E207 (12.04%) (e207-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.69 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e207-il-1000000.txt Download as CSV file: xf-e207-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E207 (12.04%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7424 0.04695 0.04467 -0.0625 1.0000 0.0082
-11.750 -0.7723 0.04006 0.03754 -0.0678 1.0000 0.0082
-11.500 -0.7918 0.03663 0.03394 -0.0675 1.0000 0.0082
-11.250 -0.8323 0.03293 0.02998 -0.0619 1.0000 0.0083
-11.000 -0.8490 0.02990 0.02673 -0.0579 1.0000 0.0086
-10.750 -0.8458 0.02847 0.02519 -0.0552 1.0000 0.0087
-10.500 -0.8341 0.02789 0.02458 -0.0532 1.0000 0.0089
-10.250 -0.8271 0.02666 0.02324 -0.0506 1.0000 0.0090
-10.000 -0.8143 0.02609 0.02262 -0.0486 1.0000 0.0093
-9.750 -0.8012 0.02550 0.02198 -0.0466 1.0000 0.0095
-9.500 -0.7741 0.02422 0.02055 -0.0477 0.9983 0.0099
-9.250 -0.7450 0.02230 0.01839 -0.0495 0.9957 0.0102
-9.000 -0.7137 0.02098 0.01690 -0.0512 0.9934 0.0106
-8.750 -0.6839 0.01978 0.01552 -0.0523 0.9898 0.0109
-8.500 -0.6499 0.01918 0.01480 -0.0540 0.9868 0.0112
-8.250 -0.6213 0.01656 0.01189 -0.0555 0.9840 0.0118
-8.000 -0.5922 0.01546 0.01074 -0.0563 0.9788 0.0123
-7.750 -0.5604 0.01475 0.00997 -0.0576 0.9729 0.0128
-7.500 -0.5306 0.01430 0.00949 -0.0582 0.9638 0.0134
-7.250 -0.5006 0.01370 0.00882 -0.0588 0.9512 0.0140
-7.000 -0.4716 0.01304 0.00805 -0.0591 0.9305 0.0144
-6.750 -0.4459 0.01253 0.00738 -0.0586 0.8999 0.0148
-6.500 -0.4223 0.01220 0.00688 -0.0577 0.8676 0.0151
-6.250 -0.3998 0.01171 0.00621 -0.0566 0.8383 0.0155
-6.000 -0.3793 0.01089 0.00520 -0.0553 0.8122 0.0164
-5.750 -0.3553 0.01055 0.00474 -0.0545 0.7891 0.0173
-5.500 -0.3306 0.01028 0.00435 -0.0539 0.7677 0.0180
-5.250 -0.3055 0.01002 0.00397 -0.0533 0.7490 0.0186
-5.000 -0.2799 0.00978 0.00363 -0.0528 0.7316 0.0192
-4.750 -0.2539 0.00958 0.00332 -0.0524 0.7155 0.0200
-4.500 -0.2279 0.00935 0.00299 -0.0520 0.7011 0.0209
-4.250 -0.2019 0.00910 0.00266 -0.0516 0.6879 0.0234
-4.000 -0.1754 0.00893 0.00243 -0.0512 0.6753 0.0262
-3.750 -0.1496 0.00862 0.00218 -0.0508 0.6638 0.0474
-3.500 -0.1238 0.00830 0.00198 -0.0505 0.6534 0.0845
-3.250 -0.0976 0.00806 0.00183 -0.0503 0.6436 0.1185
-3.000 -0.0714 0.00783 0.00169 -0.0500 0.6340 0.1570
-2.750 -0.0450 0.00758 0.00157 -0.0498 0.6254 0.2029
-2.500 -0.0193 0.00730 0.00146 -0.0495 0.6171 0.2649
-2.250 0.0067 0.00699 0.00137 -0.0493 0.6093 0.3345
-2.000 0.0328 0.00679 0.00130 -0.0490 0.6019 0.3945
-1.750 0.0598 0.00663 0.00127 -0.0489 0.5948 0.4401
-1.500 0.0865 0.00653 0.00124 -0.0486 0.5878 0.4846
-1.250 0.1140 0.00644 0.00122 -0.0485 0.5813 0.5148
-1.000 0.1410 0.00637 0.00120 -0.0483 0.5748 0.5487
-0.500 0.1955 0.00623 0.00119 -0.0480 0.5625 0.6093
-0.250 0.2226 0.00618 0.00119 -0.0478 0.5568 0.6387
0.000 0.2498 0.00610 0.00120 -0.0476 0.5509 0.6718
0.250 0.2762 0.00604 0.00121 -0.0473 0.5450 0.7081
0.500 0.3027 0.00595 0.00124 -0.0469 0.5396 0.7493
0.750 0.3287 0.00585 0.00127 -0.0464 0.5339 0.7934
1.000 0.3536 0.00577 0.00131 -0.0456 0.5284 0.8431
1.250 0.3788 0.00567 0.00138 -0.0448 0.5230 0.8985
1.500 0.4090 0.00570 0.00147 -0.0450 0.5173 0.9431
1.750 0.4437 0.00579 0.00155 -0.0464 0.5115 0.9648
2.000 0.4795 0.00587 0.00160 -0.0480 0.5052 0.9765
2.250 0.5156 0.00597 0.00166 -0.0498 0.4987 0.9839
2.500 0.5558 0.00603 0.00171 -0.0525 0.4913 0.9873
2.750 0.5934 0.00612 0.00176 -0.0547 0.4840 0.9914
