Effects of Aspect Ratio on Air Flow at a High Subsonic Mach Numbers PDF Download
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Author: W. F. Lindsey
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 18
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Book Description
Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to two on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.
Author: W. F. Lindsey
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 18
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Book Description
Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to two on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.
Author: W. F. Lindsey
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 10
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Book Description
Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to 2 on the air flow past a wing at high subsonic Mach numbers. The results incidcated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1182
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Book Description
Author: Alfred A. Adler
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 7
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Book Description
Author: Charles H. Fox
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
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Book Description
The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied herein to an aspect ratio of 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio of 0.35 triangular cross-sectional body at Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations.
Author: E. Epremian
Publisher:
ISBN:
Category : Iron
Languages : en
Pages : 746
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Book Description
Extensive fatigue tests were made on annealed Armco iron and plain carbon and alloy steels heat-treated to different strengths and microstructures. Statistics of fatigue-fracture curves and endurance limits were determined from the experimental data obtained and, for various other materials, from a survey of literature. The results were analyzed to show the relative effects of various metallurgical factors on the statistical nature of fatigue properties. Other phases of the problem studied include: dependence of statistical variation in fatigue life on stress level in the fracture range, statistics for location of crack initiation, size effect, understressing effect, and the form and method of plotting the S-N diagram.
Author: Josef Rom
Publisher: Springer Science & Business Media
ISBN: 1461228247
Category : Science
Languages : en
Pages : 408
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Book Description
The aerodynamics of aircraft at high angles of attack is a subject which is being pursued diligently, because the modern agile fighter aircraft and many of the current generation of missiles must perform well at very high incidence, near and beyond stall. However, a comprehensive presentation of the methods and results applicable to the studies of the complex aerodynamics at high angle of attack has not been covered in monographs or textbooks. This book is not the usual textbook in that it goes beyond just presenting the basic theoretical and experimental know-how, since it contains reference material to practical calculation methods and technical and experimental results which can be useful to the practicing aerospace engineers and scientists. It can certainly be used as a text and reference book for graduate courses on subjects related to high angles of attack aerodynamics and for topics related to three-dimensional separation in viscous flow courses. In addition, the book is addressed to the aerodynamicist interested in a comprehensive reference to methods of analysis and computations of high angle of attack flow phenomena and is written for the aerospace scientist and engineer who is familiar with the basic concepts of viscous and inviscid flows and with computational methods used in fluid dynamics.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1138
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 568
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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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Book Description
