M6 (85%) (m685-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 100,000 Max Cl/Cd: 50.6 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m685-il-100000.txt Download as CSV file: xf-m685-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: M6 (85%)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4722 0.10212 0.09697 -0.0179 1.0000 0.1075
-9.250 -0.4967 0.09875 0.09371 -0.0244 1.0000 0.1103
-9.000 -0.5237 0.09510 0.09016 -0.0297 1.0000 0.1107
-8.750 -0.4748 0.09106 0.08607 -0.0214 1.0000 0.1177
-8.500 -0.4822 0.08746 0.08253 -0.0238 1.0000 0.1218
-8.250 -0.5044 0.08376 0.07890 -0.0270 1.0000 0.1237
-8.000 -0.5479 0.08179 0.07685 -0.0283 1.0000 0.1254
-7.750 -0.5097 0.07680 0.07204 -0.0251 1.0000 0.1320
-7.500 -0.5176 0.07381 0.06905 -0.0249 1.0000 0.1370
-7.250 -0.5572 0.07288 0.06778 -0.0244 1.0000 0.1410
-7.000 -0.5241 0.06735 0.06259 -0.0226 1.0000 0.1484
-6.750 -0.5592 0.06768 0.06245 -0.0200 1.0000 0.1572
-6.500 -0.5289 0.06153 0.05672 -0.0190 1.0000 0.1637
-6.250 -0.5442 0.05966 0.05461 -0.0164 1.0000 0.1746
-6.000 -0.5289 0.05628 0.05140 -0.0143 1.0000 0.1802
-5.500 -0.5300 0.05175 0.04679 -0.0081 1.0000 0.1976
-5.250 -0.5365 0.04990 0.04487 -0.0042 1.0000 0.2091
-5.000 -0.5446 0.04879 0.04364 0.0002 1.0000 0.2229
-4.750 -0.5415 0.04036 0.03399 0.0034 1.0000 0.1288
-4.500 -0.5343 0.03391 0.02655 0.0083 1.0000 0.0884
-4.250 -0.5261 0.03217 0.02392 0.0128 1.0000 0.0822
-4.000 -0.4919 0.02926 0.02067 0.0111 0.9943 0.0813
-3.750 -0.4492 0.02729 0.01821 0.0083 0.9859 0.0824
-3.500 -0.4083 0.02500 0.01579 0.0053 0.9779 0.0863
-3.250 -0.3644 0.02364 0.01427 0.0021 0.9693 0.0916
-3.000 -0.3167 0.02228 0.01282 -0.0018 0.9623 0.1011
-2.750 -0.2750 0.02135 0.01174 -0.0043 0.9521 0.1108
-2.500 -0.2319 0.02021 0.01073 -0.0073 0.9435 0.1263
-2.250 -0.1895 0.01893 0.00970 -0.0101 0.9352 0.1571
-2.000 0.0214 0.01655 0.01029 -0.0408 0.9763 1.0000
-1.750 0.0769 0.01629 0.00978 -0.0468 0.9640 1.0000
-1.500 0.1316 0.01597 0.00926 -0.0526 0.9520 1.0000
-1.250 0.1832 0.01566 0.00879 -0.0576 0.9388 1.0000
-1.000 0.2314 0.01536 0.00835 -0.0619 0.9242 1.0000
-0.750 0.2745 0.01512 0.00799 -0.0650 0.9084 1.0000
-0.500 0.3106 0.01498 0.00774 -0.0667 0.8912 1.0000
-0.250 0.3407 0.01493 0.00759 -0.0671 0.8738 1.0000
0.000 0.3663 0.01496 0.00752 -0.0666 0.8567 1.0000
0.250 0.3892 0.01504 0.00752 -0.0655 0.8405 1.0000
0.500 0.4107 0.01515 0.00756 -0.0641 0.8247 1.0000
0.750 0.4317 0.01529 0.00764 -0.0627 0.8097 1.0000
1.000 0.4525 0.01544 0.00774 -0.0612 0.7951 1.0000
1.250 0.4734 0.01560 0.00787 -0.0597 0.7813 1.0000
1.500 0.4944 0.01577 0.00799 -0.0582 0.7680 1.0000
