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Investigation Of Drag Reduction By Boundary Layer Suction On A Body Of Revolution At Mach Numbers 25 3 And 35
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Book Synopsis Investigation of Drag Reduction by Boundary-layer Suction on a Body of Revolution at Mach Numbers 2.5, 3, and 3.5 by : S. R. Pate
Download or read book Investigation of Drag Reduction by Boundary-layer Suction on a Body of Revolution at Mach Numbers 2.5, 3, and 3.5 written by S. R. Pate and published by . This book was released on 1965 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Drag Reduction by Boundarylayer Suction on a Body of Revolution at Mach Numbers 2.5, 3, and 3.5 by :
Download or read book Investigation of Drag Reduction by Boundarylayer Suction on a Body of Revolution at Mach Numbers 2.5, 3, and 3.5 written by and published by . This book was released on 1965 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 40-in. supersonic tunnel of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary-layer suction for laminar flow control on a 9.2-in.diam body of revolution at Mach 2. 5, 3, and 3.5 with a Reynolds number range (based on boundarylayer rake location) from 9.9 to 51.7 million for angles of attack from 0 to =2 deg. The condition of the boundary layer was very sensitive to changes in angle of attack. Increasing the Reynolds number also decreased the maximum angle of attack. Wake, suction, and total drag coefficients and the corresponding suction coefficients are presented, along with some fully turbulent wake drag coefficients for the no suction case.
Book Synopsis Investigation of Drag Reduction by Boundary Layer Suction on a 72.5-deg Swept Wind at M 2 and 2.25 by : S. R. Pate
Download or read book Investigation of Drag Reduction by Boundary Layer Suction on a 72.5-deg Swept Wind at M 2 and 2.25 written by S. R. Pate and published by . This book was released on 1963 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 40-Inch Supersonic Tunnel (A) of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary layer suction for laminar flow control on a two-dimensional, 72.5-deg swept wing having a subsonic leading edge. Test Mach numbers were 2 and 2.25 with a Reynolds number range based on wing chord from 3 to 14 million for angles of attack of 0.15, 0.45, and 0.75 deg. With suction, full chord laminar flow was maintained at M 2, alpha 0.15, 0.45, and 0.75 deg up to a length Reynolds number of approximately 9 million. At M 2.25 and alpha 0.15 deg, full chord lam inar flow was maintained up to a Reynolds number of 6.5 x 10 to the 6th power and for alpha 0.45 and 0.75 deg, up to a Reynolds number of 3 x 10 to the 6th power. Selected data are presented.
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 Investigation of Drag Reduction by Boundarylayer Suction on a 50-degree Swept Tapered Wing at M (free-stream) Equals 2.5 to 4 by : S. R. Pate
Download or read book Investigation of Drag Reduction by Boundarylayer Suction on a 50-degree Swept Tapered Wing at M (free-stream) Equals 2.5 to 4 written by S. R. Pate and published by . This book was released on 1964 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to determine the effectiveness of boundarylayer suction for laminar flow control on a tapered, three-dimensional, 50-deg swept supersonic wing. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds number range (based on boundary-layer rake location) from 4.3 to 19.5 million for angles of attack of zero and =3 deg. Wake drag, suction drag, and total drag coefficients and the corresponding suction coefficients are presented, along with fully turbulent wake drag coefficients for the no-suction case.
Book Synopsis Viscous Drag Reduction by : C. Sinclair Wells
Download or read book Viscous Drag Reduction written by C. Sinclair Wells and published by Springer. This book was released on 2013-12-20 with total page 497 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Investigation of Drag Reduction in Maintaining the Laminar Boundary Layer by Suction by : A. Ulrich
Download or read book Theoretical Investigation of Drag Reduction in Maintaining the Laminar Boundary Layer by Suction written by A. Ulrich and published by . This book was released on 1947 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Maintenance of a laminar boundary layer by suction was suggested recently to decrease the friction drag of an immersed body, in particular an airfoil section [1]. The present treatise makes a theoretical contribution to this question in which, for several cases of suction and blowing, the stability of the laminar velocity profile is investigated. Estimates of the minimum suction quantities for maintaining the laminar boundary layer and estimates of drag reduction are thereby obtained.
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.
Download or read book Report written by and published by . This book was released on 1945 with total page 620 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Report - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Report - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1947 with total page 652 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers by : B. Regenscheit
Download or read book Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers written by B. Regenscheit and published by . This book was released on 1947 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: With an approach of the velocity of flight of a ship to the velocity of sound, there occurs a considerable increase of the drag. The reason for this must be found in the boundary layer separation caused by formation of shock waves. It will be endeavored to reduce the drag increase by suction of the boundary layer. Experimental results showed that drag increase may be considerably reduced by this method. It was, also, observed that, by suction, the position of shock waves can be altered to a considerable extent.
Book Synopsis Investigation of the Drag of Blunt-nosed Bodies of Revolution in Free Flight at Mach Numbers from 0.6 to 2.3 by : Harvey A. Wallskog
Download or read book Investigation of the Drag of Blunt-nosed Bodies of Revolution in Free Flight at Mach Numbers from 0.6 to 2.3 written by Harvey A. Wallskog and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Drag Reduction Due to Gas Injection Through Various Discrete Slots on a Three-dimensional Wing at Mach 2.01 by : Russell B. Sorrells
Download or read book Drag Reduction Due to Gas Injection Through Various Discrete Slots on a Three-dimensional Wing at Mach 2.01 written by Russell B. Sorrells and published by . This book was released on 1969 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Annual Report of the National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1946 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Book Synopsis INVESTIGATION OF DRAG REDUCTION BY BOUNDARY-LAYER SUCTION ON A 36-DEG SWEPT WING AT M by :
Download or read book INVESTIGATION OF DRAG REDUCTION BY BOUNDARY-LAYER SUCTION ON A 36-DEG SWEPT WING AT M written by and published by . This book was released on 1963 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Investigation of the Effect of Boundary-layer Suction on Profile-drag Coefficient at Supercritical Mach Numbers by : Richard B. Skoog
Download or read book Flight Investigation of the Effect of Boundary-layer Suction on Profile-drag Coefficient at Supercritical Mach Numbers written by Richard B. Skoog and published by . This book was released on 1949 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
