E207 (12.04%) (e207-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 500,000 Max Cl/Cd: 96.06 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e207-il-500000-n5.txt Download as CSV file: xf-e207-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7063 0.06358 0.06095 -0.0484 1.0000 0.0085
-12.250 -0.7332 0.05355 0.05073 -0.0566 1.0000 0.0085
-12.000 -0.7585 0.04563 0.04262 -0.0634 1.0000 0.0084
-11.750 -0.7774 0.04054 0.03734 -0.0668 1.0000 0.0084
-11.500 -0.7929 0.03736 0.03397 -0.0666 1.0000 0.0085
-11.250 -0.8064 0.03529 0.03174 -0.0636 1.0000 0.0085
-11.000 -0.8141 0.03338 0.02965 -0.0603 1.0000 0.0086
-10.750 -0.8143 0.03166 0.02774 -0.0577 1.0000 0.0087
-10.500 -0.8209 0.02902 0.02484 -0.0544 1.0000 0.0089
-10.250 -0.8150 0.02756 0.02325 -0.0520 1.0000 0.0091
-10.000 -0.8060 0.02635 0.02193 -0.0497 1.0000 0.0092
-9.750 -0.7839 0.02522 0.02068 -0.0499 0.9979 0.0095
-9.500 -0.7548 0.02410 0.01943 -0.0514 0.9939 0.0098
-9.250 -0.7269 0.02316 0.01837 -0.0524 0.9892 0.0103
-9.000 -0.6971 0.02207 0.01711 -0.0538 0.9847 0.0108
-8.750 -0.6695 0.02090 0.01576 -0.0545 0.9786 0.0112
-8.250 -0.6132 0.01881 0.01335 -0.0559 0.9621 0.0119
-8.000 -0.5835 0.01792 0.01231 -0.0567 0.9503 0.0122
-7.750 -0.5516 0.01716 0.01141 -0.0579 0.9344 0.0125
-7.500 -0.5226 0.01572 0.00980 -0.0588 0.9124 0.0132
-7.250 -0.4951 0.01507 0.00901 -0.0590 0.8837 0.0138
-7.000 -0.4712 0.01459 0.00837 -0.0583 0.8538 0.0143
-6.750 -0.4483 0.01412 0.00774 -0.0573 0.8269 0.0147
-6.500 -0.4251 0.01370 0.00715 -0.0565 0.8026 0.0152
-6.250 -0.4017 0.01329 0.00658 -0.0556 0.7813 0.0156
-6.000 -0.3777 0.01292 0.00606 -0.0549 0.7619 0.0160
-5.750 -0.3534 0.01258 0.00559 -0.0543 0.7439 0.0165
-5.500 -0.3286 0.01227 0.00515 -0.0537 0.7276 0.0169
-5.250 -0.3036 0.01197 0.00473 -0.0531 0.7128 0.0175
-5.000 -0.2787 0.01160 0.00425 -0.0526 0.6992 0.0187
-4.750 -0.2531 0.01134 0.00390 -0.0521 0.6865 0.0199
-4.500 -0.2271 0.01113 0.00360 -0.0518 0.6750 0.0211
-4.250 -0.2010 0.01094 0.00332 -0.0514 0.6640 0.0225
-4.000 -0.1746 0.01074 0.00305 -0.0511 0.6534 0.0259
-3.750 -0.1486 0.01048 0.00282 -0.0507 0.6440 0.0387
-3.500 -0.1227 0.01024 0.00261 -0.0504 0.6350 0.0601
-3.250 -0.0966 0.00998 0.00242 -0.0501 0.6261 0.0867
-3.000 -0.0708 0.00971 0.00225 -0.0499 0.6182 0.1242
-2.750 -0.0444 0.00949 0.00211 -0.0496 0.6103 0.1573
