Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Book Description
A Study of High-lift Airfoils at High Reynolds Numbers in the Langley Low-turbulence Pressure Tunnel
Experimental Results for the Eppler 387 Airfoil at Low Reynolds Numbers in the Langley Low-turbulence Pressure Tunnel
Author: Robert J. McGheePublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 240
Book Description
Wind Tunnel Tests of Two Airfoils for Wind Turbines Operating at High Reynolds Numbers
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The objectives of this study were to verify the predictions of the Eppler Airfoil Design and Analysis Code for Reynolds numbers up to 6 x 106 and to acquire the section characteristics of two airfoils being considered for large, megawatt-size wind turbines. One airfoil, the S825, was designed to achieve a high maximum lift coefficient suitable for variable-speed machines. The other airfoil, the S827, was designed to achieve a low maximum lift coefficient suitable for stall-regulated machines. Both airfoils were tested in the NASA Langley Low-Turbulence Pressure Tunnel (LTPT) for smooth, fixed-transition, and rough surface conditions at Reynolds numbers of 1, 2, 3, 4, and 6 x 106. The results show the maximum lift coefficient of both airfoils is substantially underpredicted for Reynolds numbers over 3 x 106 and emphasized the difficulty of designing low-lift airfoils for high Reynolds numbers.
Scientific and Technical Aerospace Reports
Author: Experimental Results for the Eppler 387 Airfoil at Low Reynolds Numbers in the Langley Low-Turbulence Pressure Tunnel
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781723574788
Category :
Languages : en
Pages : 234
Book Description
Experimental results were obtained for an Eppler 387 airfoil in the Langley Low Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.03 to 0.13 and a chord Reynolds number range for 60,000 to 460,000. Lift and pitching moment data were obtained from airfoil surface pressure measurements and drag data for wake surveys. Oil flow visualization was used to determine laminar separation and turbulent reattachment locations. Comparisons of these results with data on the Eppler 387 airfoil from two other facilities as well as the Eppler airfoil code are included. Mcghee, Robert J. and Walker, Betty S. and Millard, Betty F. Langley Research Center NASA-TM-4062, L-16430, NAS 1.15:4062 RTOP 505-60-21-01...
Experimental Results for the Eppler 387 Airfoil at Low Reynolds Numbers in the Langley Low-turbulence Pressure Tunnel
Author: Robert J. McGheeLangley Aerospace Test Highlights - 1986
Author: Design and Experimental Results for a Natural-laminar-flow Airfoil for General Aviation Applications
Author: Dan M. SomersSummary of Low Speed Airfoil Data
Author: Michael S. SeligPublisher: Soartech
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 320
Book Description
Design and Experimental Results for a Natural-Laminar-Flow Airfoil for General Aviation Application
Author: Dan M. SomersPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 108
Book Description
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.