Download or read book An Experimental Investigation of Leading edge Flow Separation from a 4 Percent Thick Two dimensional Biconvex Aerofoil written by Aeronautical Research council and published by . This book was released on 1958 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Leading edge Flow separation from a 4 Thick Two dimensional Biconvex Aerofoil written by B. D. Henshall and published by . This book was released on 1957 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Leading edge Flow Separation from a 4 Percent Thick Two dimensional Biconvex Aerofoil written by Aeronautical Research council and published by . This book was released on 1958 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Laminar flow Separation on a Flat Plate Induced by Deflected Trailing edge Flap at Mach 19 written by Bill Harvey and published by . This book was released on 1968 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Publications Announcements with Indexes written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 1318 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Regions of Separated Laminar Flow written by Donald E. Gault and published by . This book was released on 1955 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented from an investigation of regions of separated flow caused by separation of the laminar boundary layer (laminar-separation "bubbles"). The investigation was undertaken to obtain measurements which would define a large number of these bubbles for a wide range of Reynolds numbers and pressure gradients. In this manner, existing physical interpretations of the flow along a bubble could be studied in greater detail than in the past and, at the same time, it was hoped that the data would provide further insight into the conditions which control the occurrence and extent of a bubble.
Download or read book Reports and Memoranda written by and published by . This book was released on 1963 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt: Beginning with no. 650 each hundredth number contains a list of the Reports and memoranda published since the last list.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1973 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Flow Separation on a Two dimensional Flat Plate Haveing a Variable san Trailing edge Flap at M free Stream written by S. R. Pate and published by . This book was released on 1964 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Low speed Experimental Investigation of a Thin Faired Double wedge Airfoil Section with Nose and Trailing edge Flaps written by Leonard M. Rose and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A faired, double-wedge airfoil section, 4.23 percent thick, was investigated with plain nose and trailing-edge flaps. The nose flap was 0.16 chord of the airfoil and the trailing-edge flap was 0.25 chord of the airfoil. Section lift, drag, and pitching-momnet data are presented for a Reynolds number of 5,800,000 which corresponded to a Mach number of 0.17.
Download or read book A Low Speed Two dimensional Study of Flow Separation on the GA W 1 Airfoil with 30 percent Chord Fowler Flap written by H. C. Seetharam and published by . This book was released on 1977 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of the Leading Edge Separation Bubble written by Anthony Vincent Arena and published by . This book was released on 1978 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Qualitative Discussion on the Development of Leading edge Flow separation for a 6 Thick Two dimensional Aerofoil at M written by H. H. Pearcey and published by . This book was released on 1955 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of the Flow Around Lifting Symmetrical Double wedge Airfoils at Mach Numbers of 1 30 and 1 41 written by Paul B. Gooderum and published by . This book was released on 1956 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements were made of the flow around a 10-percent-thick, double symmetrical, two-dimensional wedge at a Mach number of 1.30 and of a 14.2-percent-thick wedge at Mach numbers of 1.30 and 1.41 for various angles of attack up to 5 degrees. Results were thus obtained in the vicinity of the theoretically interesting region between shock attachment and the lower limit for completely supersonic flow over the surface of the airfoil. Pressure and Mach number distributions, lift and drag coefficients, center of lift, and pitching moment are presented for the angles of attack used. By means of the transonic similarity laws, the results are compared with each other, with small-disturbance theory, and with shock-expansion theory wherever possible. The data show that pressure distributions on wedges of different thickness and Mach number are similar at the same values of transonic similarity parameter and reduced angle of attack for angles of attack as large as the thickness ratio; that the lift-curve slope is approximately independent of the angle of attack for an angle-of-attack range from -2 degrees to 2 degrees; and that, for the airfoils tested at Mach numbers greater than the attachment value, the center-of-pressure location is nearly independent of the angle of attack, the variation being to plus or minus 3 percent chord for the angles of attack used in this investigation. For the airfoil tested at a Mach number slightly less than the shock-attachment value, the center-of-pressure location was only roughly independent of the angle of attack, the variation of this location being to plus or minus 6 percent chord.
Download or read book Experimental Studies of Flow Separation and Stalling on a Two dimensional Airfoil at Low Speeds written by H. C. Seetharam and published by . This book was released on 1975 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aero space Engineering written by and published by . This book was released on 1959 with total page 1386 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wasserhaushalt Binnengew sser hohe See u K nstengew sser written by and published by . This book was released on 1971 with total page 215 pages. Available in PDF, EPUB and Kindle. Book excerpt:
