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Author : F. H. Kelling
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (489 download)
Download or read book Experimental Investigation of a High-lift Low-drag Aerofoil written by F. H. Kelling and published by . This book was released on 1971 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Michael S. Selig
Publisher : Soartech
ISBN 13 :
Total Pages : 320 pages
Book Rating : 4.F/5 ( download)
Download or read book Summary of Low Speed Airfoil Data written by Michael S. Selig and published by Soartech. This book was released on 1995 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : G. M. Graham
Publisher :
ISBN 13 :
Total Pages : 102 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Experimental Investigation of High Lift/high Rate Aerodynamics of an Unsteady Airfoil written by G. M. Graham and published by . This book was released on 1989 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Kim Fong Yeow
Publisher :
ISBN 13 :
Total Pages : 194 pages
Book Rating : 4.:/5 (29 download)
Download or read book An Experimental Investigation of High Rate/high Lift Aerodynamics of an Unsteady Airfoil written by Kim Fong Yeow and published by . This book was released on 1989 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Leonard M. Rose
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.3/5 (91 download)
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.
Author : Richard E. Walters
Publisher :
ISBN 13 :
Total Pages : 128 pages
Book Rating : 4.:/5 (227 download)
Download or read book An Experimental Investigation of an Airfoil Optimized for High Lift written by Richard E. Walters and published by . This book was released on 1974 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was performed on an airfoil optimized for maximum lift. The airfoil shape was designed from an optimum pressure distribution using a calculus of variation technique. The purpose of the investigation was to evaluate the validity of the method of design of the airfoil, and to determine what type of differences existed, if any, in the theoretical and experimental results. The airfoil was tested at a Reynolds number approximating the design Reynolds number of 1,000,000. The airfoil angle of attack was varied in 2 deg increments from 0 deg to 12 deg. At each angle of attack, three blowing rates were used for slots installed on the model end plates. Data recorded for each test run consisted of the airfoil static pressure distribution, static and total pressures from a wake traverse, atmospheric pressure and temperature, and the tunnel temperature. Normal and chordwise force coefficients were obtained from the static pressure data. Using the true angles of attack from potential flow theory, lift and pressure drag coefficients were found. Total drag coefficients were found from the wake traverse data. Increased blowing caused the experimental pressure coefficient distributions at higher angles of attack to come into close agreement with the theoretical pressure coefficient distribution, and resulted in increased lift and decreased drag. True two-dimensional flow was not maintained at the higher angles of attack, due at least in part to the test installation. (Author).
Author : Michael S. Selig
Publisher :
ISBN 13 :
Total Pages : 424 pages
Book Rating : 4.F/5 ( download)
Download or read book Airfoils at Low Speeds written by Michael S. Selig and published by . This book was released on 1989 with total page 424 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Robert Wellington Hovey
Publisher :
ISBN 13 :
Total Pages : 100 pages
Book Rating : 4.:/5 (253 download)
Download or read book Experimental Investigation of the Lift of Airfoils in Pitching Oscillation written by Robert Wellington Hovey and published by . This book was released on 1942 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : C.J. Davidson
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book The Experimental Investigation of the Effects of Roughness Upon Aerofoil Characteristics at Low Reynolds Numbers written by C.J. Davidson and published by . This book was released on 1985 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Clarence A. Syvertson
Publisher :
ISBN 13 :
Total Pages : 31 pages
Book Rating : 4.:/5 (254 download)
Download or read book An Experimental Investigation of the Zero-lift-drag Characteristics of Symmetrical Blunt-trailing-edge Airfoils at Mach Numbers from 2.7 to 5.0 written by Clarence A. Syvertson and published by . This book was released on 1953 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 606 pages
Book Rating : 4.:/5 (319 download)
Download or read book NASA Technical Paper written by and published by . This book was released on 1986 with total page 606 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Herman S. Fletcher
Publisher :
ISBN 13 :
Total Pages : 25 pages
Book Rating : 4.:/5 (249 download)
Download or read book Experimental Investigation of Lift, Drag, and Pitching Moment of Five Annular Airfoils written by Herman S. Fletcher and published by . This book was released on 1957 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was carried out in the Langley stability tunnel to determine the lift, drag, and pitching-moment characteristics, of a family of annular airfoils. The five annular airfoils had equal projected areas buy had varying chords and diameters which covered aspect ratios of 1/3, 2/3, 1.0, 1.5, and 3.0.
Author :
Publisher :
ISBN 13 :
Total Pages : 704 pages
Book Rating : 4.:/5 (31 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Paul B. Gooderum
Publisher :
ISBN 13 :
Total Pages : 86 pages
Book Rating : 4.:/5 (249 download)
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.
Author : Dan M. Somers
Publisher :
ISBN 13 :
Total Pages : 108 pages
Book Rating : 4.:/5 (31 download)
Download or read book Design and Experimental Results for a Natural-Laminar-Flow Airfoil for General Aviation Application written by Dan M. Somers and published by . This book was released on 1981 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: A natural-laminar-flow airfoil for general aviation applications, the NLF(1)-0416, was designed and analyzed theoretically and verified experimentally in the Langley Low-Turbulence Pressure Tunnel. The basic objective of combining the high maximum lift of the NASA low-speed airfoils with the low cruise drag of the NACA 6-series airfoils was achieved. The safety requirement that the maximum lift coefficient not be significantly affected with transition fixed near the leading edge was also met. Comparisons of the theoretical and experimental results show excellent agreement. Comparisons with other airfoils, both laminar flow and turbulent flow, confirm the achievement of the basic objective.
Author :
Publisher :
ISBN 13 :
Total Pages : 340 pages
Book Rating : 4.:/5 (317 download)
Download or read book Laminar Flow Aircraft Certification written by and published by . This book was released on 1986 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Redha Wahidi
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (691 download)
Download or read book An Experimental Investigation of Airfoils with Laminar Separation Bubbles and Effects of Distributed Suction written by Redha Wahidi and published by . This book was released on 2009 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: In an effort to understand the behavior of the laminar separation bubbles on NACA 0012 and Liebeck LA2573a airfoils at different Reynolds numbers and angles of attack, the boundary layers on the solid airfoils were investigated by measuring the mean and fluctuating components of the velocity profiles over the upper surfaces of the airfoils. Surface pressure measurements were carried out to complete the mapping of the laminar separation bubble and to calculate the lift generated by the airfoils. The experiments were carried out at Reynolds numbers of 150,000 and 250,000. The locations of separation, transition and reattachment were determined as functions of angle of attack and Reynolds number for the two airfoils. The drag was estimated from wake pressure measurements based on the momentum deficit generated by the airfoil. The size and location of the laminar separation bubble on the LA2573a airfoil did not show significant changes with Reynolds number and angle of attack for values of the angle of attack between 0 and 6 degrees. The baseline results of the size and location of the laminar separation bubble on the LA2573a airfoil were used to design a suction distribution. This suction distribution was designed based on Thwaites' criterion of separation. The effects of applying suction on the size and location of the laminar separation bubble were investigated. The results showed that the suction distribution designed in this work was effective in controlling the size of the laminar separation bubble, maintaining an unseparated laminar boundary layer to the transition point, and controlling the location of transition. The effects of different suction rates and distributions on the drag were investigated. Drag reductions of 14-24% were achieved. A figure of merit was defined as drag reductions divided by the equivalent suction drag to assess the worthiness of utilizing suction on low Reynolds number flows. The values of the figure of merit were around 4.0 which proved that the penalty of using suction was significantly less than the gain obtained in reducing the drag.
