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An Investigation Of The Section Characteristics Of Plain Unsealed Ailerons On An Naca 661 115 Airfoil Section In The Langley 8 Foot High Speed Tunnel
Download An Investigation Of The Section Characteristics Of Plain Unsealed Ailerons On An Naca 661 115 Airfoil Section In The Langley 8 Foot High Speed Tunnel full books in PDF, epub, and Kindle. Read online An Investigation Of The Section Characteristics Of Plain Unsealed Ailerons On An Naca 661 115 Airfoil Section In The Langley 8 Foot High Speed Tunnel ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis An Investigation of the Section Characteristics of Plain Unsealed Ailerons on an NACA 66,1-115 Airfoil Section in the Langley 8-foot High-speed Tunnel by : Arvo A. Luoma
Download or read book An Investigation of the Section Characteristics of Plain Unsealed Ailerons on an NACA 66,1-115 Airfoil Section in the Langley 8-foot High-speed Tunnel written by Arvo A. Luoma and published by . This book was released on 1949 with total page 65 pages. Available in PDF, EPUB and Kindle. Book excerpt: Contains section characteristics, including airfoil normal-force, airfoil pitching-moment, aileron normal force, the aileron hinge-moment coefficients, for an NACA 66,1-115 airfoil section equipped with unsealed 20-percent-chord plain ailerons of true-airfoil-contour profile and 30 degrees beveled-trailing-edge profile, for Mach numbers up to 0.75.
Book Synopsis Wind-tunnel Investigation of Aileron Effectiveness of 0.20-airfoil-chord Plain Ailerons of True Airfoil Contour on NACA 652-415, 653-418 and 654-421 Airfoil Sections by : Albert L. Braslow
Download or read book Wind-tunnel Investigation of Aileron Effectiveness of 0.20-airfoil-chord Plain Ailerons of True Airfoil Contour on NACA 652-415, 653-418 and 654-421 Airfoil Sections written by Albert L. Braslow and published by . This book was released on 1944 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation was made in the NACA two-dimensional low-turbulence pressure tunnel to determine the aileron effectiveness of 0.20-airfoil-chord plain ailerons of true airfoil contour on the NACA 652-415, 653-418, and 654-421 airfoil sections. The aileron effectiveness parameter (change in section angle of attack with aileron deflection at constant lift coefficient) decreased very slightly with an increase in airfoil thickness from 15 percent to 21 percent. At higher deflections of the ailerons and higher section angles of attack, the increment of section lift coefficient due to aileron deflection was more appreciably reduced with an increase of airfoil thickness than was the aileron effectiveness parameter.
Book Synopsis An Investigation of a High-aspect-ratio Wing Having 0.20-chord Plain Ailerons in the Langley 8-foot High-speed Tunnel by : Arvo A. Luoma
Download or read book An Investigation of a High-aspect-ratio Wing Having 0.20-chord Plain Ailerons in the Langley 8-foot High-speed Tunnel written by Arvo A. Luoma and published by . This book was released on 1946 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of Ailerons on a Low-drag Airfoil by : Robert M. Crane
Download or read book Wind-tunnel Investigation of Ailerons on a Low-drag Airfoil written by Robert M. Crane and published by . This book was released on 1944 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the Ames Aeronautical Laboratory 7- by 10-foot wind tunnel of the effects of various modifications to the profile of a 0.20-chord plain sealed aileron on an NACA 66,2-216 (a = 0.6) airfoil.
Book Synopsis Two-dimensional Wind-tunnel Investigation of 0.20-airfoil-chord Plain Ailerons of Different Contour on an NACA 651-210 Airfoil Section by : William J. Underwood
Download or read book Two-dimensional Wind-tunnel Investigation of 0.20-airfoil-chord Plain Ailerons of Different Contour on an NACA 651-210 Airfoil Section written by William J. Underwood and published by . This book was released on 1945 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation was made of three interchangeable sealed-gap 0.20-airfoil-chord plain ailerons of different contour on the NACA 651-210 airfoil section. The three aileron contours tested were the true airfoil contour, straight sides, and a beveled trailing edge. The effects of aileron contour on the section aerodynamic characteristics of the airfoil and aileron are presented herein.
