CLARK YM-18 AIRFOIL (clarym18-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YM-18 AIRFOIL (clarym18-il) Reynolds number: 50,000 Max Cl/Cd: 25.68 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarym18-il-50000-n5.txt Download as CSV file: xf-clarym18-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YM-18 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5063 0.08391 0.07613 -0.0632 1.0000 0.0967
-10.500 -0.5688 0.07640 0.06862 -0.0643 1.0000 0.0963
-10.250 -0.6236 0.07220 0.06440 -0.0614 1.0000 0.0958
-10.000 -0.6730 0.06933 0.06148 -0.0562 1.0000 0.0955
-9.750 -0.7094 0.06454 0.05640 -0.0543 0.9963 0.0957
-9.500 -0.7251 0.05845 0.04968 -0.0557 0.9864 0.0968
-9.250 -0.7018 0.05663 0.04786 -0.0572 0.9806 0.0987
-9.000 -0.6859 0.05458 0.04568 -0.0578 0.9731 0.1011
-8.750 -0.6705 0.05174 0.04248 -0.0590 0.9666 0.1041
-8.500 -0.6642 0.04867 0.03886 -0.0584 0.9580 0.1070
-8.250 -0.6369 0.04717 0.03733 -0.0598 0.9525 0.1100
-8.000 -0.6183 0.04584 0.03589 -0.0595 0.9448 0.1134
-7.750 -0.5968 0.04386 0.03348 -0.0601 0.9384 0.1181
-7.500 -0.5722 0.04271 0.03230 -0.0605 0.9320 0.1220
-7.250 -0.5500 0.04168 0.03117 -0.0605 0.9245 0.1269
-7.000 -0.5204 0.04029 0.02951 -0.0617 0.9195 0.1331
-6.750 -0.5009 0.03964 0.02889 -0.0609 0.9114 0.1381
-6.500 -0.4739 0.03854 0.02749 -0.0615 0.9050 0.1455
-6.250 -0.4396 0.03785 0.02690 -0.0632 0.9007 0.1529
-6.000 -0.4244 0.03714 0.02599 -0.0614 0.8914 0.1600
-5.750 -0.3936 0.03656 0.02549 -0.0624 0.8857 0.1684
-5.500 -0.3651 0.03591 0.02476 -0.0629 0.8799 0.1780
-5.250 -0.3452 0.03549 0.02431 -0.0619 0.8716 0.1876
-5.000 -0.3124 0.03493 0.02377 -0.0630 0.8664 0.1996
-4.750 -0.2895 0.03454 0.02337 -0.0625 0.8592 0.2123
-4.500 -0.2653 0.03418 0.02297 -0.0621 0.8518 0.2271
-4.250 -0.2313 0.03372 0.02253 -0.0633 0.8470 0.2463
-4.000 -0.2126 0.03354 0.02234 -0.0620 0.8385 0.2637
-3.750 -0.1857 0.03325 0.02208 -0.0620 0.8318 0.2845
-3.500 -0.1502 0.03283 0.02170 -0.0634 0.8275 0.3092
-3.250 -0.1352 0.03281 0.02171 -0.0615 0.8179 0.3285
-3.000 -0.1053 0.03252 0.02148 -0.0620 0.8118 0.3541
-2.750 -0.0687 0.03212 0.02112 -0.0634 0.8078 0.3846
-2.500 -0.0586 0.03224 0.02136 -0.0607 0.7970 0.4066
-2.250 -0.0274 0.03191 0.02116 -0.0611 0.7915 0.4414
-2.000 -0.0033 0.03172 0.02116 -0.0603 0.7845 0.4765
-1.750 0.0171 0.03157 0.02120 -0.0588 0.7753 0.5146
-1.500 0.0559 0.03086 0.02073 -0.0596 0.7701 0.5702
-1.250 0.0692 0.03079 0.02090 -0.0564 0.7572 0.6192
-1.000 0.1100 0.03006 0.02040 -0.0566 0.7512 0.6932
-0.750 0.1278 0.03017 0.02067 -0.0538 0.7384 0.7544
-0.500 0.1788 0.02975 0.02027 -0.0557 0.7327 0.8214
-0.250 0.2114 0.03009 0.02058 -0.0560 0.7215 0.8720
0.000 0.2720 0.02989 0.02022 -0.0607 0.7153 0.9141
0.250 0.3275 0.02996 0.02015 -0.0655 0.7065 0.9466
