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Experimental Investigation Of The Drag Of 30 60 And 90 Degree Cone Cylinders At Mach Numbers Between 15 And 82
Download Experimental Investigation Of The Drag Of 30 60 And 90 Degree Cone Cylinders At Mach Numbers Between 15 And 82 full books in PDF, epub, and Kindle. Read online Experimental Investigation Of The Drag Of 30 60 And 90 Degree Cone Cylinders At Mach Numbers Between 15 And 82 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Experimental Investigation of the Drag of 30-, 60-, and 90-degree Cone Cylinders at Mach Numbers Between 1.5 and 8.2 by : Alvin Seiff
Download or read book Experimental Investigation of the Drag of 30-, 60-, and 90-degree Cone Cylinders at Mach Numbers Between 1.5 and 8.2 written by Alvin Seiff and published by . This book was released on 1952 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Drag of 30 Degrees, 60 Degrees, and 90 Degrees Cone Cylinders at Mach Numbers Between 1.5 and 8.2 by : Alvin Seiff
Download or read book Experimental Investigation of the Drag of 30 Degrees, 60 Degrees, and 90 Degrees Cone Cylinders at Mach Numbers Between 1.5 and 8.2 written by Alvin Seiff and published by . This book was released on 1952 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Drag of 30°, 60°, and 90° Cone Cylinders at Mach Numbers Between 1.5 and 8.2 by : Alvin Seiff
Download or read book Experimental Investigation of the Drag of 30°, 60°, and 90° Cone Cylinders at Mach Numbers Between 1.5 and 8.2 written by Alvin Seiff and published by . This book was released on 1952 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1982 with total page 1282 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis The Drag of Finite-length Cylinders Determined from Flight Tests at High Reynolds Numbers for a Mach Number Range from 0.5 to 1.3 by : Clement J. Welsh
Download or read book The Drag of Finite-length Cylinders Determined from Flight Tests at High Reynolds Numbers for a Mach Number Range from 0.5 to 1.3 written by Clement J. Welsh and published by . This book was released on 1953 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: For supersonic speeds, the drag of circular cylinders is largely independent of fineness ratio and Reynolds numbers. At subsonic Mach numbers, the drag of finite-length cylinders (fineness ratios of about 60 and below) increases as their fineness ratios increase.
Book Synopsis A Wind-tunnel Investigation of Forces on Cones at Low Mach Numbers by : David Litwack
Download or read book A Wind-tunnel Investigation of Forces on Cones at Low Mach Numbers written by David Litwack and published by . This book was released on 1965 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The investigation was conducted to obtain subsonic aerodynamic forces on cones. Nine aluminum cones varying in apex angel from 10 degrees to 90 degrees were tested. Lift, drag and pitching moment were measured at angles of attack varying from -5 deg. to 180 deg. in 10 degree increments and at a dynamic pressure of up to 200 lb./sq. ft. The measured data was first corrected for tare and interference effects; three-dimensional wind-tunnel-boundary-corrections were then applied to correct the data to free-air conditions. This data is presented in graphical form as lift, drag and pitching moment coefficient versus angle of attack for each cone. A plot of drag coefficient versus Reynolds Number at each angle of attack for the 30 degree cone and the 60 degree cone showed the drag almost constant for each angle of attack over the small range of Reynolds Numbers tested (Re = 15,000 to Re = 57,000). The maximum lift to drag ratio for the three smallest cones (10 deg. to 30 deg. cone apex angle) occurred at an angle of attack between 30 deg. to 40 deg.; for every other cone (40 deg. to 90 deg. cone apex angle) the maximum L/D was at an angle of attack between 120 deg. and 130 deg. (Author).
Book Synopsis Experimental Stability and Drag of a Pointed and a Blunted 30 ̊half-angle Cone at Mach Numbers from 11.5 to 34 in Air by : Peter F. Intrieri
Download or read book Experimental Stability and Drag of a Pointed and a Blunted 30 ̊half-angle Cone at Mach Numbers from 11.5 to 34 in Air written by Peter F. Intrieri and published by . This book was released on 1966 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Effects of Viscosity on the Drag of Bodies of Revolution at a Mach Number of 1.5 by : Dean R. Chapman
Download or read book Experimental Investigation of the Effects of Viscosity on the Drag of Bodies of Revolution at a Mach Number of 1.5 written by Dean R. Chapman and published by . This book was released on 1947 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Tests were conducted to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested both with smooth surfaces and with roughness added to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. The principal geometric variables investigated were after-body shape and length-diameter ratio. For most models, force tests and base pressure measurements were made over a range of Reynolds numbers, based on model length, from 0.6 million to 5.0 millions. Schlieren photographs were used to analyze the effects of viscosity on flow separation and shock-wave configuration near the base and to verify the condition of the boundary layer as deduced from force tests. The results are discussed and compared with theoretical calculations.
