AS5046 (16%) (as5046-il)
AS5046 (16%) - AS5046 airfoil Ashok Gopalarathnam/Selig 16% airfoil
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(as5046-il) AS5046 (16%) AS5046 airfoil Ashok Gopalarathnam/Selig 16% airfoil Max thickness 16% at 37.6% chord. Max camber 0.7% at 77.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AS5046 (16%) 1.0000 .00134 .99804 .00200 .99260 .00372 .98401 .00594 .97220 .00866 .95749 .01168 .93979 .01474 .91895 .01797 .89512 .02146 .86847 .02532 .83924 .02960 .80767 .03441 .77409 .03982 .73889 .04596 .70270 .05277 .66609 .06004 .62962 .06733 .59358 .07375 .55759 .07896 .52139 .08307 .48502 .08610 .44860 .08824 .41235 .08957 .37649 .09013 .34123 .08996 .30680 .08908 .27342 .08752 .24130 .08527 .21060 .08233 .18148 .07874 .15411 .07456 .12868 .06983 .10538 .06454 .08429 .05863 .06537 .05215 .04876 .04527 .03450 .03803 .02260 .03058 .01322 .02302 .00632 .01544 .00193 .00801 .00003 .00097 .00071 -.00489 .00510 -.00988 .01342 -.01505 .02489 -.02044 .03925 -.02596 .05625 -.03155 .07571 -.03710 .09745 -.04246 .12133 -.04752 .14723 -.05216 .17505 -.05634 .20462 -.06003 .23577 -.06321 .26829 -.06582 .30198 -.06783 .33664 -.06919 .37208 -.06986 .40806 -.06980 .44435 -.06899 .48068 -.06725 .51700 -.06445 .55315 -.06046 .58935 -.05509 .62582 -.04860 .66265 -.04132 .70010 -.03396 .73735 -.02722 .77354 -.02135 .80827 -.01632 .84111 -.01210 .87165 -.00870 .89952 -.00605 .92439 -.00407 .94591 -.00256 .96421 -.00129 .97931 -.00050 .99065 -.00052 .99763 -.00101 1.0000 -.00134 http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/ |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for AS5046 (16%) (as5046-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| as5046-il | 50,000 | 9 | 28.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 50,000 | 5 | 28.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 100,000 | 9 | 42.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 100,000 | 5 | 42.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 200,000 | 9 | 58.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 200,000 | 5 | 55.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 500,000 | 9 | 77.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 500,000 | 5 | 69.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 1,000,000 | 9 | 90.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 1,000,000 | 5 | 83.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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