description
Abstract: An investigation of the pressure distribution for a body of revolution, consisting of a 33-1/3-caliber (5.75 fineness ratio) tangent ogival nose and a cylindrical afterbody, has been made for an angle-of-attack range of 0° to 35.5° at a Mach number of 1.98 and a Reynolds number of approximately 0.5 x 106m based on body diameter. Comparisons of the theoretical and experimental pressure distributions are made to show the nature of the effects of both viscosity and cross-flow compressibility. The experimental load distributions are compared with those predicted by the method suggested in NACA RM A9I26 which includes an approximate method for taking into account the effects of viscosity on the lift distribution.
Author: John M. Swihart
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 46
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Book Description
Abstract: The effects of varying Reynolds number on the pressure distribution over a transonic body of revolution are presented. Angles of attack from -2° to 15° were investigated through a Mach number range from 0.60 to 1.09. The Reynolds number based on body length varied from 9 x 106 to 39 x 106, and on maximum diameter from 1.35 x 105 to 4.53 x 105. There were small effects of Reynolds number on the axial pressure distributions of these bodies. These effects were of such a nature as to cause an increase of 0.05 in the normal-force coefficient of the body when tested in the subcritical cross-flow Reynolds number range. A comparison between values of incremental pressure coefficient due to angle of attack and theoretical values was made.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 26
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Book Description
Author: Bruce B. Estabrooks
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 50
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1026
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Book Description
Author: Carl Kaplan
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 252
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Book Description
Author: Song Fu
Publisher: Springer Nature
ISBN: 981974010X
Category :
Languages : en
Pages : 1991
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Book Description
Author: Virgil E. Schrock
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 678
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Book Description
The constant-pressure specific heat of carbon dioxide has been measured over the range of temperatures and pressures from ambient condtions to 1000 pounds per square inch gage and 1000 degrees F using a steady-flow calorimeter operated on an open cycle. It appears that the apparatus as used in this determination will yield values with a probable error of 0.5 percent at the highest temperature level considered. The results of these tests check the widely accepted spectroscopic data within 1 percent. The values at elevated pressure are in reasonable agreement with those derived from the zero-pressure spectroscopic values and the application of the Beattie-Bridgeman equation of state. Only very limited calorimetric data are available in the literature, but substantial agreement exists with those considered reliable.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 162
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Book Description