3.000 0.6303 0.00618 0.00180 -0.0567 0.4762 0.9947
3.250 0.6689 0.00626 0.00185 -0.0591 0.4681 0.9975
3.500 0.7068 0.00632 0.00189 -0.0614 0.4592 1.0000
3.750 0.7312 0.00640 0.00196 -0.0607 0.4519 1.0000
4.000 0.7552 0.00649 0.00203 -0.0600 0.4438 1.0000
4.250 0.7795 0.00658 0.00211 -0.0593 0.4361 1.0000
4.500 0.8033 0.00670 0.00220 -0.0585 0.4267 1.0000
4.750 0.8277 0.00679 0.00230 -0.0578 0.4174 1.0000
5.000 0.8518 0.00692 0.00241 -0.0570 0.4078 1.0000
5.250 0.8755 0.00706 0.00253 -0.0563 0.3967 1.0000
5.500 0.8993 0.00722 0.00265 -0.0555 0.3845 1.0000
5.750 0.9227 0.00740 0.00279 -0.0546 0.3695 1.0000
6.000 0.9461 0.00759 0.00296 -0.0538 0.3528 1.0000
6.250 0.9689 0.00783 0.00314 -0.0529 0.3325 1.0000
6.500 0.9907 0.00814 0.00336 -0.0519 0.3084 1.0000
6.750 1.0100 0.00864 0.00366 -0.0504 0.2685 1.0000
7.000 1.0275 0.00927 0.00407 -0.0487 0.2222 1.0000
7.250 1.0455 0.00989 0.00449 -0.0471 0.1847 1.0000
7.500 1.0639 0.01048 0.00491 -0.0456 0.1509 1.0000
7.750 1.0827 0.01105 0.00534 -0.0442 0.1236 1.0000
8.000 1.1013 0.01163 0.00578 -0.0428 0.0990 1.0000
8.250 1.1203 0.01217 0.00623 -0.0415 0.0804 1.0000
8.500 1.1396 0.01269 0.00667 -0.0402 0.0655 1.0000
8.750 1.1589 0.01319 0.00711 -0.0390 0.0536 1.0000
9.000 1.1777 0.01370 0.00758 -0.0376 0.0435 1.0000
9.250 1.1956 0.01425 0.00808 -0.0362 0.0342 1.0000
9.500 1.2121 0.01485 0.00865 -0.0345 0.0248 1.0000
9.750 1.2245 0.01566 0.00938 -0.0322 0.0143 1.0000
10.000 1.2377 0.01637 0.01009 -0.0300 0.0103 1.0000
10.250 1.2480 0.01705 0.01079 -0.0273 0.0085 1.0000
10.500 1.2567 0.01774 0.01154 -0.0243 0.0078 1.0000
10.750 1.2686 0.01831 0.01216 -0.0220 0.0073 1.0000
11.000 1.2784 0.01903 0.01294 -0.0196 0.0069 1.0000
11.250 1.2888 0.01976 0.01372 -0.0174 0.0067 1.0000
11.500 1.2952 0.02074 0.01477 -0.0149 0.0062 1.0000
11.750 1.3006 0.02187 0.01597 -0.0125 0.0060 1.0000
12.000 1.3000 0.02348 0.01769 -0.0100 0.0057 1.0000
12.250 1.3026 0.02503 0.01934 -0.0081 0.0055 1.0000
12.500 1.3083 0.02648 0.02086 -0.0067 0.0055 1.0000
12.750 1.3141 0.02803 0.02249 -0.0056 0.0054 1.0000
13.000 1.3143 0.03017 0.02474 -0.0044 0.0053 1.0000
13.250 1.3180 0.03212 0.02676 -0.0037 0.0053 1.0000
13.500 1.3189 0.03443 0.02917 -0.0031 0.0052 1.0000
13.750 1.3213 0.03668 0.03150 -0.0027 0.0050 1.0000
14.000 1.3231 0.03907 0.03398 -0.0025 0.0050 1.0000
14.250 1.3219 0.04182 0.03684 -0.0023 0.0049 1.0000
14.500 1.3182 0.04494 0.04006 -0.0023 0.0049 1.0000
14.750 1.3216 0.04733 0.04252 -0.0025 0.0047 1.0000
15.000 1.3156 0.05086 0.04616 -0.0028 0.0047 1.0000
15.250 1.3121 0.05422 0.04961 -0.0033 0.0046 1.0000
15.500 1.3126 0.05720 0.05266 -0.0039 0.0045 1.0000
15.750 1.3060 0.06113 0.05671 -0.0047 0.0045 1.0000
16.000 1.3011 0.06503 0.06069 -0.0057 0.0044 1.0000
16.250 1.2946 0.06922 0.06499 -0.0069 0.0044 1.0000
16.500 1.2906 0.07323 0.06909 -0.0082 0.0044 1.0000
16.750 1.2827 0.07788 0.07385 -0.0097 0.0044 1.0000
17.000 1.2778 0.08224 0.07830 -0.0113 0.0043 1.0000
17.250 1.2688 0.08735 0.08350 -0.0134 0.0042 1.0000
17.500 1.2624 0.09214 0.08840 -0.0153 0.0042 1.0000
17.750 1.2543 0.09736 0.09371 -0.0175 0.0042 1.0000
18.000 1.2460 0.10269 0.09914 -0.0199 0.0041 1.0000
18.250 1.2364 0.10836 0.10492 -0.0225 0.0041 1.0000
18.500 1.2251 0.11446 0.11112 -0.0255 0.0040 1.0000
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Polar data table (+)
Polar graphs
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