E209 (13.72%) (e209-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 200,000 Max Cl/Cd: 69.86 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e209-il-200000-n5.txt Download as CSV file: xf-e209-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E209 (13.72%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6445 0.08256 0.07861 -0.0454 1.0000 0.0125
-13.000 -0.6859 0.07049 0.06629 -0.0536 1.0000 0.0123
-12.750 -0.7152 0.06216 0.05773 -0.0591 1.0000 0.0120
-12.500 -0.7318 0.05667 0.05207 -0.0624 1.0000 0.0121
-12.250 -0.7468 0.05182 0.04704 -0.0650 1.0000 0.0122
-12.000 -0.7598 0.04765 0.04267 -0.0666 1.0000 0.0122
-11.750 -0.7700 0.04425 0.03911 -0.0674 1.0000 0.0123
-11.500 -0.7781 0.04153 0.03623 -0.0672 1.0000 0.0126
-11.250 -0.7862 0.03914 0.03366 -0.0659 1.0000 0.0126
-11.000 -0.7944 0.03718 0.03155 -0.0634 1.0000 0.0128
-10.750 -0.8021 0.03559 0.02980 -0.0598 1.0000 0.0130
-10.500 -0.8045 0.03391 0.02795 -0.0567 1.0000 0.0133
-10.250 -0.8028 0.03227 0.02613 -0.0539 1.0000 0.0136
-10.000 -0.7983 0.03077 0.02444 -0.0512 1.0000 0.0140
-9.750 -0.7910 0.02960 0.02302 -0.0487 1.0000 0.0149
-9.500 -0.7841 0.02815 0.02149 -0.0462 1.0000 0.0154
-9.250 -0.7748 0.02711 0.02043 -0.0439 1.0000 0.0160
-9.000 -0.7643 0.02616 0.01939 -0.0416 1.0000 0.0166
-8.750 -0.7532 0.02519 0.01833 -0.0394 1.0000 0.0175
-8.500 -0.7223 0.02382 0.01679 -0.0410 0.9952 0.0186
-8.250 -0.6915 0.02257 0.01538 -0.0425 0.9895 0.0197
-8.000 -0.6601 0.02132 0.01410 -0.0444 0.9837 0.0213
-7.750 -0.6298 0.02048 0.01319 -0.0456 0.9759 0.0235
-7.500 -0.5972 0.01955 0.01212 -0.0473 0.9694 0.0255
-7.250 -0.5701 0.01858 0.01112 -0.0478 0.9589 0.0280
-7.000 -0.5411 0.01790 0.01036 -0.0485 0.9479 0.0311
-6.750 -0.5117 0.01708 0.00948 -0.0493 0.9365 0.0347
-6.500 -0.4803 0.01639 0.00871 -0.0503 0.9245 0.0400
-6.250 -0.4483 0.01566 0.00797 -0.0515 0.9114 0.0489
-6.000 -0.4155 0.01499 0.00727 -0.0528 0.8968 0.0629
-5.750 -0.3834 0.01435 0.00667 -0.0540 0.8803 0.0836
-5.500 -0.3525 0.01378 0.00613 -0.0549 0.8618 0.1108
-5.250 -0.3233 0.01328 0.00566 -0.0554 0.8425 0.1412
-4.750 -0.2724 0.01223 0.00486 -0.0550 0.8041 0.2390
-4.500 -0.2489 0.01175 0.00455 -0.0544 0.7863 0.3021
-4.250 -0.2246 0.01146 0.00437 -0.0538 0.7696 0.3561
-4.000 -0.1991 0.01133 0.00423 -0.0533 0.7542 0.3966
-3.750 -0.1731 0.01127 0.00409 -0.0528 0.7398 0.4261
-3.500 -0.1470 0.01123 0.00399 -0.0523 0.7265 0.4512
