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Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 878

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Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 878

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Book Description

Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range

Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range PDF Author: John M. Swihart
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 46

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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.

Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total, Base, and Skin-friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag

Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total, Base, and Skin-friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag PDF Author: August F. Bromm
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26

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Index of NACA Technical Publications

Index of NACA Technical Publications PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1338

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Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel

Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel PDF Author: Donald E. Coletti
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28

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NACA Research Memorandum

NACA Research Memorandum PDF Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 72

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Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8

Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 PDF Author: Davis H. Crawford
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 680

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At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.

A Selected Listing of NASA Scientific and Technical Reports for ...

A Selected Listing of NASA Scientific and Technical Reports for ... PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818

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Investigations at Supersonic Speeds of the Base Pressure on Bodies of Revolution with and Without Sweptback Stabilizing Fins

Investigations at Supersonic Speeds of the Base Pressure on Bodies of Revolution with and Without Sweptback Stabilizing Fins PDF Author: Eugene S. Love
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 70

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Average Skin-friction Drag Coefficients from Tank Tests of a Parabolic Body of Revolution (NACA RM-10)

Average Skin-friction Drag Coefficients from Tank Tests of a Parabolic Body of Revolution (NACA RM-10) PDF Author: Elmo J. Mottard
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 26

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Average skin-friction drag coefficients were obtained from boundary-layer total-pressure measurements on a parabolic body of revolution (NACA RM-10) basic fineness ratio 15 in water at Reynolds numbers from 4,400,000 to 70,000,000. The tests were made in the Langley tank no. 1 with the body sting-mounted at a depth of two maximum body diameters. The arithmetic mean of three drag measurements taken around the body was in good agreement with flat-palte results, but, apparently because of the slight surface wave casue by the body, the distribution of the boundary layer around the body was not uniform over part of the Reynolds number range.