0.500 0.3947 0.02975 0.01980 -0.0724 0.6980 0.9709
0.750 0.4631 0.02934 0.01921 -0.0796 0.6903 0.9915
1.000 0.4942 0.02930 0.01908 -0.0808 0.6788 1.0000
1.250 0.5043 0.02934 0.01901 -0.0779 0.6679 1.0000
1.500 0.5234 0.02915 0.01869 -0.0763 0.6582 1.0000
1.750 0.5283 0.02940 0.01887 -0.0726 0.6457 1.0000
2.000 0.5582 0.02900 0.01832 -0.0724 0.6375 1.0000
2.250 0.5600 0.02942 0.01868 -0.0683 0.6240 1.0000
2.500 0.5805 0.02935 0.01850 -0.0667 0.6137 1.0000
2.750 0.5983 0.02937 0.01842 -0.0648 0.6024 1.0000
3.000 0.6084 0.02967 0.01864 -0.0618 0.5897 1.0000
3.250 0.6417 0.02931 0.01814 -0.0620 0.5810 1.0000
3.500 0.6472 0.02983 0.01862 -0.0585 0.5673 1.0000
3.750 0.6669 0.03000 0.01868 -0.0570 0.5564 1.0000
4.000 0.6904 0.03006 0.01865 -0.0560 0.5459 1.0000
4.250 0.7028 0.03055 0.01908 -0.0535 0.5339 1.0000
4.500 0.7355 0.03039 0.01878 -0.0538 0.5251 1.0000
4.750 0.7425 0.03116 0.01953 -0.0508 0.5129 1.0000
5.000 0.7746 0.03112 0.01936 -0.0511 0.5050 1.0000
5.250 0.7812 0.03200 0.02024 -0.0482 0.4941 1.0000
5.500 0.8166 0.03195 0.02006 -0.0490 0.4872 1.0000
5.750 0.8181 0.03306 0.02121 -0.0455 0.4768 1.0000
6.000 0.8508 0.03313 0.02117 -0.0460 0.4700 1.0000
6.250 0.8547 0.03427 0.02235 -0.0429 0.4612 1.0000
6.500 0.8781 0.03473 0.02277 -0.0423 0.4544 1.0000
6.750 0.9003 0.03530 0.02330 -0.0417 0.4481 1.0000
7.000 0.9052 0.03656 0.02462 -0.0390 0.4404 1.0000
7.250 0.9349 0.03680 0.02482 -0.0392 0.4348 1.0000
7.500 0.9426 0.03805 0.02611 -0.0370 0.4281 1.0000
7.750 0.9509 0.03932 0.02743 -0.0351 0.4215 1.0000
8.000 0.9828 0.03946 0.02753 -0.0354 0.4165 1.0000
8.250 0.9818 0.04127 0.02943 -0.0327 0.4099 1.0000
8.500 0.9863 0.04285 0.03108 -0.0307 0.4034 1.0000
8.750 1.0207 0.04278 0.03096 -0.0311 0.3986 1.0000
9.000 1.0099 0.04536 0.03366 -0.0280 0.3920 1.0000
9.250 1.0074 0.04758 0.03598 -0.0259 0.3853 1.0000
9.500 1.0466 0.04702 0.03538 -0.0264 0.3808 1.0000
9.750 1.0140 0.05157 0.04010 -0.0228 0.3732 1.0000
10.000 1.0070 0.05450 0.04312 -0.0212 0.3663 1.0000
10.250 1.0556 0.05284 0.04143 -0.0216 0.3626 1.0000
10.500 0.9567 0.06488 0.05373 -0.0185 0.3497 1.0000
10.750 0.9913 0.06386 0.05273 -0.0178 0.3459 1.0000
11.000 1.0524 0.06033 0.04914 -0.0176 0.3435 1.0000
11.250 0.9387 0.07597 0.06502 -0.0173 0.3273 1.0000
11.500 0.9861 0.07294 0.06200 -0.0160 0.3253 1.0000
12.000 0.9196 0.08794 0.07718 -0.0174 0.3035 1.0000
12.500 0.8599 0.10342 0.09281 -0.0207 0.2786 1.0000
12.750 0.8791 0.10366 0.09310 -0.0199 0.2733 1.0000
13.000 0.9117 0.10161 0.09108 -0.0182 0.2706 1.0000
13.500 0.8836 0.11269 0.10227 -0.0208 0.2507 1.0000
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Polar data table (+)
Polar graphs
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