-3.250 -0.1207 0.01122 0.00388 -0.0519 0.7140 0.4718
-3.000 -0.0943 0.01120 0.00378 -0.0515 0.7026 0.4881
-2.750 -0.0676 0.01118 0.00368 -0.0512 0.6912 0.5026
-2.500 -0.0409 0.01117 0.00360 -0.0509 0.6808 0.5164
-2.250 -0.0142 0.01117 0.00352 -0.0506 0.6713 0.5293
-2.000 0.0125 0.01115 0.00345 -0.0503 0.6616 0.5416
-1.750 0.0394 0.01114 0.00340 -0.0500 0.6528 0.5532
-1.500 0.0663 0.01114 0.00334 -0.0497 0.6444 0.5648
-1.000 0.1201 0.01114 0.00326 -0.0492 0.6286 0.5878
-0.750 0.1471 0.01112 0.00325 -0.0490 0.6208 0.5988
-0.500 0.1741 0.01114 0.00322 -0.0488 0.6138 0.6102
-0.250 0.2012 0.01114 0.00322 -0.0486 0.6065 0.6219
0.000 0.2280 0.01115 0.00322 -0.0483 0.5998 0.6330
0.250 0.2550 0.01115 0.00325 -0.0481 0.5931 0.6448
0.500 0.2818 0.01116 0.00327 -0.0479 0.5864 0.6575
0.750 0.3086 0.01118 0.00330 -0.0476 0.5803 0.6713
1.000 0.3353 0.01119 0.00336 -0.0474 0.5736 0.6863
1.250 0.3618 0.01122 0.00341 -0.0470 0.5680 0.7024
1.500 0.3882 0.01122 0.00350 -0.0467 0.5613 0.7207
1.750 0.4144 0.01124 0.00358 -0.0462 0.5555 0.7413
2.000 0.4404 0.01126 0.00367 -0.0457 0.5496 0.7636
2.250 0.4664 0.01128 0.00378 -0.0452 0.5433 0.7888
2.500 0.4924 0.01132 0.00389 -0.0447 0.5381 0.8173
2.750 0.5195 0.01134 0.00404 -0.0443 0.5316 0.8493
3.000 0.5496 0.01141 0.00418 -0.0446 0.5256 0.8823
3.250 0.5845 0.01150 0.00434 -0.0459 0.5194 0.9142
3.500 0.6215 0.01160 0.00449 -0.0478 0.5124 0.9435
3.750 0.6583 0.01173 0.00462 -0.0498 0.5059 0.9674
4.000 0.6955 0.01184 0.00478 -0.0519 0.4976 0.9856
4.250 0.7332 0.01197 0.00492 -0.0541 0.4889 1.0000
4.500 0.7555 0.01210 0.00505 -0.0531 0.4808 1.0000
4.750 0.7781 0.01224 0.00523 -0.0522 0.4722 1.0000
5.000 0.8008 0.01241 0.00537 -0.0512 0.4640 1.0000
5.250 0.8238 0.01255 0.00556 -0.0503 0.4541 1.0000
5.500 0.8467 0.01272 0.00574 -0.0494 0.4443 1.0000
5.750 0.8694 0.01290 0.00594 -0.0485 0.4338 1.0000
6.000 0.8923 0.01308 0.00615 -0.0476 0.4220 1.0000
6.250 0.9150 0.01327 0.00638 -0.0467 0.4091 1.0000
6.500 0.9373 0.01349 0.00662 -0.0457 0.3952 1.0000
6.750 0.9591 0.01374 0.00689 -0.0447 0.3793 1.0000
7.000 0.9801 0.01403 0.00716 -0.0435 0.3616 1.0000
7.250 1.0008 0.01434 0.00748 -0.0423 0.3404 1.0000
7.500 1.0198 0.01475 0.00783 -0.0409 0.3161 1.0000
7.750 1.0372 0.01525 0.00825 -0.0393 0.2871 1.0000
8.000 1.0521 0.01589 0.00877 -0.0374 0.2523 1.0000
8.500 1.0761 0.01755 0.01011 -0.0329 0.1871 1.0000
