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Effects Of Fixing Boundary Layer Transition For A Swept And A Triangular Wing And Body Combination At Mach Numbers From 060 To 140
Download Effects Of Fixing Boundary Layer Transition For A Swept And A Triangular Wing And Body Combination At Mach Numbers From 060 To 140 full books in PDF, epub, and Kindle. Read online Effects Of Fixing Boundary Layer Transition For A Swept And A Triangular Wing And Body Combination At Mach Numbers From 060 To 140 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 by : Louis S. Stivers
Download or read book Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 written by Louis S. Stivers and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 by :
Download or read book Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 written by and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 by : Louis S. Stivers
Download or read book Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 written by Louis S. Stivers and published by . This book was released on 1960 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Journal of the Royal Aeronautical Society by : Royal Aeronautical Society
Download or read book The Journal of the Royal Aeronautical Society written by Royal Aeronautical Society and published by . This book was released on 1960 with total page 1156 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0 by : W. F. Lindsey
Download or read book The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0 written by W. F. Lindsey and published by . This book was released on 1954 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.
Book Synopsis Effects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate by : Don W. Jillie
Download or read book Effects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate written by Don W. Jillie and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Analytical Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5 by : Samuel Ralph Pate
Download or read book Experimental and Analytical Investigation of Boundary-layer Transition on Swept Wings at Mach Numbers 2.5 to 5 written by Samuel Ralph Pate and published by . This book was released on 1965 with total page 95 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Effects of Mach Number, Leading-edge Bluntness, and Sweep on Boundary-layer Transition on a Flat Plate by : DON W. JILLIE
Download or read book Effects of Mach Number, Leading-edge Bluntness, and Sweep on Boundary-layer Transition on a Flat Plate written by DON W. JILLIE and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of leading-edge bluntness and sweep on boundary-layer transition on flat plate models were investigated at Mach numbers of 2.00, 2.50, 3.00, and 4.00. The effect of sweep on transition was also determined on a flat plate model equipped with an elliptical nose at a Mach number of 0.27. Models used for the supersonic investigation had leading-edge radii varying from 0.0005 to 0.040 inch. The free-stream unit Reynolds number was held constant at 15 million per foot for the supersonic tests and the angle of attack was 0 degrees. Surface flow conditions were determined by visual observation and recorded photographically. For the models with the blunter leading edges, the transition Reynolds number (based on free-stream flow conditions) was approximately doubled by an increase in Mach number from 2.50 to 4.00; and nearly the same result was predicted from shock-loss considerations. At all supersonic Mach numbers, increases in sweep reduced the transition Reynolds number and the amount of reduction increased with increases in bluntness. The shock-loss method considerably underestimated the sweep effects, with swept wings. (Author).
Book Synopsis Three-dimensional Boundary-layer Transition on a Swept Wing at Mach 3.5 by : L. N. Cattafesta
Download or read book Three-dimensional Boundary-layer Transition on a Swept Wing at Mach 3.5 written by L. N. Cattafesta and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781729234693 Total Pages :48 pages Book Rating :4.2/5 (346 download)
Book Synopsis Preliminary In-Flight Boundary Layer Transition Measurements on a 45 Deg Swept Wing at Mach Numbers Between 0.9 and 1.8 by : National Aeronautics and Space Adm Nasa
Download or read book Preliminary In-Flight Boundary Layer Transition Measurements on a 45 Deg Swept Wing at Mach Numbers Between 0.9 and 1.8 written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-10-25 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary flight experiment was flown to generate a full-scale supersonic data base to aid the assessment of computational codes, to improve instrumentation for measuring boundary layer transition at supersonic speeds, and to provide preliminary information for the definition of follow-on programs. The experiment was conducted using an F-15 aircraft modified with a small cleanup test section on the right wing. Results are presented for Mach (M) numbers from 0.9 to 1.8 at altitudes from 25,000 to 55,000 ft. At M greater than or = 1.2, transition occurred near or at the leading edge for the clean configuration. The furthest aft that transition was measured was 20 percent chord at M = 0.9 and M = 0.97. No change in transition location was observed after the addition of a notch-bump on the leading edge of the inboard side of the test section which was intended to minimize attachment line transition problems. Some flow visualization was attempted during the flight experiment with both subliming chemicals and liquid crystals. However, difficulties arose from the limited time the test aircraft was able to hold test conditions and the difficulty of positioning the photo chase aircraft during supersonic test points. Therefore, no supersonic transition results were obtained. Johnson, J. Blair Armstrong Flight Research Center RTOP 533-02-21...
Book Synopsis Boundary Layer Transition on a Sweptback Wing: Effect of Incidence by : P.R. Owen
Download or read book Boundary Layer Transition on a Sweptback Wing: Effect of Incidence written by P.R. Owen and published by . This book was released on 1953 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary-layer Transition and Displacement-thickness Effects on Zero-lift Drag of a Series of Power-law Bodies at Mach 6 by : George C. Ashby
Download or read book Boundary-layer Transition and Displacement-thickness Effects on Zero-lift Drag of a Series of Power-law Bodies at Mach 6 written by George C. Ashby and published by . This book was released on 1974 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Mach Number, Leading-edge Bluntness, and Sweep on Boundary-layer Transition on a Flat Plate/ by Don W. Jillie; Edward J. Hopkins by : Don W. Jillie
Download or read book Effects of Mach Number, Leading-edge Bluntness, and Sweep on Boundary-layer Transition on a Flat Plate/ by Don W. Jillie; Edward J. Hopkins written by Don W. Jillie and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of Trailing-edge Control Deflection on the Loading Over a 60 Deg Delta-wing-body Combination by :
Download or read book The Effect of Trailing-edge Control Deflection on the Loading Over a 60 Deg Delta-wing-body Combination written by and published by . This book was released on 1959 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Effects of Body Indentation and of Wing-plan-form Modification on the Longitudinal Characteristics of a 60 Degree Swept-wing Body Combination at Mach Numbers of 1.41, 1.61, and 2.01 by : John R. Jr Sevier
Download or read book Investigation of the Effects of Body Indentation and of Wing-plan-form Modification on the Longitudinal Characteristics of a 60 Degree Swept-wing Body Combination at Mach Numbers of 1.41, 1.61, and 2.01 written by John R. Jr Sevier and published by . This book was released on 1955 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Mach Numbers of 0.20 to 3.50 of a Blended Diamond Wing and Body Combination of Sonic Design But with Low Wave-drag Increase with Increasing Mach Number by : George H. Holdaway
Download or read book Investigation at Mach Numbers of 0.20 to 3.50 of a Blended Diamond Wing and Body Combination of Sonic Design But with Low Wave-drag Increase with Increasing Mach Number written by George H. Holdaway and published by . This book was released on 1959 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
