Coanda 2 (coanda2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Coanda 2 (coanda2-il) Reynolds number: 100,000 Max Cl/Cd: 53.21 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-coanda2-il-100000.txt Download as CSV file: xf-coanda2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Coanda 2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4267 0.10150 0.09669 -0.0179 1.0000 0.0723
-8.500 -0.4355 0.09981 0.09511 -0.0192 1.0000 0.0727
-8.250 -0.4411 0.09788 0.09325 -0.0214 1.0000 0.0729
-8.000 -0.4419 0.09535 0.09076 -0.0247 1.0000 0.0731
-7.750 -0.4396 0.09238 0.08779 -0.0275 1.0000 0.0733
-7.500 -0.4325 0.08568 0.08119 -0.0216 1.0000 0.0746
-7.250 -0.4264 0.08198 0.07748 -0.0191 1.0000 0.0763
-7.000 -0.4227 0.07872 0.07425 -0.0194 1.0000 0.0771
-6.750 -0.4184 0.07546 0.07101 -0.0200 1.0000 0.0779
-6.500 -0.4134 0.07205 0.06760 -0.0207 1.0000 0.0790
-6.250 -0.4069 0.06865 0.06418 -0.0215 1.0000 0.0801
-6.000 -0.3989 0.06517 0.06066 -0.0223 1.0000 0.0811
-5.750 -0.3895 0.06157 0.05699 -0.0232 1.0000 0.0821
-5.500 -0.3734 0.05317 0.04805 -0.0281 1.0000 0.0609
-5.250 -0.3654 0.04968 0.04459 -0.0262 1.0000 0.0596
-5.000 -0.3545 0.04587 0.04063 -0.0251 1.0000 0.0582
-4.750 -0.3418 0.04167 0.03617 -0.0239 1.0000 0.0578
-4.500 -0.3280 0.03725 0.03131 -0.0224 1.0000 0.0592
-4.250 -0.3123 0.03645 0.03046 -0.0206 1.0000 0.0682
-3.750 -0.2824 0.02980 0.02277 -0.0157 1.0000 0.0885
-3.500 -0.2684 0.02920 0.02191 -0.0135 1.0000 0.1246
-3.000 -0.2956 0.03077 0.02561 0.0004 1.0000 0.4104
-2.750 -0.3008 0.02945 0.02456 0.0091 1.0000 0.4928
-2.500 -0.2954 0.02800 0.02316 0.0146 1.0000 0.5404
-2.250 -0.1864 0.02549 0.01773 -0.0057 1.0000 0.2238
-2.000 -0.1621 0.02428 0.01622 -0.0046 1.0000 0.2042
-1.750 -0.1391 0.02376 0.01523 -0.0033 1.0000 0.1943
-1.500 -0.1180 0.02279 0.01414 -0.0022 1.0000 0.1910
-1.250 -0.0956 0.02251 0.01340 -0.0007 1.0000 0.1810
-1.000 -0.0747 0.02169 0.01255 0.0002 1.0000 0.1784
-0.750 -0.0541 0.02118 0.01195 0.0013 1.0000 0.1757
-0.500 -0.0168 0.02087 0.01148 -0.0010 0.9947 0.1730
-0.250 0.0387 0.02062 0.01106 -0.0067 0.9830 0.1712
0.000 0.0931 0.02027 0.01066 -0.0121 0.9702 0.1714
0.250 0.1476 0.01987 0.01032 -0.0176 0.9566 0.1760
0.500 0.2027 0.01935 0.00985 -0.0229 0.9426 0.1787
0.750 0.2545 0.01869 0.00931 -0.0273 0.9264 0.1801
1.000 0.3114 0.01787 0.00867 -0.0327 0.9099 0.1833
1.250 0.3725 0.01700 0.00797 -0.0386 0.8933 0.1901
1.500 0.4359 0.01604 0.00718 -0.0448 0.8750 0.2016
1.750 0.4907 0.01511 0.00653 -0.0491 0.8460 0.2280
2.000 0.6326 0.01270 0.00585 -0.0722 0.7794 1.0000
2.250 0.6680 0.01271 0.00555 -0.0726 0.7119 1.0000
2.500 0.6960 0.01308 0.00558 -0.0718 0.6542 1.0000
2.750 0.7163 0.01361 0.00569 -0.0695 0.5913 1.0000
3.000 0.7358 0.01410 0.00587 -0.0674 0.5384 1.0000
3.250 0.7558 0.01453 0.00610 -0.0656 0.4931 1.0000
3.500 0.7777 0.01495 0.00641 -0.0642 0.4606 1.0000
3.750 0.7998 0.01538 0.00683 -0.0629 0.4312 1.0000
4.000 0.8182 0.01583 0.00706 -0.0609 0.3783 1.0000
4.250 0.8386 0.01627 0.00736 -0.0594 0.3325 1.0000
4.500 0.8608 0.01670 0.00779 -0.0581 0.2982 1.0000
4.750 0.8817 0.01728 0.00824 -0.0567 0.2503 1.0000
5.000 0.9003 0.01823 0.00879 -0.0550 0.1728 1.0000
5.250 0.9135 0.02018 0.00993 -0.0528 0.0586 1.0000
5.500 0.9314 0.02154 0.01128 -0.0508 0.0443 1.0000
5.750 0.9489 0.02287 0.01274 -0.0488 0.0396 1.0000
6.000 0.9661 0.02412 0.01419 -0.0466 0.0384 1.0000
6.250 0.9822 0.02544 0.01570 -0.0443 0.0377 1.0000
6.500 0.9975 0.02693 0.01733 -0.0419 0.0375 1.0000
6.750 1.0142 0.02864 0.01912 -0.0397 0.0375 1.0000
7.000 1.0338 0.03070 0.02125 -0.0380 0.0377 1.0000
7.250 1.0567 0.03335 0.02399 -0.0367 0.0383 1.0000
7.500 1.0808 0.03706 0.02791 -0.0359 0.0392 1.0000
7.750 1.1015 0.03844 0.02968 -0.0339 0.0405 1.0000
8.000 1.1181 0.04128 0.03312 -0.0313 0.0426 1.0000
8.250 1.1264 0.04489 0.03733 -0.0283 0.0437 1.0000
8.500 1.1304 0.04855 0.04150 -0.0251 0.0442 1.0000
8.750 1.1290 0.05275 0.04620 -0.0218 0.0457 1.0000
9.000 1.1243 0.05724 0.05108 -0.0187 0.0475 1.0000
9.250 1.1199 0.06216 0.05622 -0.0164 0.0494 1.0000
9.500 1.1132 0.06578 0.06026 -0.0132 0.0530 1.0000
9.750 1.0795 0.06979 0.06465 -0.0091 0.0543 1.0000
10.000 1.0485 0.07430 0.06939 -0.0074 0.0552 1.0000
10.250 1.0212 0.07964 0.07489 -0.0086 0.0553 1.0000
10.500 0.9855 0.08852 0.08394 -0.0144 0.0583 1.0000
10.750 0.9531 0.09947 0.09494 -0.0231 0.0585 1.0000
11.000 0.9326 0.10976 0.10512 -0.0291 0.0603 1.0000
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Polar data table (+)
Polar graphs
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