The Design of Single Slotted-flapped Airfoil Sections for Low Reynolds Numbers PDF Download
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Author: Lawrence A. Schienbein Publisher: ISBN: Category : Aerofoils Languages : en Pages : 0
Book Description
The problems associated with the design of a slotted-flap airfoil for high lift and low drag at low Reynolds 6 numbers (-10 ) were investigated and a single slotted-flap airfoil was designed using a simplified design technique. A basic design philosophy was developed; the main points being the proper choice of the basic airfoil section and the modification of the flap section to achieve the desired loading. The maximum' lift coefficient for low drag was determined by the onset of flow separation on the main section while the flap was designed to remain unstalled. The effects of the boundary layer on the lift and the pressure distribution were accounted for by a camber change related to the calculated boundary layer displacement thicknesses. A maximum usable lift coefficient of 2 was found for the slotted-flap airfoil designed in the course of the project.
Author: Lawrence A. Schienbein Publisher: ISBN: Category : Aerofoils Languages : en Pages : 0
Book Description
The problems associated with the design of a slotted-flap airfoil for high lift and low drag at low Reynolds 6 numbers (-10 ) were investigated and a single slotted-flap airfoil was designed using a simplified design technique. A basic design philosophy was developed; the main points being the proper choice of the basic airfoil section and the modification of the flap section to achieve the desired loading. The maximum' lift coefficient for low drag was determined by the onset of flow separation on the main section while the flap was designed to remain unstalled. The effects of the boundary layer on the lift and the pressure distribution were accounted for by a camber change related to the calculated boundary layer displacement thicknesses. A maximum usable lift coefficient of 2 was found for the slotted-flap airfoil designed in the course of the project.
Author: Richard Eppler Publisher: Springer Science & Business Media ISBN: 3662026465 Category : Technology & Engineering Languages : en Pages : 569
Book Description
This detailed book describes a procedure for the design and analysis of subsonic airfoils. Contains 116 new airfoils for a wide range of Reynolds numbers and application requirements, including the input data for the computer code.
Author: Leonard M. Rose Publisher: ISBN: Category : Aerofoils Languages : en Pages : 28
Book Description
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.
Author: Seymour M. Bogdonoff Publisher: ISBN: Category : Aerofoils Languages : en Pages : 7
Book Description
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
Author: Dan M. Somers Publisher: ISBN: Category : Aerofoils Languages : en Pages : 132
Book Description
A flapped natural laminar flow airfoil for general aviation applications, the NLF(1)-0215F, has been 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 has been achieved. The safety requirement that the maximum lift coefficient not be significantly affected with transition fixed near the leading edge has also been met. Comparisons of the theoretical and experimental results show generally good agreement.
Author: Lawrence A. Schienbein
Author: Lawrence A. Schienbein
Author: Richard Eppler
Author: 
Author: Stanley Jay Miley
Author: Michael S. Selig
Author: James L. Amick
Author: Michael S. Selig
Author: Leonard M. Rose
Author: Seymour M. Bogdonoff
Author: Dan M. Somers