AN EXPERIMENTAL INVESTIGATION OF THE SURFACE PRESSURE AND THE LAMINAR BOUNDARY LAYER ON A BLUNT FLAT PLATE IN HYPERSONIC FLOW. VOL 1. SURFACE PRESSURE DISTRIBUTIONS ON A BLUNTED FLAT PLATE.

AN EXPERIMENTAL INVESTIGATION OF THE SURFACE PRESSURE AND THE LAMINAR BOUNDARY LAYER ON A BLUNT FLAT PLATE IN HYPERSONIC FLOW. VOL 1. SURFACE PRESSURE DISTRIBUTIONS ON A BLUNTED FLAT PLATE. PDF Author:
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Category :
Languages : en
Pages : 115

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Book Description
Pressures were measured over the surface of an unswept blunt flat plate having a cylindrical leading edge 1/2-inch in diameter. The flat plate was side-mounted in the ALOSU 12-inch continuous hypersonic wind tunnel. Separate tests were conducted with cylinders in order to obtain detailed data for the leading-edge. Stagnation temperatures were sufficiently high to eliminate condensation effects. The leading edge and cylinder pressure ratios were noted to be independent of both Mach number and Reynolds number. The flat plate pressure ratios show a small dependence on Mach number. Reynolds number effects on the plate pressure ratios were small except at the lower levels of Reynolds number where the interaction of the thickened boundary layer caused increases in pressure.

An Experimental Investigation of the Surface Pressure and the Laminar Boundary Layer on a Blunt Flat Plate in Hypersonic Flow: Surface pressure distributions on a blunted flat plate

An Experimental Investigation of the Surface Pressure and the Laminar Boundary Layer on a Blunt Flat Plate in Hypersonic Flow: Surface pressure distributions on a blunted flat plate PDF Author: G. M. Gregorek
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 124

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Book Description
Vol. 1 Pressures were measured over the surface of an unswept blunt flat plate having a cylindrical leading edge 1/2-inch in diameter. The flat plate was side-mounted in the ALOSU 12-inch continuous hypersonic wind tunnel. Separate tests were conducted with cylinders in order to obtain detailed data for the leading-edge. Stagnation temperatures were sufficiently high to eliminate condensation effects. The leading edge and cylinder pressure ratios were noted to be independent of both Mach number and Reynolds number. The flat plate pressure ratios show a small dependence on Mach number. Reynolds number effects on the plate pressure ratios were small except at the lower levels of Reynolds number where the interaction of the thickened boundary layer caused increases in pressure.

AN EXPERIMENTAL INVESTIGATION OF THE SURFACE PRESSURE AND THE LAMINAR BOUNDARY LAYER ON A BLUNT FLAT PLATE IN HYPERSONIC FLOW. VOLUME 2. LAMINAR BOUNDARY LAYER PROFILE ON THE FLAT PLATE.

AN EXPERIMENTAL INVESTIGATION OF THE SURFACE PRESSURE AND THE LAMINAR BOUNDARY LAYER ON A BLUNT FLAT PLATE IN HYPERSONIC FLOW. VOLUME 2. LAMINAR BOUNDARY LAYER PROFILE ON THE FLAT PLATE. PDF Author:
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Category :
Languages : en
Pages : 119

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The laminar boundary layer on unswept, 1/2-inch thick, cylindrically- blunted flat plate was examined at Mach numbers of 7, 10, 12 and 14; at Reynolds numbers from 9000 to 21,300, based on the plate thickness; and at angles-of- attack of 0, 10 (compression) and 15 degrees (expansion). The layer was probed at three stations, S/D = 8, 16 and 22 using a pitot probe and a sonic-pneumatic total temperature probe. The tests were conducted in the 12-inch continuous hypersonic wind tunnel of the Ohio State University Aerodynamic Laboratory. The two probe outputs, together with the static pressure at the wall, were processed through an analogue computer and the results, i.e., Mach number, velocity, temperature, etc., are tabulated as functions of distance from the surface. Integrations were performed to obtain displacement and momentum thicknesses. Skin friction was also obtained, through the measurement of the velocity gradient at the wall. The results are presented in tabulated form, while typical data are plotted to illustrate the trends established by Mach number, Reynolds number and angle-of-attack.

An Experimental Investigation of the Surface Pressure and the Laminar Boundary Layer on a Blunt Flat Plate in Hypersonic Flow: Laminar boundary layer profile on the flat plane

An Experimental Investigation of the Surface Pressure and the Laminar Boundary Layer on a Blunt Flat Plate in Hypersonic Flow: Laminar boundary layer profile on the flat plane PDF Author: G. M. Gregorek
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 126

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Book Description
Vol. 1 Pressures were measured over the surface of an unswept blunt flat plate having a cylindrical leading edge 1/2-inch in diameter. The flat plate was side-mounted in the ALOSU 12-inch continuous hypersonic wind tunnel. Separate tests were conducted with cylinders in order to obtain detailed data for the leading-edge. Stagnation temperatures were sufficiently high to eliminate condensation effects. The leading edge and cylinder pressure ratios were noted to be independent of both Mach number and Reynolds number. The flat plate pressure ratios show a small dependence on Mach number. Reynolds number effects on the plate pressure ratios were small except at the lower levels of Reynolds number where the interaction of the thickened boundary layer caused increases in pressure.

The Flow Field Over Blunted Flat Plates and Its Effect on Turbulent Boundary-layer Growth and Heat Transfer at a Mach Number of 4.7

The Flow Field Over Blunted Flat Plates and Its Effect on Turbulent Boundary-layer Growth and Heat Transfer at a Mach Number of 4.7 PDF Author: Thorval Tendeland
Publisher:
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 64

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Technical Abstract Bulletin

Technical Abstract Bulletin PDF Author:
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ISBN:
Category : Science
Languages : en
Pages : 684

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
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Category : Aeronautics
Languages : en
Pages : 1126

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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

NASA Technical Note

NASA Technical Note PDF Author:
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ISBN:
Category :
Languages : en
Pages : 452

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U.S. Government Research Reports

U.S. Government Research Reports PDF Author:
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Category : Science
Languages : en
Pages : 814

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Keywords Index to U.S. Government Technical Reports (permuted Title Index).

Keywords Index to U.S. Government Technical Reports (permuted Title Index). PDF Author: United States. Department of Commerce. Office of Technical Services
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Category : Government publications
Languages : en
Pages : 618

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