Book Synopsis Wind-tunnel Investigation of Ailerons on a Low-drag Airfoil by : Robert M. Crane
Download or read book Wind-tunnel Investigation of Ailerons on a Low-drag Airfoil written by Robert M. Crane and published by . This book was released on 1944 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the Ames Aeronautical Laboratory 7- by 10-foot wind tunnel of the effects of a trailing edge of a 0.20-chord plain sealed aileron on an NACA 66,2-216 (a = 0.6) airfoil.
Book Synopsis Investigation at Transonic Speeds of the Hinge-moment Characteristics of a 1/8-scale Model of the X-1E Aileron by : William C. Moseley (Jr.)
Download or read book Investigation at Transonic Speeds of the Hinge-moment Characteristics of a 1/8-scale Model of the X-1E Aileron written by William C. Moseley (Jr.) and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Tests of a Blunt-nose Aileron with Beveled Trailing Edge on an NACA 66(215)-216 Airfoil with Several Modifications of Aileron Nose and Adjacent Airfoil Contour by : J. D. Bird
Download or read book Wind-tunnel Tests of a Blunt-nose Aileron with Beveled Trailing Edge on an NACA 66(215)-216 Airfoil with Several Modifications of Aileron Nose and Adjacent Airfoil Contour written by J. D. Bird and published by . This book was released on 1945 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Ailerons having a beveled trailing edge and a blunt-nose overhand of 35 percent aileron chord on an NACA 66(215)-216 airfoil have been tested in the two-dimensional-flow test section of the Langley stability tunnel. Five configurations of the model were tested with various modifications of the aileron nose and adjacent airfoil contour to determine the effect of these modifications on the lift and aileron hinge-moment characteristics. The results indicated that making the nose of the aileron more elliptical decreased the balance of hinge moments at small aileron angels and increased the balance of hinge moments at large aileron angles. The lift coefficients, especially at large aileron angles, were increased by this modification. Flaring the airfoil contour near the aileron nose had an effect on the hinge moments for small aileron angles similar to the effect of making the aileron nose less blunt, whereas rounding the airfoil contour had an effect similar to making the aileron nose more blunt. Flaring the airfoil contour caused a decrease in the lift resulting from aileron deflection. The effects of airfoil-contour changes were small at large aileron angles. Comparison with other data indicated that, for small aileron angels, the increments of hinge-moment coefficient resulting from a beveled trailing edge and a blunt-nose overhang were additive.
Book Synopsis A Effect of Leakage Past Aileron Nose on Aerodynamic Characteristics of Plain and Internally Balanced Ailerons on NACA 66(215)-216 by : J. D. Bird
Download or read book A Effect of Leakage Past Aileron Nose on Aerodynamic Characteristics of Plain and Internally Balanced Ailerons on NACA 66(215)-216 written by J. D. Bird and published by . This book was released on 1945 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation has been made in two-dimensional flow to determine the effect of leakage past the aileron nose on the aerodynamic characteristics of ailerons. Plain and internally balanced ailerons of 0.20 airfoil chord were tested on an NACA 66(215)-216, a-1.0 airfoil. The effects of amount and type of leakage, aileron contour, and Mach number and Reynolds number were investigated. The results of the tests indicated that a small amount of leakage area changed the pressure distributions over the plain and internally balanced ailerons markedly. This change generally resulted in negative increments in the lift and hinge-moment parameters c [subscript l] subscript [delta], c [subscript h] subscript [alpha], and c [subscript h] subscript [delta]. A further increase in the leakage area produced smaller changes in these parameters for the internally balanced aileron.
Book Synopsis Investigation of the Hinge-Moment Fluctuations of a 0.20-Chord Plain Ailerons on a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed-Tunnel by :
Download or read book Investigation of the Hinge-Moment Fluctuations of a 0.20-Chord Plain Ailerons on a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed-Tunnel written by and published by . This book was released on 1947 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: Photographic records of hinge moment fluctuations were made by means of an oscillograph connected to an electrical strain gage. At super critical Mach numbers, frequencies of the order of magnitude of 50 to 100 cycles per second were observed for the hinge-moment fluctuations of the aileron of the model. For a 104.5 foot span airplane, full scale hinge-moment-fluctuation frequencies are indicated to be of the same order of magnitude as the wing natural frequencies.
