public abstract class NACA6ASeries extends NACA6Series
This class represents an arbitrary NACA 6*A series airfoil section such as a NACA 63A-020 airfoil.
Ported from FORTRAN "NACA6.FOR" to Java by: Joseph A. Huwaldt, June 3, 2010
Original FORTRAN "NACA4" code had the following note:
AUTHORS - Charles L.Ladson and Cuyler W. Brooks, NASA Langley
Liam Hardy, NASA Ames
Ralph Carmichael, Public Domain Aeronautical Software
Last FORTRAN version: 23Nov96 2.0 RLC
NOTES - This program has also been known as LADSON and SIXSERIES and
as SIXSERIE on systems with a 8-letter name limit.
REFERENCES- NASA Technical Memorandum TM X-3069 (September, 1974),
by Charles L. Ladson and Cuyler W. Brooks, Jr., NASA Langley Research Center.
"Theory of Wing Sections", by Ira Abbott and Albert Von Doenhoff.
Modified by: Joseph A. Huwaldt
| Constructor and Description |
|---|
NACA6ASeries(double CLi,
double thickness,
double length)
Create a NACA 6*A series airfoil with the specified parameters.
|
getCamber, getLower, getLowerYp, getProfile, getUpper, getUpperYp, toStringpublic NACA6ASeries(double CLi, double thickness, double length)
CLi - Design lift coefficient (e.g.: 63A-206 has CLi = 0.2).thickness - The thickness to chord ratio (e.g.: 0.20 ==> 20% t/c).length - The chord length.