Method of Designing Airfoils with Prescribed Velocity Distributions in Compressible Potential Flows PDF Download
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Author: George R. Costello
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 32
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Book Description
By the assumption that the pressure-volume relation is linear, a method is given for computing the airfoil shape with a prescribed velocity distribution in a potential flow of a compressible nonviscous fluid.
Author: George R. Costello
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 32
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Book Description
By the assumption that the pressure-volume relation is linear, a method is given for computing the airfoil shape with a prescribed velocity distribution in a potential flow of a compressible nonviscous fluid.
Author: George R. Costello
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 30
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Book Description
If the prescribed velocity distribution is not theoretically attainable, the method gives a way of modifying the distribution so as to obtain a blade shape.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1026
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Book Description
Author: Lewis Research Center
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 542
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Book Description
Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 646
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Book Description
The aerodynamic forces and moments exerted on pitched and yawed wing-body combinations consisting of a slender body of revolution and a cruciform arrangement of thin wings have been investigated by two theoretical methods. One method, an extension of the slender wing-body theory of NACA TN No. 1662, makes possible the determination of simple closed expressions for the load distribution, of simple closed expressions for the load distribution, the forces, and the moments for slender cruciform-wing and body combinations in which the wings may be dissimilar plan form. The second method treats cruciform-wing and body combinations consisting of a body of revolution and identical wings of arbitrary aspect ratio and plan form. The results are valid at subsonic, transonic, and supersonic speeds.
Author: Robert O. Bullock
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 552
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1360
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Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.
Author: Alois T. Sutor
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 706
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Book Description
Analytical expressions are derived to show the geometric, thermodynamic, and aerodynamic relations among compressor, turbine, and exhaust nozzle for a gas-turbine engine. For a known compressor performance map, a matching method is described to show some of the design compromises that must be made when the components are to be combined into a turbine-propeller engine. A method of predicting engine performance for a range of operating conditions from known component maps is presented. An illustrative example of the matching method and the performance analysis is presented, showing some of the practical limitations of engine operation.
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 578
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 498
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Book Description
