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Wind Tunnel Investigation Of Aileron Effectiveness Of 020 Airfoil Chord Plain Ailerons Of True Airfoil Contour On Naca 652 415 653 418 And 654 421 Airfoil Sections
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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 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 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 Wind-tunnel Investigation of Aileron Effectiveness of 0.20-airfoil-chord Plain Ailerons of True Airfoil Contour on NACA 65 2-415, 65 3-418 and 65 4-421 Airfoil Sections by : Albert L. Braslov
Download or read book Wind-tunnel Investigation of Aileron Effectiveness of 0.20-airfoil-chord Plain Ailerons of True Airfoil Contour on NACA 65 2-415, 65 3-418 and 65 4-421 Airfoil Sections written by Albert L. Braslov and published by . This book was released on 1944 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the NACA two-dimensional low-turbulence pressure tunnel to determine the aileron effectiveness of 0.2-airfoil-chord plain ailerons of true airfoil contour on the NACA 65(sub 2)-415, 65(sub 3)-418, and 65(sub 4)-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 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 Two-dimensional Wind-tunnel Investigation of 0.20-airfoil-chord Plain Ailerons of Different Contour on an NACA 65(1)-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 65(1)-210 Airfoil Section written by William J. Underwood and published by . This book was released on 1945 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made of three interchangeable sealed-gap 0.20-airfoil-chord plain ailerons of different contour on the NACA 65(sub 1)-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 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 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 46 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 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 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were made on an NACA 23012 airfoil fitted with a 20-percent-chord, true-contour aileron with 35-percent-chord, extreme blunt-nose balance. The tests were made in the two-dimensional test section of the NACA stability tunnel at a range of airspeeds from 160 to 360 miles per hour, which corresponded to a range of Mach numbers from 0.195 to 0.475. The primary purpose of the investigation was to determine the variation of the aerodynamic characteristics of this type of aileron with airspeed; the effect of variations of gap width and balance-nose radii was also investigated.
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 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 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 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: Hinge moment, lift, and pressure-distribution measurements were made on a Frise aileron on an NACA 23012 airfoil in the two-dimensional test section of the LMAL stability tunnel. Speeds up to 360 miles per hour corresponding to a Mach number of about 0.470 were used. The nose radius of the aileron was varied from 0.0012 to 0.0150 of the airfoil chord. Tests also were made with an increased vent gap and with the lower surface of the airfoil at the entrance of the slot rounded to a radius of 0.02 of the airfoil chord. The primary purpose of all tests was to determine the effects of speed on this type of aileron.
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 Wind-tunnel Investigation of Control-surface Characteristics by : M. Leroy Spearman
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.
