Download or read book Wind tunnel Investigation of NACA 66 215 216 66 1 212 and 651 212 Airfoils with 0 20 airfoil chord Split Flaps written by Felicien F. Fullmer and published by . This book was released on 1944 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation was carried out in the NACA two-dimensional low-turbulence pressure tunnel of the NACA 66(215)-216, 66,1-212, and 651-212 airfoil sections equipped with split flaps having chords 20 percent of the airfoil chord. The purpose was to determine the maximum-lift characteristics of these low-drag airfoil sections with split flaps. All the present tests were made at a Reynolds number of approximately 6 x 106 and a Mach number of about 0.15.

Download or read book Wind Tunnel Investigation of NACA 66 215 216 66 1 212 and 651 212 Airfoils with 0 20 Airfoil Chord Split Flaps Classic Reprint written by Felicien F. Fullmer Jr and published by Forgotten Books. This book was released on 2018-03-19 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Excerpt from Wind-Tunnel Investigation of Naca 66(215)-216, 66, 1 212, and 651-212 Airfoils With 0. 20 Airfoil-Chord Split Flaps Lanclev Memorial Aeronautical Laboratory National Advisory Committee for Aeronautics Langley Field, Va. About the Publisher Forgotten Books publishes hundreds of thousands of rare and classic books. Find more at www.forgottenbooks.com This book is a reproduction of an important historical work. Forgotten Books uses state-of-the-art technology to digitally reconstruct the work, preserving the original format whilst repairing imperfections present in the aged copy. In rare cases, an imperfection in the original, such as a blemish or missing page, may be replicated in our edition. We do, however, repair the vast majority of imperfections successfully; any imperfections that remain are intentionally left to preserve the state of such historical works.

Download or read book Wind tunnel Investigation of N A C A 66 215 216 66 1 212 and 651 212 Airfoils with 20 airfoil chord Split Flaps written by Jr. Felicien F. Fullmer and published by . This book was released on 1945 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of NACA 66 215 216 66 1 212 and 65 1 212 Airfoils with 0 20 airfoil chord Split Flaps written by Felicien F. Jr Fullmer and published by . This book was released on 1944 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Reports Having Application to Personal Aircraft written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1946 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of an NACA 23021 Airfoil with a 0 32 airfoil chord Double Slotted Flap written by Jack Fischel and published by . This book was released on 1944 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation was made in the LMAL 7- by 10-foot wind tunnel of an NACA 23021 airfoil with a double slotted flap having a chord 32 percent of the airfoil chord (0.32c) to determine the aerodynamic section characteristics with the flaps deflected at various positions. The effects of moving the fore flap and rear flap as a unit and of deflecting or removing the lower lip of the slot were also determined.

Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1948 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.

Download or read book Correlation of Cylinder head Temperatures and Coolant Heat Rejections of a Multicylinder Liquid cooled Engine of 1710 cubic inch Displacement written by Bruce T. Lundin and published by . This book was released on 1950 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of the Lift Characteristics of an NACA 27 212 Airfoil with Two Types of Flap written by Robert S. Swanson and published by . This book was released on 1940 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 27-212 airfoil with a 20-percent-chord split flap and with two arrangements of a 25.66-percent-chord slotted flap to determine the section lift characteristics as affected by flap deflection, flap position, and slot shape for the slotted flap. For the two arrangements of the slotted flap, the flap positions for maximum section lift are given. Comparable data on the NACA 23012 airfoil equipped with similar flaps are also given.

Download or read book Wind tunnel Investigation of Seven Thin NACA Airfoil Sections to Determine Optimum Double slotted flap Configurations written by Jones F. Cahill and published by . This book was released on 1948 with total page 75 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation was made to determine the optimum double-slotted-flap positions for NACA 63-210, 64-208, 64-210, 641-212, 65-210, 66-210, and 1410 airfoils. Optimum fore-flap positions were generally 1 percent chord forward and 3 percent chord below the slot lip. Optimum flap positions varied considerably. Maximum lifts decreased as position of minimum pressure moved to the rear and as thickness decreased. Scale-effect tests showed that maximum lifts increased as Reynolds number was increased from 2,400,000 to 6,000,000 and changed but slightly above 6,000,000.

Download or read book Wind tunnel Investigation of N A C A 23012 23021 and 23030 Airfoils with Various Sizes of Split Flap written by Carl Joseph Wenzinger and published by . This book was released on 1940 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigation of Control Surface Characteristics written by H. Page Hoggard and published by . This book was released on 1943 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force-test measurements in two-dimensional flow have been made in the NACA 4- by 6-foot vertical tunnel to determine the aerodynamic effects of changing the alignment of the cover plates on a sealed internally balanced flap. An NACA 0015 airfoil was utilized for the tests. The chord of the straight-contour flap was 30 percent of the airfoil chord and the balance with 50 percent of the flap chord.

Download or read book Wind tunnel Investigation of Control surface Characteristics written by H. Page Hoggard and published by . This book was released on 1944 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure-distribution tests have been made in the NACA 4- by 6-foot vertical tunnel of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The 15-percent bevel was tested with the bevel corner faired with both large and small radii. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of the horizontal and vertical tail surfaces.

Download or read book Wind tunnel Investigation of Control surface Characteristics written by M. Leroy Spearman and published by . This book was released on 1945 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Wind-tunnel tests have been made to determine the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap having a chord 25 percent of the airfoil chord and a balancing tab having a chord 50 percent of the airfoil chord or 200 percent of the flap chord so linked that the tab would deflect at a given rate with respect to the flap. Three linkage ratios were tested on the model. The tests indicated that the flap and tab could be linked to give hinge-moment balance with flap deflection and with angle of attack and yet have greater lift effectiveness than a plain flap of similar size with a conventional balancing tab having a chord 20 percent of the flap chord linked to give hinge-moment balance with flap deflection only.

Download or read book Two dimensional Wind tunnel Investigation of Two NACA Low drag Airfoil Sections Equipped with Slotted Flaps and a Plain NACA Low drag Airfoil Section for XF6U 1 Airplane written by Lawrence K. Loftin and published by . This book was released on 1946 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: A two-dimensional wind-tunnel investigation was conducted to determine the aerodynamic characteristics of the NACA 65(215)-114 airfoil (root section), the NACA 65,1-212, a = 0.6, airfoil (tip section), and an intermediate airfoil section of the Chance-Vought XF6U-1 airplane.