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:

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:

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:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1967 with total page 1206 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Boundary layer Transition on Swept Wings at Mach Numbers 2 5 to 5 written by S. R. Pate and published by . This book was released on 1963 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 12-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine boundary-layer transition locations on swept wings having a circular arc profile and modified arc profile. Test Mach numbers were from 2.5 to 5 over a Reynolds-number-per-inch range from 0.14 to 1. 08 million at sweep angles of 24, 36, and 50 deg for angles of attack of 0 and approximately -4 deg. Boundary-layer transition Reynolds numbers determined by a pitot probe, and results obtained visually with a sub limable solid are presented. The major factors influencing boundary-layer transition were wing sweep and model leading edge geometry. Increasing wing sweep and leading edge bluntness above a sweep angle of approximately 20 deg decreased the transition Reynolds number at all test Mach numbers.

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.

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:

Download or read book Effects of Sweep and Angle of Attack on Boundary layer Transition on Wings at Mach Number 4 04 written by Robert W. Dunning and published by . This book was released on 1955 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: The data showed that transition always occurred along a front parallel to the wing leading edge, and that increasing the leading-edge sweep angle or increasing the angle of attack between the undisturbed stream and model surface caused the transition line to move closer to the wing leading edge and, in general, decreased the transition Reynolds number.

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:

Download or read book Some Effects of Leading edge Sweep on Boundary layer Transition at Supersonic Speeds written by Gary T. Chapman and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Engineering Index written by and published by . This book was released on 1954 with total page 1212 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book Aerospace Engineering written by and published by . This book was released on 1958-05 with total page 1236 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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).

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...

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: