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Pressure Distribution Test Of Sharp Leading Edge Wing And Wing Body Combinations At Mach 21
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Book Synopsis Pressure Distribution Test of Sharp Leading-edge Wing and Wing-body Combinations at Mach 21 by : P. C. SHELTON
Download or read book Pressure Distribution Test of Sharp Leading-edge Wing and Wing-body Combinations at Mach 21 written by P. C. SHELTON and published by . This book was released on 1961 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distribution tests were made on a delta wing model and two wing-body combinations, all with sharp leading edges, in tunnel Hotshot 2 at a Mach number of 21 and a Reynolds number per foot of 400,000. Angle of attack ranged from -5 to +20 deg. Typical spanwise pressure distributions on the flat lower surface of model W4 are shown. It is observed that the pressure increases near the leading edge. The effect of adding the body to model W4 to obtain model W4B1 increases the pressure considerably over the entire lower surface. The spanwise pressure distribution of model (W-B)1 on the upper and lower surfaces is also shown. (Author).
Book Synopsis Pressure Distribution Tests of Several Sharp Leading Edge Wings, Bodies, and Body-wing Combinations at Mach 5 and 8 by : R. E. Randall
Download or read book Pressure Distribution Tests of Several Sharp Leading Edge Wings, Bodies, and Body-wing Combinations at Mach 5 and 8 written by R. E. Randall and published by . This book was released on 1960 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distribution data were obtained on several sharp leading edge wings, conical bodies, and body-wing combinations at Mach 5 and 8. Shadowgraphs of shock wave and boundary layer phenomena were obtained at various angles of attack. Vapor screen photographs were taken with liquefied flow conditions in the test section to visualize the cross-sectional shape of the shock wave.
Book Synopsis Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 by : Barry Moskowitz
Download or read book Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 written by Barry Moskowitz and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
Book Synopsis Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 by : Harold Mirels
Download or read book Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 written by Harold Mirels and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Book Synopsis Force Tests of Several Sharp Leading Edge Wing-body Combinations at Mach 8 by : C. G. BURCHFIELD
Download or read book Force Tests of Several Sharp Leading Edge Wing-body Combinations at Mach 8 written by C. G. BURCHFIELD and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data were obtained on several, sharp leading edge, wing-body combinations to support a theoretical investigation by the Grumman Aircraft Engineering Corporation. Forces and moments were determined at Mach 8 and at a unit Reynolds number of 2 x 10 to the -6th power per foot. Data were also obtained on a few models at a Reynolds number of 0.8 x 10 to the -6th power per foot. All models were pitched from -10 to +20 deg. Two of the models were yawed from -3 to +15 deg while the pitch was held at a constant zero deg. (Author).
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 828 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on with total page 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Pressure-distribution Investigation of Interference Effects Produced at a Mach Number of 3.11 by Wedge- Shaped Bodies Located Under a Triangular Wing by : Lowell E. Hasel
Download or read book An Experimental Pressure-distribution Investigation of Interference Effects Produced at a Mach Number of 3.11 by Wedge- Shaped Bodies Located Under a Triangular Wing written by Lowell E. Hasel and published by . This book was released on 1959 with total page 120 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 Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1962 with total page 1990 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1974 with total page 804 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Determination of the Pressure Distribution on a Rectangular Wing Oscillating in the First Bending Mode for Mach Numbers from 0.24 to 1.30 by : Henry C. Lessing
Download or read book Experimental Determination of the Pressure Distribution on a Rectangular Wing Oscillating in the First Bending Mode for Mach Numbers from 0.24 to 1.30 written by Henry C. Lessing and published by . This book was released on 1960 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Prediction of Pressures in Hypersonic Flow with Special Reference to Configurations Having Attached Leading-edge Shock by : Harold R. Mead
Download or read book Theoretical Prediction of Pressures in Hypersonic Flow with Special Reference to Configurations Having Attached Leading-edge Shock written by Harold R. Mead and published by . This book was released on 1962 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of tests which are part of an experimental hypersonic research program designed to support an investigation of new theoretical means for the prediction of pressures on attached-shock configurations at hypersonic speeds. The data obtained include six-component force data at Mach 8 for seven configurations which were previously pressure tested at Mach 5 and 8 under the original program. The force tests were run in tunnel B of the Von Karman Facility of the Arnold Engineering Development Center. The ranges of test variables were: angle of attack, -10 degrees to 20 degrees; angle of yaw, -3 degrees to 15 degrees; Reynolds number per foot, 0.8 and 2.0 x 10(superscript 6). Data were also obtained at a nominal Mach number of 21 for three pressure instrumented configurations tested earilier at Mach 5 and 8 under the original program. The tests were run in tunnel HS-2 of the Von Karman Facility. Pitch data were measured over the angle of attack range -5 degrees to 20 degrees at a Reynolds number per foot of approximately 4X10(superscript 6). Some of the measured pressures are compared with thin-shock-layer thoery, Newtonian pressure formula, equivalent-cone and tangent-wedge approximations with the thin-shock-layer theory being generally superior in appropriate applications.
Book Synopsis Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta and Arrow Plan Forms by : George H. Holdaway
Download or read book Investigation at Mach Numbers of 0.20 to 3.50 of Blended Wing-body Combinations of Sonic Design with Diamond, Delta and Arrow Plan Forms written by George H. Holdaway and published by . This book was released on 1960 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distribution and Flow Visualization Tests of a 1.5 Elliptic Cone at Mach 10 by : R. L. Palko
Download or read book Pressure Distribution and Flow Visualization Tests of a 1.5 Elliptic Cone at Mach 10 written by R. L. Palko and published by . This book was released on 1963 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for tests conducted on a 1.5 elliptic cone to determine the pressure distribution, flow streamlines, and shock wave shape at high angles of attack. The tests were performed at a Mach number of 10 and a freestream unit Reynolds number of 1.6 x 10 to the 6th power per foot. The angle-of-attack range was from 0 to 60 deg. The model was oriented both with the major and the minor axis of the ellipse located in the pitch plane.
Book Synopsis Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 by : Marvin Kussoy
Download or read book Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 written by Marvin Kussoy and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :United States. National Aeronautics and Space Administration Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :472 pages Book Rating :4.F/5 ( download)
Book Synopsis NASA Scientific and Technical Reports by : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on with total page 472 pages. Available in PDF, EPUB and Kindle. Book excerpt:
