E195 (11.82%) (e195-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 200,000 Max Cl/Cd: 80.09 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e195-il-200000.txt Download as CSV file: xf-e195-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E195 (11.82%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3714 0.09031 0.08693 -0.0442 1.0000 0.0608
-9.000 -0.3987 0.08445 0.08122 -0.0524 1.0000 0.0621
-8.750 -0.4178 0.07959 0.07645 -0.0565 1.0000 0.0622
-8.500 -0.4429 0.07630 0.07316 -0.0569 1.0000 0.0623
-8.250 -0.4673 0.07415 0.07102 -0.0546 1.0000 0.0624
-8.000 -0.3231 0.06250 0.05976 -0.0486 0.9940 0.0725
-7.750 -0.4405 0.06689 0.06401 -0.0529 0.9951 0.0652
-7.500 -0.4139 0.06222 0.05926 -0.0593 0.9865 0.0677
-7.250 -0.4047 0.05132 0.04759 -0.0753 0.9685 0.0763
-7.000 -0.3725 0.04811 0.04455 -0.0773 0.9620 0.0787
-6.750 -0.3639 0.03199 0.02642 -0.0808 0.9459 0.0399
-6.500 -0.3379 0.02742 0.02153 -0.0820 0.9351 0.0379
-6.250 -0.3089 0.02429 0.01793 -0.0828 0.9248 0.0369
-6.000 -0.2790 0.02195 0.01519 -0.0832 0.9142 0.0367
-5.750 -0.2517 0.02025 0.01319 -0.0830 0.9012 0.0371
-5.500 -0.2248 0.01892 0.01163 -0.0825 0.8884 0.0378
-5.250 -0.1982 0.01809 0.01058 -0.0819 0.8760 0.0393
-5.000 -0.1745 0.01667 0.00910 -0.0812 0.8642 0.0422
-4.750 -0.1498 0.01586 0.00822 -0.0804 0.8534 0.0447
-4.500 -0.1258 0.01519 0.00745 -0.0795 0.8419 0.0483
-4.250 -0.1027 0.01438 0.00659 -0.0785 0.8311 0.0553
-4.000 -0.0797 0.01342 0.00576 -0.0775 0.8220 0.0931
-3.750 -0.0567 0.01266 0.00534 -0.0769 0.8125 0.1784
-3.500 -0.0327 0.01221 0.00511 -0.0764 0.8035 0.2500
-3.250 -0.0090 0.01173 0.00494 -0.0758 0.7957 0.3447
-3.000 0.0143 0.01142 0.00492 -0.0750 0.7870 0.4387
-2.750 0.0389 0.01122 0.00485 -0.0742 0.7802 0.5082
-2.500 0.0634 0.01108 0.00481 -0.0735 0.7720 0.5606
-2.250 0.0885 0.01096 0.00474 -0.0727 0.7656 0.6114
-2.000 0.1125 0.01083 0.00476 -0.0717 0.7581 0.6623
-1.750 0.1370 0.01071 0.00472 -0.0706 0.7518 0.7129
-1.500 0.1609 0.01061 0.00474 -0.0694 0.7451 0.7642
-1.250 0.1854 0.01052 0.00476 -0.0681 0.7388 0.8203
-1.000 0.2153 0.01051 0.00479 -0.0678 0.7334 0.8783
-0.750 0.2560 0.01057 0.00482 -0.0699 0.7266 0.9270
-0.500 0.3044 0.01065 0.00476 -0.0738 0.7213 0.9599
-0.250 0.3569 0.01072 0.00474 -0.0790 0.7149 0.9828
0.000 0.4142 0.01071 0.00459 -0.0853 0.7089 0.9994
0.250 0.4368 0.01080 0.00457 -0.0846 0.7035 1.0000
0.500 0.4581 0.01090 0.00463 -0.0837 0.6969 1.0000
0.750 0.4815 0.01101 0.00464 -0.0829 0.6918 1.0000
1.000 0.5042 0.01117 0.00476 -0.0821 0.6857 1.0000
1.250 0.5278 0.01130 0.00485 -0.0814 0.6799 1.0000
1.500 0.5529 0.01146 0.00491 -0.0809 0.6753 1.0000
1.750 0.5758 0.01163 0.00510 -0.0801 0.6686 1.0000
2.000 0.6007 0.01177 0.00519 -0.0796 0.6634 1.0000
2.250 0.6253 0.01196 0.00537 -0.0790 0.6581 1.0000
2.500 0.6493 0.01214 0.00555 -0.0783 0.6518 1.0000
2.750 0.6752 0.01229 0.00564 -0.0779 0.6470 1.0000
3.000 0.6989 0.01249 0.00590 -0.0772 0.6405 1.0000
3.250 0.7242 0.01264 0.00604 -0.0767 0.6345 1.0000
