Experimental Investigation of the Flow about the Leading Edge of a Flat Plate
Author : Jaan Alfred Laurmann
Publisher :
Page : 44 pages
File Size : 27,59 MB
Release : 1954
Category :
ISBN :
Experimental Investigation of Laminar-flow Separation on a Flat Plate Induced by Deflected Trailing-edge Flap at Mach 19
Author : Bill Harvey
Publisher :
Page : 60 pages
File Size : 46,42 MB
Release : 1968
Category : Flaps (Airplanes)
ISBN :
Book Description
Experimental Investigation of Boundary Layer Transition on a Flat Plate with a Point Heat Source at the Leading Edge
Author : W. J. McCroskey
Publisher :
Page : 40 pages
File Size : 34,10 MB
Release : 1962
Category :
ISBN :
Book Description
The addition of heat to the boundary layer of an insulated flat plate by means of a point heat source at the leading edge has been found to delay the transition of laminar flow to turbulence. This paper describes an experimental investigation of the variation of transition Reynolds number on a roughened flat plate model with a heat source of strength, Q, spanning the leading edge. The present problem is compared with the problem of an aerodynamically heated boundary layer on an insulated flat plate. Transition Reynolds number was found to increase with increasing S over a range equivalent to a Mach number variation of 0
Theoretical and Experimental Investigation of Supercavitating Hydrofoils Operating Near the Free Water Surface
Author : Virgil E. Johnson
Publisher :
Page : 84 pages
File Size : 26,81 MB
Release : 1961
Category : Cavitation
ISBN :
Book Description
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
Author : G. M. Gregorek
Publisher :
Page : 126 pages
File Size : 28,75 MB
Release : 1963
Category : Aerodynamics, Hypersonic
ISBN :
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 Effect of the Angle of Attack and the Leading Edge Thickness on the Heat Transfer Rate to a Flat Plate at M
Author : Hossein Parsapour
Publisher :
Page : pages
File Size : 25,67 MB
Release : 1967
Category :
ISBN :
Book Description
NASA Technical Note
Author :
Publisher :
Page : 392 pages
File Size : 20,75 MB
Release : 1968
Category :
ISBN :
Book Description
NASA Memorandum
Author : United States. National Aeronautics and Space Administration
Publisher :
Page : 590 pages
File Size : 10,94 MB
Release : 1959
Category : Aeronautics
ISBN :
Book Description
Experimental Investigation of Boundary Layer Behavior in a Simulated Low Pressure Turbine
Author : Ki-Hyeon Sohn
Publisher :
Page : 16 pages
File Size : 26,88 MB
Release : 1998
Category : Boundary layers
ISBN :
Book Description
Investigation of Flow Separation on a Two-dimensional Flat Plate Haveing a Variable-san Trailing-edge Flap at M [free Stream]
Author : S. R. Pate
Publisher :
Page : 46 pages
File Size : 37,54 MB
Release : 1964
Category : Laminar boundary layer
ISBN :
Book Description
An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional flat plate having a variable-span trailing edge flap in the 12-in. Supersonic Tunnel (D) of the von Karman Gas Dynamics Facility. The tests were made at Mach numers 3 and 5 at zero angle of attack and over a Reynolds number range (based on plate length) from 0.26 to 16.7 x 10 to the 6th power. Model surface pressure distributions, schlieren photographs, and velocity distributions are presented. The effects of unit Reynolds number, plate length, flap span, and flap deflection angle on the separated region are investigated, and comparisons are made with existing theory.
