Surface Pressure Distributions on a Large-scale 49 Degree Sweptback Wing-body-tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge PDF Download
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Author: H. Clyde McLemore
Publisher:
ISBN:
Category :
Languages : en
Pages : 128
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Book Description
Author: H. Clyde McLemore
Publisher:
ISBN:
Category :
Languages : en
Pages : 128
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Book Description
Author: H. Clyde McLemore
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 134
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 498
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Author: Marvin P. Fink
Publisher:
ISBN:
Category : Compressed air
Languages : en
Pages : 52
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Book Description
An investigation has been conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35° sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 65(1)-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with half-span and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range or angles of attack from -8° to 16° for Reynolds numbers from 1.8 x 106 to 4.4 x 106 and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hot-jet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Skin temperatures were about 340° F and wing heating could be handled with available materials without cooling. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane.
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Author: Marvin P. Fink
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 2106
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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: H. Clyde McLemore
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
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Book Description
