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A Effect Of Leakage Past Aileron Nose On Aerodynamic Characteristics Of Plain And Internally Balanced Ailerons On Naca 66215 216
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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 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 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 Aerodynamic Characteristics for Internal-balance and Frise Type Ailerons on an NACA 6 Series Low-drag Tip Section of the Wing for the XP-63 Airplane by : William J. Underwood
Download or read book Aerodynamic Characteristics for Internal-balance and Frise Type Ailerons on an NACA 6 Series Low-drag Tip Section of the Wing for the XP-63 Airplane written by William J. Underwood and published by . This book was released on 1942 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were made in the two-dimensional low-turbulence tunnel of a model submitted by Bell Aircraft Corporation as the tip section of the wing of the XP-63 airplane. The model was an NACA 66,2x-216 a = 0.6 airfoil section of 50-inch chord and made of dural according to standard sheet-metal practice. The model was fitted for an internal-balance aileron with a tab and a Frise type aileron.
Book Synopsis WInd-tunnel Tests of Ailerons at Various Speeds by : W. Letko
Download or read book WInd-tunnel Tests of Ailerons at Various Speeds written by W. Letko and published by . This book was released on 1943 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure-distribution tests of an NACA 66,2-216, a = 1.0, airfoil, equipped with a blunt-nose-balance aileron and a sealed internal-balance aileron, and of an NACA 23012 airfoil, equipped with a Frise aileron and a blunt-nose- aileron, were made in the two-dimensional test-balance section of the LMAL stability tunnel. The tests were made at various airspeeds corresponding to Mach numbers of approximately 0.20 to 0.47. The pressures were measured on the upper and lower surface at the mid-spans of the main airfoil and the aileron for several different aileron deflections at several angles of attack.
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 WInd-tunnel Tests of Ailerons at Various Speeds by : W. Letko
Download or read book WInd-tunnel Tests of Ailerons at Various Speeds written by W. Letko and published by . This book was released on 1943 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.
Book Synopsis A Study of the Effects of Radii of Gyration and Altitude on Aileron Effectiveness at High Speed by : Leo F. Fehlner
Download or read book A Study of the Effects of Radii of Gyration and Altitude on Aileron Effectiveness at High Speed written by Leo F. Fehlner and published by . This book was released on 1943 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Introduction: Because the time to bank combat aircraft has become increasingly important and because information on the variation in the time to bank with altitude and with weight distribution along the wings is not available, the present theoretical investigation was made to determine the magnitude of these effects. The variation in the necessary aileron control and in the time required to bank to 45° and 90° with altitude and radii of gyration for a typical fighter or a pursuit airplane have been computed and are presented herein.
Book Synopsis A Flight Investigation of NACA Aileron Modifications for the Improvement of the Lateral Control Characterisitcs of a High-speed Fighter Airplance by : Walter C. Williams
Download or read book A Flight Investigation of NACA Aileron Modifications for the Improvement of the Lateral Control Characterisitcs of a High-speed Fighter Airplance written by Walter C. Williams and published by . This book was released on 1945 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: A flight investigation was made to improve the lateral control of a high-speed fighter airplane. Tests were made of the airplance with the original aileron installation and with a set of modified ailerons developed by the NACA. This modification consisted of an increased balance chord and increased nose radius. In order to determine the best aileron performance with the NACA modified aileron, tests were made with various aileron-deflection ranges and riggings with the original control assembly and with an experimental differential control unit developed by the manufacturer. The test program included the speed range from 150 to 400 miles per hour.
Book Synopsis Wind-tunnel Tests of a Blunt-nose Aileron with Beveled Trailing Edge on an NACA 66(215)-216 Airfoil with Several Modification 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 Modification of Aileron Nose and Adjacent Airfoil Contour written by J. D. Bird and published by . This book was released on 1945 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: Ailerons having a beveled trailing edge and a blunt-nose overhang 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 the aileron hinge-moment characteristics.
Book Synopsis Ailerons of 0.20 Airfoil Chord and True Contour with 0.60 Aileron-chord Sealed Internal Balance on the NACA 66,2-216 Airfoil by : H. G. Denaci
Download or read book Ailerons of 0.20 Airfoil Chord and True Contour with 0.60 Aileron-chord Sealed Internal Balance on the NACA 66,2-216 Airfoil written by H. G. Denaci and published by . This book was released on 1943 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis WInd-tunnel Tests of Ailerons at Various Speeds by : H. G. Denaci
Download or read book WInd-tunnel Tests of Ailerons at Various Speeds written by H. G. Denaci and published by . This book was released on 1943 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hinge-moment, lift, and pressure difference across the balance, and pressure-distribution measurements were made in the two-dimensional test section of the stability tunnel on a 0.60 aileron-chord sealed internal,-balance aileron on the NACA 66,2-216, a = 1.0 airfoil.
Book Synopsis Ailerons of 0.20 Airfoil Chord and True Contour with 0.35 Aileron-chord Extreme Blunt Nose Balance on the NACA 66,2-216 Airfoil by : W. Letko
Download or read book Ailerons of 0.20 Airfoil Chord and True Contour with 0.35 Aileron-chord Extreme Blunt Nose Balance on the NACA 66,2-216 Airfoil written by W. Letko and published by . This book was released on 1943 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil With Various Types of Aileron by : Langley Aeronautical Laboratory
Download or read book Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil With Various Types of Aileron written by Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-09 with total page 26 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 Two-dimensional Wind-tunnel Investigation of Sealed 0.22-airfoil-chord Internally Balanced Ailerons of Different Contour on an NACA 65(112)-213 Airfoil by : Albert L. Braslow
Download or read book Two-dimensional Wind-tunnel Investigation of Sealed 0.22-airfoil-chord Internally Balanced Ailerons of Different Contour on an NACA 65(112)-213 Airfoil written by Albert L. Braslow and published by . This book was released on 1946 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: A two-dimensional wind-tunnel investigation was made of two interchangeable sealed 0.22-airfoil-chord internally balanced ailerons on an NACA 65(112)-213 airfoil. One of the ailerons tested was of true contour and the other was modified by partly eliminating the cusp near the trailing edge. Tests were made to determine the effects of the aileron contour modified on the section aerodynamic characteristics of the airfoil and aileron.
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 1946 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