3.500 0.7496 0.01281 0.00620 -0.0762 0.6286 1.0000
3.750 0.7740 0.01296 0.00639 -0.0756 0.6214 1.0000
4.000 0.8006 0.01308 0.00649 -0.0752 0.6155 1.0000
4.250 0.8243 0.01321 0.00670 -0.0744 0.6071 1.0000
4.500 0.8509 0.01331 0.00676 -0.0740 0.6005 1.0000
4.750 0.8747 0.01342 0.00696 -0.0733 0.5916 1.0000
5.000 0.9004 0.01351 0.00707 -0.0727 0.5838 1.0000
5.250 0.9254 0.01356 0.00716 -0.0721 0.5747 1.0000
5.500 0.9496 0.01364 0.00732 -0.0713 0.5651 1.0000
5.750 0.9753 0.01367 0.00736 -0.0707 0.5559 1.0000
6.000 0.9993 0.01370 0.00747 -0.0699 0.5450 1.0000
6.250 1.0228 0.01375 0.00761 -0.0690 0.5331 1.0000
6.500 1.0463 0.01379 0.00772 -0.0681 0.5203 1.0000
6.750 1.0691 0.01382 0.00783 -0.0670 0.5054 1.0000
7.000 1.0914 0.01387 0.00793 -0.0658 0.4885 1.0000
7.250 1.1128 0.01397 0.00807 -0.0645 0.4684 1.0000
7.500 1.1317 0.01413 0.00823 -0.0628 0.4396 1.0000
7.750 1.1476 0.01447 0.00848 -0.0607 0.3991 1.0000
8.000 1.1598 0.01511 0.00891 -0.0581 0.3457 1.0000
8.250 1.1654 0.01616 0.00961 -0.0547 0.2840 1.0000
8.500 1.1689 0.01741 0.01053 -0.0513 0.2292 1.0000
8.750 1.1711 0.01871 0.01155 -0.0477 0.1831 1.0000
9.000 1.1723 0.01989 0.01255 -0.0440 0.1475 1.0000
9.250 1.1716 0.02122 0.01368 -0.0402 0.1167 1.0000
9.500 1.1707 0.02270 0.01499 -0.0367 0.0865 1.0000
9.750 1.1646 0.02465 0.01675 -0.0331 0.0581 1.0000
10.000 1.1547 0.02711 0.01909 -0.0296 0.0401 1.0000
10.250 1.1483 0.02952 0.02148 -0.0269 0.0346 1.0000
10.500 1.1518 0.03133 0.02342 -0.0252 0.0316 1.0000
10.750 1.1536 0.03337 0.02553 -0.0237 0.0292 1.0000
11.000 1.1511 0.03586 0.02804 -0.0221 0.0273 1.0000
11.250 1.1520 0.03817 0.03042 -0.0207 0.0262 1.0000
11.500 1.1586 0.04002 0.03239 -0.0197 0.0247 1.0000
11.750 1.1651 0.04192 0.03437 -0.0188 0.0234 1.0000
12.000 1.1713 0.04393 0.03644 -0.0177 0.0226 1.0000
12.250 1.1786 0.04588 0.03848 -0.0167 0.0220 1.0000
12.500 1.1867 0.04790 0.04052 -0.0156 0.0211 1.0000
12.750 1.2014 0.04978 0.04244 -0.0142 0.0206 1.0000
13.000 1.2203 0.05197 0.04475 -0.0128 0.0202 1.0000
13.250 1.2305 0.05432 0.04731 -0.0119 0.0200 1.0000
13.500 1.2385 0.05705 0.05026 -0.0111 0.0199 1.0000
13.750 1.2407 0.06018 0.05363 -0.0105 0.0198 1.0000
14.000 1.2422 0.06366 0.05735 -0.0101 0.0199 1.0000
14.250 1.2385 0.06761 0.06155 -0.0098 0.0199 1.0000
14.500 1.2320 0.07189 0.06606 -0.0099 0.0200 1.0000
14.750 1.2222 0.07667 0.07108 -0.0103 0.0201 1.0000
15.000 1.2103 0.08186 0.07650 -0.0111 0.0202 1.0000
15.250 1.2004 0.08648 0.08136 -0.0122 0.0203 1.0000
15.500 1.1858 0.09163 0.08671 -0.0140 0.0204 1.0000
15.750 1.1707 0.09706 0.09234 -0.0163 0.0204 1.0000
16.000 1.1561 0.10262 0.09811 -0.0191 0.0206 1.0000
16.250 1.1368 0.10960 0.10529 -0.0228 0.0206 1.0000
16.500 1.1047 0.11978 0.11581 -0.0293 0.0214 1.0000
16.750 1.0345 0.14111 0.13760 -0.0438 0.0228 1.0000
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Polar data table (+)
Polar graphs
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