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 Download
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Author: August F. Bromm
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
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Book Description
Author: August F. Bromm
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
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Book Description
Author: August F. Bromm
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 20
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Book Description
An investigation has been conducted in the Langley 9-inch supersonic tunnel to determine the effect of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag at zero lift of seven boattail bodies of revolution designed for minimum wave drag according to NACA Technical Note 2550. The investigation covered a Reynolds number range from approximately 1,000,000 to 10,000,000 at Mach numbers of 1.62, 1.93, and 2.41, respectively. The results show that base drag and, in general, the total drag increase with increasing values of the ratio of base area to maximum area B/S(max), although the results reported in NACA Technical Note 3054 showed that the wave drag decreased with ticreasing values of B/S(max). The laminar skin-friction drag is in agreement with the theoretical predictions used, and, within the Mach number range of these tests, the simple Blasius incompressible theory gives a satisfactory prediction. Except for values of B/S(max) near 1, the Reynolds number of transition increases with increasing Mach number and, as this ratio approaches 1, this variation is seen to reverse. These variations in Reynolds number of transition with Mach number appear to be associated with the changes in pressure gradient over the rear of the bodies.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 878
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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.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 342
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Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1640
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1020
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Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
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Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category :
Languages : en
Pages : 1576
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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