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Skin Friction Drag And Boundary Layer Transition On A Parabolic Body Of Revolution Naca Rm 10 At A Mach Number Of 16 In The Langley 4 By 4 Foot Supersonic Pressure Tunnel
Download Skin Friction Drag And Boundary Layer Transition On A Parabolic Body Of Revolution Naca Rm 10 At A Mach Number Of 16 In The Langley 4 By 4 Foot Supersonic Pressure Tunnel full books in PDF, epub, and Kindle. Read online Skin Friction Drag And Boundary Layer Transition On A Parabolic Body Of Revolution Naca Rm 10 At A Mach Number Of 16 In The Langley 4 By 4 Foot Supersonic Pressure Tunnel ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Technical Note - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1957 with total page 878 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range by : John M. Swihart
Download or read book Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range written by John M. Swihart and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The effects of varying Reynolds number on the pressure distribution over a transonic body of revolution are presented. Angles of attack from -2° to 15° were investigated through a Mach number range from 0.60 to 1.09. The Reynolds number based on body length varied from 9 x 106 to 39 x 106, and on maximum diameter from 1.35 x 105 to 4.53 x 105. There were small effects of Reynolds number on the axial pressure distributions of these bodies. These effects were of such a nature as to cause an increase of 0.05 in the normal-force coefficient of the body when tested in the subcritical cross-flow Reynolds number range. A comparison between values of incremental pressure coefficient due to angle of attack and theoretical values was made.
Book Synopsis Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total, Base, and Skin-friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag by : August F. Bromm
Download or read book Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total, Base, and Skin-friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag written by August F. Bromm and published by . This book was released on 1953 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Index of NACA Technical Publications by : United States. National Advisory Committee for Aeronautics
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1955 with total page 1338 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel by : Donald E. Coletti
Download or read book Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel written by Donald E. Coletti and published by . This book was released on 1952 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NACA Research Memorandum written by and published by . This book was released on 19?? with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 by : Davis H. Crawford
Download or read book Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 written by Davis H. Crawford and published by . This book was released on 1956 with total page 680 pages. Available in PDF, EPUB and Kindle. Book excerpt: At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by :
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by and published by . This book was released on 1954 with total page 818 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigations at Supersonic Speeds of the Base Pressure on Bodies of Revolution with and Without Sweptback Stabilizing Fins by : Eugene S. Love
Download or read book Investigations at Supersonic Speeds of the Base Pressure on Bodies of Revolution with and Without Sweptback Stabilizing Fins written by Eugene S. Love and published by . This book was released on 1952 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Average Skin-friction Drag Coefficients from Tank Tests of a Parabolic Body of Revolution (NACA RM-10) by : Elmo J. Mottard
Download or read book Average Skin-friction Drag Coefficients from Tank Tests of a Parabolic Body of Revolution (NACA RM-10) written by Elmo J. Mottard and published by . This book was released on 1953 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Average skin-friction drag coefficients were obtained from boundary-layer total-pressure measurements on a parabolic body of revolution (NACA RM-10) basic fineness ratio 15 in water at Reynolds numbers from 4,400,000 to 70,000,000. The tests were made in the Langley tank no. 1 with the body sting-mounted at a depth of two maximum body diameters. The arithmetic mean of three drag measurements taken around the body was in good agreement with flat-palte results, but, apparently because of the slight surface wave casue by the body, the distribution of the boundary layer around the body was not uniform over part of the Reynolds number range.
Book Synopsis Investigation of the Variation with Reynolds Number of the Base, Wave, and Skin-friction Drag of a Parabolic Body of Revolution (NACA RM-10) at Mach Numbers of 1.62, 1.93, and 2.41 in the Langley 9-inch Supersonic Tunnel by : Eugene S. Love
Download or read book Investigation of the Variation with Reynolds Number of the Base, Wave, and Skin-friction Drag of a Parabolic Body of Revolution (NACA RM-10) at Mach Numbers of 1.62, 1.93, and 2.41 in the Langley 9-inch Supersonic Tunnel written by Eugene S. Love and published by . This book was released on 1952 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Journal of the Royal Aeronautical Society by :
Download or read book Journal of the Royal Aeronautical Society written by and published by . This book was released on 1954 with total page 910 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 A Transonic Investigation of the Effects of Semisubmerged-store Cavities and of Slots on the Zero-lift Drag of a Body of Revolution by : George H. Holdaway
Download or read book A Transonic Investigation of the Effects of Semisubmerged-store Cavities and of Slots on the Zero-lift Drag of a Body of Revolution written by George H. Holdaway and published by . This book was released on 1957 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Roughness Drag Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder from Force Tests at Transonic Speeds by : K. R. Czarnecki
Download or read book Roughness Drag Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder from Force Tests at Transonic Speeds written by K. R. Czarnecki and published by . This book was released on 1969 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Review of High-speed, Convective, Heat-transfer Computation Methods by : Michael E. Tauber
Download or read book A Review of High-speed, Convective, Heat-transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Handbook of Supersonic Aerodynamics by : Johns Hopkins University. Applied Physics Laboratory
Download or read book Handbook of Supersonic Aerodynamics written by Johns Hopkins University. Applied Physics Laboratory and published by . This book was released on 1952 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:
