Wind Tunnel Investigation Of The Boundary Layer On An Naca 0009 Airfoil Having 0 25 And 0 50 Airfoil Chord Plain Sealed Flaps
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Wind Tunnel Investigation Of The Boundary Layer On An Naca 0009 Airfoil Having 0 25 And 0 50 Airfoil Chord Plain Sealed Flaps
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Author : Jack D. Brewer
language : en
Publisher:
Release Date : 1948
Wind Tunnel Investigation Of The Boundary Layer On An Naca 0009 Airfoil Having 0 25 And 0 50 Airfoil Chord Plain Sealed Flaps written by Jack D. Brewer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Aerofoils categories.
An investigation was conducted in the Langley 4- by 6-foot tunnel to determine the boundary-layer characteristics of an NACA 0009 airfoil equipped with 0.25- and 0.50-airfoil chord plain sealed flaps. The tests were made to define as thoroughly as possible the characteristics of two of the configurations used in a comprehensive investigation of control surface characteristics and also to provide additional data for comparison with previous boundary-layer analyses. The measured velocity profiles and the boundary-layer parameters determined from them are presented.
Wind Tunnel Investigation Of Control Surface Characteristics
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Author : H. Page Hoggard
language : en
Publisher:
Release Date : 1944
Wind Tunnel Investigation Of Control Surface Characteristics written by H. Page Hoggard and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1944 with Aerodynamic load categories.
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.
Wind Tunnel Investigation Of Control Surface Characteristics
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Author : H. Page Hoggard
language : en
Publisher:
Release Date : 1943
Wind Tunnel Investigation Of Control Surface Characteristics written by H. Page Hoggard and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1943 with Aerofoils categories.
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.
Wind Tunnel Investigation Of Control Surface Characteristics
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Author : Richard I. Sears
language : en
Publisher:
Release Date : 1943
Wind Tunnel Investigation Of Control Surface Characteristics written by Richard I. Sears and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1943 with Aerofoils categories.
Force-test measurements in two-dimensional flow have been made in the NACA 4- by 6-foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 airfoil equipped with a double plain flap that consisted of a plain forward flap having a chord 20 percent of the airfoil chord ().20c) and a plain rearward flap having a chord 15 percent of the airfoil chord.
Wind Tunnel Investigation Of An Naca 23021 Airfoil With A 0 32 Airfoil Chord Double Slotted Flap
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Author : Jack Fischel
language : en
Publisher:
Release Date : 1944
Wind Tunnel Investigation Of An Naca 23021 Airfoil With A 0 32 Airfoil Chord Double Slotted Flap written by Jack Fischel and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1944 with Aerodynamics categories.
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.
Wind Tunnel Investigation Of Control Surface Characteristics
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Author : Langley Aeronautical Laboratory
language : en
Publisher: Hassell Street Press
Release Date : 2021-09-09
Wind Tunnel Investigation Of Control Surface Characteristics written by Langley Aeronautical Laboratory and has been published by Hassell Street Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2021-09-09 with categories.
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.
Wind Tunnel Investigation Of Control Surface Characteristics
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Author : H. Page Jr Hoggard
language : en
Publisher:
Release Date : 1944
Wind Tunnel Investigation Of Control Surface Characteristics written by H. Page Jr Hoggard and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1944 with categories.
Wind Tunnel Investigation Of Control Surface Characteristics
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Author : Langley Aeronautical Laboratory
language : en
Publisher: Hassell Street Press
Release Date : 2021-09-10
Wind Tunnel Investigation Of Control Surface Characteristics written by Langley Aeronautical Laboratory and has been published by Hassell Street Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2021-09-10 with categories.
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.
Summary Of Results Of A Wind Tunnel Investigation Of Nine Related Horizontal Tails
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Author : Jules B. Dods
language : en
Publisher:
Release Date : 1955
Summary Of Results Of A Wind Tunnel Investigation Of Nine Related Horizontal Tails written by Jules B. Dods and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with Aeronautics categories.
The results of a wind-tunnel investigation of a series of models of nine related horizontal tails have been summarized to provide basic design information; to indicate the effects of aspect ratio, sweepback, and changes in the Mach number; and to provide experimental values of the lift and hinge-moment parameters for comparison with values computed by a method employing lifting-surface theory. The models had aspect ratios from 2 to 6, angles of sweepback of the quarter-chord line from 5.7 degrees to 45 degrees, a taper ratio of 0.5, and had 30-percent-chord, sealed, plain flaps. The Mach number was varied from 0.12 to 0.94 for Reynolds numbers of 2, 3, or 4 million. Also, a constant-chord airfoil having the NACA 64A010 section and completely spanning the wind tunnel was tested at a Mach number of 0.12. This airfoil had the same section and flap-chord ratio as the nine horizontal-tail models.
Wind Tunnel Investigation Of Control Surface Characteristics 22 Medium And Large Aerodynamic Balance Of Two Nose Shapes And A Plain Overhang Used With A 0 20 Airfoil Chord Flap On An Naca 0009 Airfoil
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Author :
language : en
Publisher:
Release Date : 1945
Wind Tunnel Investigation Of Control Surface Characteristics 22 Medium And Large Aerodynamic Balance Of Two Nose Shapes And A Plain Overhang Used With A 0 20 Airfoil Chord Flap On An Naca 0009 Airfoil written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1945 with categories.
The NACA is conducting an extensive investigation determine the characteristics of various types of flap arrangement suitable for use as control surface and to provide data for design purpose. The investigation, which made in the Langley 4- by 6-foot vertical tunnel, had included test of modifications of flap profile, trailing edge angle, gap size, flap nose shape and balance chord, however most of those tests have been made in two dimensional flow with a flap having a chord 30 percent of the airfoil chord (0.30c). The present tests have extended the investigation of balance chord and flap nose shape, which was reported in reference 1 for a 0.40c flap, to a 0.20c flap. Data on the pressure across the flap nose seal and a method of applying these pressure across the flap nose seal and a method of applying these pressure data in the design of internal balances are presented. Tab data are presented for the plain flap and for a flap with aerodynamic balance.