Book Synopsis Experiments on Drag of Revolving Disks, Cylinders and Streamline Rods at High Speeds by : Theodore Theodorsen
Download or read book Experiments on Drag of Revolving Disks, Cylinders and Streamline Rods at High Speeds written by Theodore Theodorsen and published by . This book was released on 1944 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An experimental investigation concerned primarily with the extension of test data on the drag of revolving disks, cylinders, and streamline rods to high Mach numbers and Reynolds numbers is presented. A Mach number of 2.7 was reached for revolving rods with Freon 113 as the medium. The tests on disks extended to a Reynolds number of 7,000,000. Parts of the study are devoted to a reexamination of the von Kármán-Prandtl logarithmic resistance law and the Ackeret-Taylor supersonic drag formula and conditions for their validity. The tests confirm, in general, earlier theories and add certain new results. A finding of first importance is that the skin friction does not depend on the Mach number. Of interest, also, are experimental results on revolving rods at very high Mach numbers, which show drag curves of the type familiar from ballistics. A new result which may have general applicability is that the effect of surface roughness involves two distinct parameters, particle size and particle unit density. The particle size uniquely determines the Reynolds number at which the effect of the roughness first appears, whereas the particle unit density determines the behavior of the drag coefficient at higher Reynolds numbers. Beyond the critical Reynolds number at which the roughness effect appears, the drag coefficient is found to be a function of unit density. In the limiting case of particle "saturation," or a maximum density of particles, the drag coefficient remains constant as the Reynolds number is increased.
Book Synopsis Experimental Investigation of the Effects of Support Interference on the Drag of Bodies of Revolution at a Mach Number of 1.5 by : Edward W. Perkins
Download or read book Experimental Investigation of the Effects of Support Interference on the Drag of Bodies of Revolution at a Mach Number of 1.5 written by Edward W. Perkins and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains the results of an experimental investigation to determine the effects of support interference on the base drag and fore drage of two bodies of revolution. The results show that the rear supports affect the drag of a body of revolution through the immediate influence on the pressures acting over the rear portions of the body and thus the magnitude of the interference depends on the afterbody shape of the model, the Reynolds number of flow, and the condition of the boundary layer.
Book Synopsis An Experimental Investigation of the Near Wake of a Slender Cone at Mach Number by : Robert J. Cresci
Download or read book An Experimental Investigation of the Near Wake of a Slender Cone at Mach Number written by Robert J. Cresci and published by . This book was released on 1965 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: Various experimental data were obtained in the near wake region of a 10 degree angle sharp cone at free stream Mach numbers of 8.0 and 11.8. The Mach 8.0 tests were conducted at free stream Reynolds numbers of 300,000 and 1,700,000 per foot; laminar and turbulent boundary layers were obtained on the cone surface at these respective Reynolds numbers. Data obtained include radial profiles of temperature, pressure, and Mach number at axial locations between one and three base diameters downstream of the model. Heat transfer and pressure distributions on the model base were also obtained. The Mach 11.8 tests were conducted at a free stream Reynolds number of 600,000 per foot and the surface boundary layer for all these tests were laminar. Data obtained include centerline distributions of Mach number, pressure, and temperature for a distance between one and four base diameters downstream of the model. Centerline temperatures were also obtained in the recirculation region for model wall to stagnation temperature ratios of 0.06 and 0.47. In addition, total temperature profiles were obtained downstream of the rear stagnation point. (Author).
Book Synopsis Aerodynamic Characteristics of a Slender Cone-cylinder Body of Revolution at a Mach Number of 3.85 by : John R. Jack
Download or read book Aerodynamic Characteristics of a Slender Cone-cylinder Body of Revolution at a Mach Number of 3.85 written by John R. Jack and published by . This book was released on 1951 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3,850,000. Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for small angles of attack. The measured mean skin-friction coefficients agreed well with theoretical values obtained for laminar flow over cones.
Book Synopsis Experimental Stability and Drag of a Pointed and a Blunted 30 Degrees Half-angle Cone at Mach Numbers from 11.5 to 34 in Air by : Peter F. Intrieri
Download or read book Experimental Stability and Drag of a Pointed and a Blunted 30 Degrees Half-angle Cone at Mach Numbers from 11.5 to 34 in Air written by Peter F. Intrieri and published by . This book was released on 1966 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Zero-lift Drag of a Fin-stabilized Body of Fineness Ratio 10 at Mach Numbers Between 0.6 and 10 by : Carlton S. James
Download or read book Experimental Investigation of the Zero-lift Drag of a Fin-stabilized Body of Fineness Ratio 10 at Mach Numbers Between 0.6 and 10 written by Carlton S. James and published by . This book was released on 1953 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Near Wake of a Slender Cone at M[ach] by : Robert J. Cresci
Download or read book An Experimental Investigation of the Near Wake of a Slender Cone at M[ach] written by Robert J. Cresci and published by . This book was released on 1965 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Supersonic Flow Past Circular Cones at High Angles of Attack by : Abdollah Modavi
Download or read book An Experimental Investigation of Supersonic Flow Past Circular Cones at High Angles of Attack written by Abdollah Modavi and published by . This book was released on 1978 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U.S. Government Research & Development Reports by :
Download or read book U.S. Government Research & Development Reports written by and published by . This book was released on 1970 with total page 1298 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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