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Flight Investigation Of The Effect Of Boundary Layer Suction On Profile Drag Coefficient At Supercritical Mach Numbers
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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 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 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 1953 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1949 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Studies on Dynamics and Instrumentation of the Holloman Track by : Air Force Missile Development Center (U.S.)
Download or read book Studies on Dynamics and Instrumentation of the Holloman Track written by Air Force Missile Development Center (U.S.) and published by . This book was released on 1959 with total page 638 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Abstracts by : United States. National Advisory Committee for Aeronautics
Download or read book Research Abstracts written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1951 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NACA Research Memorandum by : United States. National Advisory Committee for Aeronautics
Download or read book NACA Research Memorandum written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1948 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Boundary-layer Control for Drag Reduction of a Swept-wing Section at Low Speed and High Reynolds Numbers by : Donald E. Gault
Download or read book An Experimental Investigation of Boundary-layer Control for Drag Reduction of a Swept-wing Section at Low Speed and High Reynolds Numbers written by Donald E. Gault and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Drag Reduction by Boundary-layer Suction on a Flat Plate and a 36-deg Swept Wing at Supersonic Speeds by : S. R. Pate
Download or read book Investigation of Drag Reduction by Boundary-layer Suction on a Flat Plate and a 36-deg Swept Wing at Supersonic Speeds written by S. R. Pate and published by . This book was released on 1962 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in a 40-in. supersonic tunnel to determine the effectiveness of boundary-layer suction for laminar flow control on a two-dimensional, biconvex, 36-degree swept wing and on a flat plate with and without shock impingement. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds-number/in. range from 0.17 to 0.66 x 10 to the sixth power. With suction, full chord laminar flow was maintained on the flat plate at free stream Mach number of 2.5 and 3 at length Reynolds numbers of 22 and 26.5 x 10 to the sixth power, respectively, which resulted in a total drag reduction of 77 and 74%. With suction and shock impingement across the plate resulting from a 1-degree shock generator angle, full chord laminar flow was maintained at free stream Mach number of 2.5, 3, and 3.5 at length Reynolds numbers of 19.7, 18.9, and 21.7 x 10 to the sixth power, respectively. On the 36-degree swept wing, full chord laminar flow was maintained with suction up to a length Reynolds number of 11.3 x 10 to the sixth power at free stream Mach number of 3. (Author).
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 Boundary Layer Suction on a 50-deg Swept Tapered Wing at M (free-stream) by : S. R. Pate
Download or read book Investigation of Drag Reduction by Boundary Layer Suction on a 50-deg Swept Tapered Wing at M (free-stream) written by S. R. Pate and published by . This book was released on 1964 with total page 32 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 boundary layer 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 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 Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 by : Mitchel H. Bertram
Download or read book Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 written by Mitchel H. Bertram and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Technical Report, AFMDC-TR. by : Air Force Missile Development Center (U.S.)
Download or read book Technical Report, AFMDC-TR. written by Air Force Missile Development Center (U.S.) and published by . This book was released on 1959 with total page 642 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Reports by : University of Minnesota. Department of Aeronautical Engineering
Download or read book Research Reports written by University of Minnesota. Department of Aeronautical Engineering and published by . This book was released on 1953 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Determination of Drag and Pressure Recovery of Two Scoop Inlets Located at Maximum-body-diameter Station at Mach Numbers from 0.8 to 1.8 by : Leonard W. Putland
Download or read book Flight Determination of Drag and Pressure Recovery of Two Scoop Inlets Located at Maximum-body-diameter Station at Mach Numbers from 0.8 to 1.8 written by Leonard W. Putland and published by . This book was released on 1956 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-flow ratios from 0.76 to 0.96 have been flight tested at an angle of attack of approximately zero degrees over a Mach number range from 0.8 to 1.8, and a Reynolds number range from 2,000,000 to7,000,000 based on body maximum diameter. One of the scoop inlets had a circular cross section with a boundary-layer diverter. The other scoop inlet had a semicircular cross section wrapped partly around the body with a boundary-layer splitter plate ahead of the inlet.
Book Synopsis Technical Report by : Air Force Missile Development Center (U.S.).
Download or read book Technical Report written by Air Force Missile Development Center (U.S.). and published by . This book was released on 1959 with total page 636 pages. Available in PDF, EPUB and Kindle. Book excerpt:
