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Wind Tunnel Tests Of A Blunt Nose Aileron With Beveled Trailing Edge On An Naca 66215 216 Airfoil With Several Modification Of Aileron Nose And Adjacent Airfoil Contour
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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 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 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 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 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 Wind Tunnel Investigation of Control Surface Characteristics by : H. Page Hoggard
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.
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : H. Page Hoggard
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.
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : John M. Riebe
Download or read book Wind-tunnel Investigation of Control-surface Characteristics written by John M. Riebe and published by . This book was released on 1945 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Wind-tunnel tests have been made to investigate the characteristics of an NACA 0009 airfoil with a 40-percent-chord flap having medium and large aerodynamic balances of elliptical and blunt nose shapes and having a plain overhang. The results are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed and unsealed. Tests were also made to determine the effectiveness of a tab, which was 20 percent of the flap chord, on the plain sealed flap and on the 35-percent-flap-chord elliptical-overhang flap with gap sealed. The pressure difference across the flap-nose seal was also determined for the plain sealed flap.
Book Synopsis Wind-tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semispan Ailerons and with Nonperforated, Balanced Double Split Flaps for Use as Aerodynamic Brakes by : Thomas A. Toll
Download or read book Wind-tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semispan Ailerons and with Nonperforated, Balanced Double Split Flaps for Use as Aerodynamic Brakes written by Thomas A. Toll and published by . This book was released on 1945 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Tests have been made in the Langley 7- by 10-foot tunnel to determine the applicability of nonperforated, balanced double split flaps for use as aerodynamic brakes. Information was desired on the braking power of the flaps as well as on the effectiveness and the stability of a conventional trailing-edge aileron located immediately behind the flaps. A rectangular 10- by 60-inch wing model of NACA 2212 airfoil section was used for the tests. Results were obtained for flat-plate flaps with no wing cut-outs and for flaps having Clark Y sections with cut-outs made in the wing to simulate the space left open by the deflected flaps. The flap deflections, the chordwise location, and the gaps between the flaps and the airfoil contour were varied over wide ranges in order to determine the optimum configuration. In addition to the force tests, an investigation was made to determine any buffeting tendencies of the aileron. Silk tufts and a flexible torque rod were used for these tests.
Book Synopsis Wind-tunnel Investigation of Control-surface Characteristics by : John M. Riebe
Download or read book Wind-tunnel Investigation of Control-surface Characteristics written by John M. Riebe and published by . This book was released on 1945 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an elliptical overhang of 0.35 flap chord. The pressure difference across the flap seal was also determined for the plain sealed flap.
Book Synopsis Flight Tests of Experimental Beveled-trailing-edge Frise Ailerons on a Fighter Airplane by : R. Fabian Goranson
Download or read book Flight Tests of Experimental Beveled-trailing-edge Frise Ailerons on a Fighter Airplane written by R. Fabian Goranson and published by . This book was released on 1946 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight measurements have been made to determine the characteristics of a pair of experimental ailerons designed to provide a close degree of balance and to maintain a linear variation of aileron effectiveness with aileron angle through a large deflection range. The ailerons, which were tested on a production fighter airplane, incorporated an unswept Frise nose and a beveled trailing edge. These ailerons were designed for application to an experimental fighter airplane, which was to employ wings similar to those of the test airplane as outer panels added to those of the test airplane as outer panels added to a rectangular center section. Individual aileron hinge moments, aileron rolling effectiveness, and stick-force characteristics were measured in abrupt aileron rolls over an equivalent airspeed range from approximately 109 to 276 miles per hour.
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:
Book Synopsis Wind-tunnel Investigation of an NACA 23021 Airfoil with a 0.32-airfoil-chord Double Slotted Flap by : Jack Fischel
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.
Book Synopsis Low-speed Experimental Investigation of a Thin, Faired, Double-wedge Airfoil Section with Nose and Trailing-edge Flaps by : Leonard M. Rose
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.
Book Synopsis Wind Tunnel Tests on Airfoil Boundary Layer Control Using a Backward-opening Slot by : C. H. Dearborn
Download or read book Wind Tunnel Tests on Airfoil Boundary Layer Control Using a Backward-opening Slot written by C. H. Dearborn and published by . This book was released on 1931 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