8.750 1.0869 0.01842 0.01086 -0.0305 0.1605 1.0000
9.000 1.0974 0.01927 0.01162 -0.0281 0.1379 1.0000
9.250 1.1050 0.02013 0.01241 -0.0253 0.1198 1.0000
9.500 1.1128 0.02098 0.01324 -0.0225 0.1046 1.0000
9.750 1.1202 0.02190 0.01414 -0.0199 0.0917 1.0000
10.000 1.1269 0.02291 0.01513 -0.0174 0.0808 1.0000
10.250 1.1341 0.02394 0.01618 -0.0152 0.0713 1.0000
10.500 1.1406 0.02508 0.01734 -0.0130 0.0632 1.0000
10.750 1.1453 0.02640 0.01867 -0.0110 0.0564 1.0000
11.000 1.1508 0.02776 0.02009 -0.0093 0.0500 1.0000
11.250 1.1544 0.02936 0.02172 -0.0077 0.0451 1.0000
11.500 1.1591 0.03098 0.02342 -0.0064 0.0404 1.0000
11.750 1.1610 0.03292 0.02538 -0.0053 0.0363 1.0000
12.000 1.1656 0.03475 0.02731 -0.0044 0.0329 1.0000
12.250 1.1672 0.03692 0.02952 -0.0037 0.0300 1.0000
12.500 1.1695 0.03913 0.03181 -0.0032 0.0274 1.0000
12.750 1.1725 0.04133 0.03411 -0.0028 0.0252 1.0000
13.000 1.1731 0.04385 0.03668 -0.0026 0.0232 1.0000
13.250 1.1720 0.04663 0.03954 -0.0025 0.0217 1.0000
13.500 1.1731 0.04924 0.04227 -0.0024 0.0204 1.0000
13.750 1.1732 0.05201 0.04515 -0.0026 0.0193 1.0000
14.000 1.1716 0.05507 0.04832 -0.0028 0.0182 1.0000
14.250 1.1687 0.05836 0.05170 -0.0033 0.0174 1.0000
14.500 1.1643 0.06196 0.05540 -0.0039 0.0166 1.0000
14.750 1.1628 0.06529 0.05886 -0.0046 0.0161 1.0000
15.000 1.1609 0.06878 0.06248 -0.0054 0.0151 1.0000
15.250 1.1589 0.07238 0.06619 -0.0064 0.0145 1.0000
15.500 1.1560 0.07622 0.07013 -0.0076 0.0138 1.0000
15.750 1.1519 0.08033 0.07433 -0.0090 0.0133 1.0000
16.000 1.1458 0.08487 0.07895 -0.0107 0.0126 1.0000
16.250 1.1424 0.08905 0.08328 -0.0121 0.0123 1.0000
16.500 1.1385 0.09343 0.08780 -0.0138 0.0119 1.0000
16.750 1.1342 0.09795 0.09245 -0.0156 0.0116 1.0000
17.000 1.1293 0.10272 0.09736 -0.0177 0.0111 1.0000
17.250 1.1244 0.10756 0.10232 -0.0199 0.0109 1.0000
17.500 1.1187 0.11263 0.10751 -0.0223 0.0106 1.0000
17.750 1.1132 0.11772 0.11272 -0.0248 0.0105 1.0000
18.000 1.1070 0.12310 0.11821 -0.0275 0.0102 1.0000
18.250 1.1008 0.12855 0.12377 -0.0304 0.0100 1.0000
18.500 1.0949 0.13403 0.12936 -0.0334 0.0099 1.0000
18.750 1.0885 0.13964 0.13506 -0.0365 0.0098 1.0000
19.000 1.0826 0.14520 0.14074 -0.0396 0.0096 1.0000
19.250 1.0754 0.15126 0.14691 -0.0431 0.0095 1.0000
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Polar data table (+)
Polar graphs
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