Analysis and Comparison with Theory of Flow-field Measurements Near a Lifting Rotor in the Langley Full-scale Tunnel PDF Download
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Author: Harry H. Heyson
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 696
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Book Description
Results of an investigation in the Langley full-scale tunnel of the induced flow near a lifting rotor are given. Measurements of stream angles and velocities were made in several transverse planes along and behind the rotor in four different conditions representative of the cruising and high-speed ranges of flight. These measurements indicate that available theory may be used to calculate with reasonable accuracy the induced flow over the forward three-quarters of the disk for these flight conditions provided that a realistic nonuniform rotor disk-load distribution is assumed. Rearward of the three-quarter-diameter point, calculations of the induced velocity are increasingly inaccurate due to the rolling up of the trailing-vortex system. Farther rearward, well behind the rotor, the flow may be represented more accurately by the flow behind a uniformly loaded wing.
Author: Harry H. Heyson
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 696
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Book Description
Results of an investigation in the Langley full-scale tunnel of the induced flow near a lifting rotor are given. Measurements of stream angles and velocities were made in several transverse planes along and behind the rotor in four different conditions representative of the cruising and high-speed ranges of flight. These measurements indicate that available theory may be used to calculate with reasonable accuracy the induced flow over the forward three-quarters of the disk for these flight conditions provided that a realistic nonuniform rotor disk-load distribution is assumed. Rearward of the three-quarter-diameter point, calculations of the induced velocity are increasingly inaccurate due to the rolling up of the trailing-vortex system. Farther rearward, well behind the rotor, the flow may be represented more accurately by the flow behind a uniformly loaded wing.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: Alberta Y. Alksne
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 338
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 900
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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Book Description
Author: Warren J. Whitney
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 716
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Book Description
Mass-flow tables for ratios of specific heats of 1.3 and 1.4 are presented for the entire range of critical velocity ratio. The tables enable a quick and accurate determination of the integrated average specific mass flow across a region where the end-point velocities are known, commensurate with the assumptions that the total state is constant and the static pressure varies linearly between the two velocities. A numerical example is included to illustrate the use of the tables. All quantities are in nondimensional form and are tabulated sgainst critical velocity ratio. The tables include specific-mass-flow parameter and ratio of static to total pressure.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1208
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Book Description
Author: Sandra K. Faull
Publisher: Arlington, Va. : United States Historical Documents Institute
ISBN:
Category : Reference
Languages : en
Pages : 608
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1640
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Book Description
