AS5045 (15%) (as5045-il)
AS5045 (15%) - AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil
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(as5045-il) AS5045 (15%) AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil Max thickness 15% at 37.5% chord. Max camber 1% at 27.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AS5045 (15%) 1.0000 .00125 .99810 .00168 .99262 .00289 .98385 .00461 .97186 .00684 .95690 .00935 .93892 .01196 .91780 .01477 .89367 .01788 .86673 .02140 .83721 .02541 .80536 .03000 .77153 .03526 .73615 .04132 .69982 .04811 .66317 .05543 .62680 .06283 .59096 .06923 .55516 .07433 .51913 .07831 .48292 .08123 .44664 .08325 .41052 .08449 .37479 .08499 .33967 .08478 .30537 .08387 .27211 .08229 .24008 .08005 .20946 .07717 .18043 .07367 .15315 .06959 .12777 .06496 .10446 .05981 .08330 .05416 .06436 .04806 .04778 .04161 .03361 .03483 .02185 .02787 .01263 .02078 .00593 .01366 .00173 .00668 .00000 .00008 .00109 -.00530 .00587 -.00990 .01434 -.01476 .02592 -.01980 .04036 -.02496 .05747 -.03017 .07703 -.03536 .09884 -.04037 .12277 -.04507 .14872 -.04937 .17657 -.05321 .20618 -.05657 .23735 -.05943 .26989 -.06175 .30359 -.06349 .33826 -.06458 .37369 -.06501 .40968 -.06473 .44597 -.06373 .48229 -.06181 .51861 -.05884 .55478 -.05472 .59103 -.04922 .62759 -.04265 .66456 -.03535 .70215 -.02815 .73949 -.02165 .77577 -.01601 .81059 -.01127 .84351 -.00739 .87413 -.00440 .90208 -.00224 .92701 -.00085 .94861 -.00008 .96671 .00018 .98110 .00002 .99155 -.00045 .99786 -.00099 1.0000 -.00125 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 AS5045 (15%) (as5045-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| as5045-il | 50,000 | 9 | 30 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 50,000 | 5 | 29.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 100,000 | 9 | 44 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 100,000 | 5 | 43.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 200,000 | 9 | 59.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 200,000 | 5 | 56.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 500,000 | 9 | 79.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 500,000 | 5 | 70.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 1,000,000 | 9 | 92.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 1,000,000 | 5 | 81.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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