1.750 0.5160 0.01592 0.00809 -0.0568 0.7553 1.0000
2.000 0.5371 0.01608 0.00823 -0.0553 0.7420 1.0000
2.250 0.5577 0.01628 0.00844 -0.0538 0.7282 1.0000
2.500 0.5785 0.01646 0.00862 -0.0523 0.7143 1.0000
2.750 0.5995 0.01662 0.00878 -0.0507 0.7005 1.0000
3.000 0.6207 0.01677 0.00892 -0.0492 0.6867 1.0000
3.250 0.6423 0.01690 0.00905 -0.0476 0.6732 1.0000
3.500 0.6645 0.01702 0.00914 -0.0461 0.6603 1.0000
3.750 0.6853 0.01721 0.00936 -0.0446 0.6458 1.0000
4.000 0.7062 0.01741 0.00963 -0.0430 0.6315 1.0000
4.250 0.7272 0.01762 0.00989 -0.0416 0.6175 1.0000
4.500 0.7483 0.01778 0.01009 -0.0399 0.6026 1.0000
4.750 0.7694 0.01787 0.01023 -0.0382 0.5865 1.0000
5.000 0.7904 0.01787 0.01023 -0.0364 0.5686 1.0000
5.250 0.8117 0.01782 0.01016 -0.0345 0.5498 1.0000
5.500 0.8306 0.01783 0.01024 -0.0324 0.5279 1.0000
5.750 0.8501 0.01775 0.01015 -0.0303 0.5046 1.0000
6.000 0.8678 0.01772 0.01014 -0.0279 0.4776 1.0000
6.250 0.8850 0.01774 0.01018 -0.0255 0.4483 1.0000
6.500 0.9011 0.01785 0.01029 -0.0230 0.4149 1.0000
6.750 0.9153 0.01809 0.01048 -0.0202 0.3727 1.0000
7.000 0.9252 0.01865 0.01082 -0.0169 0.3082 1.0000
7.250 0.9232 0.02030 0.01174 -0.0122 0.1994 1.0000
7.500 0.9198 0.02249 0.01328 -0.0075 0.1328 1.0000
7.750 0.9227 0.02417 0.01467 -0.0036 0.1087 1.0000
8.000 0.9285 0.02568 0.01607 -0.0001 0.0941 1.0000
8.250 0.9372 0.02719 0.01744 0.0028 0.0858 1.0000
8.500 0.9520 0.02864 0.01894 0.0051 0.0795 1.0000
8.750 0.9684 0.03014 0.02035 0.0067 0.0741 1.0000
9.000 0.9899 0.03210 0.02232 0.0077 0.0699 1.0000
9.250 1.0099 0.03374 0.02413 0.0090 0.0670 1.0000
9.500 1.0308 0.03563 0.02618 0.0101 0.0649 1.0000
9.750 1.0504 0.03768 0.02838 0.0113 0.0636 1.0000
10.000 1.0680 0.03992 0.03080 0.0126 0.0626 1.0000
10.250 1.0827 0.04234 0.03346 0.0142 0.0621 1.0000
10.500 1.0937 0.04498 0.03639 0.0163 0.0619 1.0000
10.750 1.1000 0.04778 0.03951 0.0188 0.0620 1.0000
11.000 1.0977 0.05061 0.04276 0.0222 0.0627 1.0000
11.250 1.0866 0.05369 0.04626 0.0262 0.0634 1.0000
11.500 1.0707 0.05688 0.04982 0.0302 0.0643 1.0000
11.750 1.0494 0.05980 0.05299 0.0346 0.0648 1.0000
12.000 1.0257 0.06313 0.05657 0.0377 0.0656 1.0000
12.250 1.0005 0.06701 0.06067 0.0393 0.0661 1.0000
12.500 0.9738 0.07177 0.06563 0.0394 0.0673 1.0000
12.750 0.9458 0.07727 0.07130 0.0382 0.0682 1.0000
13.000 0.9169 0.08368 0.07784 0.0357 0.0691 1.0000
13.250 0.8900 0.09083 0.08508 0.0324 0.0700 1.0000
13.500 0.8857 0.09668 0.09093 0.0315 0.0714 1.0000
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Polar data table (+)
Polar graphs
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