Low Speed NLF Airfoils
Author | : Ashok Gopalarathnam |
Publisher | : |
Total Pages | : |
Release | : 1999 |
Genre | : |
ISBN | : |
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Author | : Ashok Gopalarathnam |
Publisher | : |
Total Pages | : |
Release | : 1999 |
Genre | : |
ISBN | : |
Author | : Dan M. Somers |
Publisher | : |
Total Pages | : 108 |
Release | : 1981 |
Genre | : Aerofoils |
ISBN | : |
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.
Author | : Jeffrey Keith Jepson |
Publisher | : |
Total Pages | : 68 |
Release | : 2003 |
Genre | : |
ISBN | : |
Keywords: inverse airfoil design, natural laminar flow airfoils.
Author | : J.K. Viken |
Publisher | : |
Total Pages | : |
Release | : 1987 |
Genre | : |
ISBN | : |
Author | : Cornelis P. Van Dam |
Publisher | : |
Total Pages | : 36 |
Release | : 1984 |
Genre | : Airplanes |
ISBN | : |
Author | : C. P. Vandam |
Publisher | : |
Total Pages | : 36 |
Release | : 1984 |
Genre | : |
ISBN | : |
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.
Author | : |
Publisher | : |
Total Pages | : 82 |
Release | : 1997 |
Genre | : |
ISBN | : |
Author | : Dan M. Somers |
Publisher | : |
Total Pages | : 132 |
Release | : 1981 |
Genre | : Aerofoils |
ISBN | : |
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 | : Michael S. Selig |
Publisher | : Soartech |
Total Pages | : 320 |
Release | : 1995 |
Genre | : Technology & Engineering |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 340 |
Release | : 1986 |
Genre | : Fluid dynamics |
ISBN | : |