Design Of Airfoil For Low Speed Flight Applications
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Design Of Airfoil For Low Speed Flight Applications
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Author : Anirudh Shukla
language : en
Publisher: LAP Lambert Academic Publishing
Release Date : 2012-02
Design Of Airfoil For Low Speed Flight Applications written by Anirudh Shukla and has been published by LAP Lambert Academic Publishing this book supported file pdf, txt, epub, kindle and other format this book has been release on 2012-02 with categories.
Airfoils are the basic elements from which aircraft wings are designed. Their properties help determine the properties of the wing so designed by the use of the airfoil shape. Though there are a large number of available airfoils for various applications, this study aims to produce an airfoil giving higher lift characteristics at low speeds compared to the most commonly used airfoil for these applications. This is done by combining the desired characteristics of higher lift airfoils with the ones which have higher stall angles at low speeds from the NACA series of airfoils.Thus, effectively giving a more efficient airfoil for low speed applications over a larger angle of attack range. The airfoil so designed is compared with the benchmark airfoil through simulations to evaluate the lift and the drag of the airfoils using XFOIL.
Summary Of Low Speed Airfoil Data
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Author : Michael S. Selig
language : en
Publisher: Soartech
Release Date : 1995
Summary Of Low Speed Airfoil Data written by Michael S. Selig and has been published by Soartech this book supported file pdf, txt, epub, kindle and other format this book has been release on 1995 with Technology & Engineering categories.
Design And Testing Of A Winglet Airfoil For Low Speed Aircraft
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Author : Mark D. Maughmer
language : en
Publisher:
Release Date : 2001
Design And Testing Of A Winglet Airfoil For Low Speed Aircraft written by Mark D. Maughmer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with categories.
Airfoils At Low Speeds
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Author : Michael S. Selig
language : en
Publisher:
Release Date : 1989
Airfoils At Low Speeds written by Michael S. Selig and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1989 with Aerodynamics categories.
Natural Laminar Flow Airfoil Design Considerations For Winglets On Low Speed Airplanes
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Author : Cornelis P. Van Dam
language : en
Publisher:
Release Date : 1984
Natural Laminar Flow Airfoil Design Considerations For Winglets On Low Speed Airplanes written by Cornelis P. Van Dam and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1984 with Airplanes categories.
Natural Laminar Flow Airfoil Design Considerations For Winglets On Low Speed Airplanes
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Author : C. P. Vandam
language : en
Publisher:
Release Date : 1984
Natural Laminar Flow Airfoil Design Considerations For Winglets On Low Speed Airplanes written by C. P. Vandam and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1984 with categories.
Winglet airfoil section characteristics which significantly influence cruise performance and handling qualities of an airplane are discussed. A good winglet design requires an airfoil section with a low cruise drag coefficient, a high maximum lift coefficient, and a gradual and steady movement of the boundary layer transition location with angle of attack. The first design requirement provides a low crossover lift coefficient of airplane drag polars with winglets off and on. The other requirements prevent nonlinear changes in airplane lateral/directional stability and control characteristics. These requirements are considered in the design of a natural laminar flow airfoil section for winglet applications and chord Reynolds number of 1 to 4 million.
Design And Experimental Results For A Natural Laminar Flow Airfoil For General Aviation Application
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Author : Dan M. Somers
language : en
Publisher:
Release Date : 1981
Design And Experimental Results For A Natural Laminar Flow Airfoil For General Aviation Application written by Dan M. Somers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Aerofoils categories.
A natural-laminar-flow airfoil for general aviation applications, the NLF(1)-0416, was designed and analyzed theoretically and verified experimentally in the Langley Low-Turbulence Pressure Tunnel. The basic objective of combining the high maximum lift of the NASA low-speed airfoils with the low cruise drag of the NACA 6-series airfoils was achieved. The safety requirement that the maximum lift coefficient not be significantly affected with transition fixed near the leading edge was also met. Comparisons of the theoretical and experimental results show excellent agreement. Comparisons with other airfoils, both laminar flow and turbulent flow, confirm the achievement of the basic objective.
Application Of The Program Profile For The Design Of Low Speed Low Observable Configuration Airfoils
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Author :
language : en
Publisher:
Release Date : 1992
Application Of The Program Profile For The Design Of Low Speed Low Observable Configuration Airfoils written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with categories.
This study investigated-the use of the program PROFILE for the design of low-speed, low-observable configuration airfoils. For our purposes, low- observable configuration is defined as being characterized by a small leading- edge radius of less than 1.18 percent chord and a thickness-to-chord ratio of 2. 5 to 5.5 percent. A methodology was developed whereby the input parameters to prescribe the velocity distribution over the airfoil could be determined by a power law relationship. This relationship enables the designer to develop symmetric airfoils with the desired thickness-to-chord and leading-edge radius within the stated constraints. The resulting symmetric airfoils compared very well with NACA 4-digit airfoils of like thickness-to-chord ratio. The resulting airfoils have an increased stall angle compared to the NACA 4-digit airfoils ... Low-Speed, Low-Observable, Symmetric Airfoils, Small Leading-Edge Radius, PROFILE, Small Thickness-to-Chord Ratio.
Low Speed Aerodynamic Characteristics Of A 17 Percent Thick Airfoil Section Designed For General Aviation Applications
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Author : Robert J. McGhee
language : en
Publisher:
Release Date : 1973
Low Speed Aerodynamic Characteristics Of A 17 Percent Thick Airfoil Section Designed For General Aviation Applications written by Robert J. McGhee and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1973 with Aerodynamics categories.
"An investigation was conducted in the Langley low-turbulence pressure tunnel to determine the low-speed two-dimensional aerodynamic characteristics of a 17-percent thick airfoil designed for general aviation applications. The results are compared with a typical older NACA 65 series airfoil section. Also, a comparison between experimental data and predictions, based on a theoretical method for calculating the viscous flow about the airfoil, is presented. The tests were conducted over a Mach number range from 0.10 to 0.28 and an angle-of-attack range from -10° to 24°. Reynolds numbers, based on the airfoil chord, were varied from about 2.0x106 to 20.0x106. The results of the investigation indicate that maximum section lift coefficients increased rapidly at Reynolds numbers from about 2.0x106 to 6.0x106 and attained values greater than 2.0 for the plain airfoil and greater than 3.0 with a 20-percent-chord split flap deflected 60°. Stall characteristics were generally gradual and of the trailing-edge type either with or without the split flap. At a lift coefficient of 1.0 (climb condition) the section lift-drag ratio increased from about 65 to 85 as the Reynolds number increased from about 2.0x106 to 6.0x106. Maximum section lift coefficients were about 30 percent greater than that of a typical older NACA 65 series airfoil section and the section lift-drag ratio at a lift coefficient of 0.90 was about 50 percent greater. Agreement of experimental results with predictions based on a theoretical method which included viscous effects was good for the pressure distributions as long as no boundary-layer flow separation was present, but the theoretical method predicted drag values greatly in excess of the measured values."--Page 1
Low Speed Aerodynamic Characteristics Of A 16 Percent Thick Variable Geometry Airfoil Designed For General Aviation Applications
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Author : Richard W. Barnwell
language : en
Publisher:
Release Date : 1978
Low Speed Aerodynamic Characteristics Of A 16 Percent Thick Variable Geometry Airfoil Designed For General Aviation Applications written by Richard W. Barnwell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1978 with Aerofoils categories.