Book Synopsis Investigation in the Langley 19-foot Pressure Tunnel of Two Wings of NACA 65-210 and 64-210 Airfoil Sections with Various Type Flaps by : James C. Sivells
Download or read book Investigation in the Langley 19-foot Pressure Tunnel of Two Wings of NACA 65-210 and 64-210 Airfoil Sections with Various Type Flaps written by James C. Sivells and published by . This book was released on 1948 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 19-foot pressure tunnel to determine the maximum lift and stalling characteristics of two thin wings equipped with several types of flaps. Split, single slotted, and double slotted flaps were tested on one wing which had NACA 65-210 airfoil sections and split and double slotted flaps were tested on the other, which had NACA 64-210 airfoil sections. Both wings had zero sweep, an aspect ratio of 9, and a ratio of root to tip chord of 2.5. Wings were tested with and without a representative fuselage and with and without leading-edge roughness.
Book Synopsis Wind-tunnel Investigation of Aileron Effectiveness of 0.20-airfoil-chord Plain Ailerons of True Airfoil Contour on NACA 652-415, 653-418 and 654-421 Airfoil Sections by : Langley Aeronautical Laboratory
Download or read book Wind-tunnel Investigation of Aileron Effectiveness of 0.20-airfoil-chord Plain Ailerons of True Airfoil Contour on NACA 652-415, 653-418 and 654-421 Airfoil Sections written by Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-09 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Book Synopsis Airfoil Section Data Obtained in the N.A.C.A. Variable-density Tunnel as Affected by Support Interference and Other Corrections by : Eastman Nixon Jacobs
Download or read book Airfoil Section Data Obtained in the N.A.C.A. Variable-density Tunnel as Affected by Support Interference and Other Corrections written by Eastman Nixon Jacobs and published by . This book was released on 1939 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Collection and Analysis of Wind-tunnel Data on the Characteristics of Isolated Tail Surfaces with and Without End Plates by : WIlliam R. Bates
Download or read book Collection and Analysis of Wind-tunnel Data on the Characteristics of Isolated Tail Surfaces with and Without End Plates written by WIlliam R. Bates and published by . This book was released on 1947 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of 19 isolated tail surfaces have been determined by wind-tunnel tests and tests have also been made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. Thes data from these tests have been collected and analyzed.
Book Synopsis An Investigation of the Lateral-Control Characteristics of Spoilers on a High-Aspect-Ratio Wing of NACA 65-210 Section in the Langley 8-Foot High-Speed Tunnel by :
Download or read book An Investigation of the Lateral-Control Characteristics of Spoilers on a High-Aspect-Ratio Wing of NACA 65-210 Section in the Langley 8-Foot High-Speed Tunnel written by and published by . This book was released on 1947 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three and six-percent-chord spoilers were tested on upper surface of high aspect ratio wing at 60 and 70 percent wing chord. Spoilers were mounted ahead of conventional 20 percent chord, straight-sided-profile ailerons, and had same span of 37.5 percent wing semispan. Spanwise loadings, moments, and rolling-moment coefficients were determined from pressure-distribution measurements.
Book Synopsis Wind Tunnel Investigation of a Plain Aileron with Various Trailing-edge Modifications on a Tapered Wing by : Francis Melvin Rogallo
Download or read book Wind Tunnel Investigation of a Plain Aileron with Various Trailing-edge Modifications on a Tapered Wing written by Francis Melvin Rogallo and published by . This book was released on 1942 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the LMAL 7- by 10-foot tunnel of various modifications to the trailing edge of a 0.155-chord plain aileron on a semispan model of the tapered wing of a fighter airplane. The modifications considered in the present report were: (1) plain and unrigged ailerons with fixed positive tabs to provide upfloating tendencies and allow reduction of stick force through the use of conventional differential aileron linkages; and (2) plain and downrigged ailerons with fixed negative tabs to provide downfloating tendencies and allow reductions of stick force through the use of reversed differential aileron linkages. The effect of a gap at the aileron nose was investigated for each of the basic modifications.
Book Synopsis Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils from Tests in the NACA Two-dimensional Low-turbulence Pressure Tunnel by : Albert E. Von Doenhoff
Download or read book Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils from Tests in the NACA Two-dimensional Low-turbulence Pressure Tunnel written by Albert E. Von Doenhoff and published by . This book was released on 1944 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Two low-drag airfoils, the NACA 747A315 and the NACA 747A415, designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient have been tested in the NACA two-dimensional low-turbulence pressure tunnel. Section lift, drag, and pitching-moment coefficients are presented for Reynolds numbers of 3 x 106, 6 x 106, and 9 x 106, together with section lift and section drag data for a Reynolds number of 6 x 106 for the same airfoils with roughened leading edges.