-2.500 -0.0181 0.00928 0.00198 -0.0494 0.6030 0.1943
-2.250 0.0079 0.00901 0.00186 -0.0492 0.5957 0.2460
-2.000 0.0338 0.00876 0.00176 -0.0489 0.5891 0.3018
-1.750 0.0592 0.00844 0.00169 -0.0486 0.5824 0.3830
-1.500 0.0850 0.00825 0.00166 -0.0483 0.5761 0.4445
-1.250 0.1116 0.00810 0.00163 -0.0480 0.5697 0.4891
-1.000 0.1385 0.00804 0.00160 -0.0478 0.5637 0.5171
-0.750 0.1657 0.00798 0.00158 -0.0476 0.5576 0.5428
-0.500 0.1926 0.00792 0.00157 -0.0474 0.5516 0.5704
-0.250 0.2194 0.00787 0.00156 -0.0471 0.5462 0.5986
0.000 0.2462 0.00780 0.00157 -0.0469 0.5403 0.6280
0.250 0.2727 0.00775 0.00158 -0.0466 0.5347 0.6595
0.500 0.2991 0.00767 0.00161 -0.0462 0.5295 0.6942
0.750 0.3251 0.00759 0.00164 -0.0457 0.5237 0.7342
1.000 0.3504 0.00752 0.00168 -0.0451 0.5185 0.7778
1.250 0.3757 0.00741 0.00174 -0.0443 0.5131 0.8257
1.500 0.4018 0.00736 0.00182 -0.0437 0.5075 0.8761
1.750 0.4346 0.00739 0.00192 -0.0445 0.5021 0.9182
2.000 0.4715 0.00746 0.00200 -0.0464 0.4960 0.9439
2.250 0.5064 0.00756 0.00206 -0.0479 0.4902 0.9604
2.500 0.5402 0.00764 0.00214 -0.0491 0.4842 0.9720
2.750 0.5740 0.00773 0.00221 -0.0505 0.4776 0.9807
3.000 0.6098 0.00782 0.00227 -0.0522 0.4702 0.9864
3.250 0.6446 0.00792 0.00235 -0.0538 0.4620 0.9920
3.500 0.6798 0.00801 0.00243 -0.0555 0.4532 0.9966
3.750 0.7134 0.00812 0.00252 -0.0569 0.4443 1.0000
4.000 0.7372 0.00823 0.00262 -0.0561 0.4347 1.0000
4.250 0.7612 0.00835 0.00273 -0.0553 0.4253 1.0000
4.500 0.7849 0.00849 0.00285 -0.0545 0.4158 1.0000
4.750 0.8087 0.00864 0.00298 -0.0538 0.4052 1.0000
5.000 0.8325 0.00879 0.00312 -0.0530 0.3938 1.0000
5.250 0.8560 0.00896 0.00328 -0.0522 0.3806 1.0000
5.500 0.8793 0.00916 0.00345 -0.0513 0.3662 1.0000
5.750 0.9020 0.00939 0.00364 -0.0504 0.3495 1.0000
6.000 0.9243 0.00966 0.00386 -0.0495 0.3292 1.0000
6.250 0.9461 0.00998 0.00412 -0.0484 0.3063 1.0000
6.500 0.9663 0.01043 0.00443 -0.0472 0.2743 1.0000
6.750 0.9852 0.01099 0.00482 -0.0458 0.2365 1.0000
7.000 1.0044 0.01155 0.00524 -0.0445 0.2059 1.0000
7.250 1.0222 0.01221 0.00572 -0.0430 0.1702 1.0000
7.500 1.0404 0.01284 0.00622 -0.0415 0.1413 1.0000
7.750 1.0568 0.01359 0.00678 -0.0399 0.1101 1.0000
8.000 1.0756 0.01414 0.00726 -0.0386 0.0917 1.0000
8.250 1.0935 0.01473 0.00778 -0.0372 0.0753 1.0000
8.500 1.1106 0.01536 0.00833 -0.0356 0.0605 1.0000
8.750 1.1277 0.01595 0.00888 -0.0341 0.0491 1.0000
9.000 1.1441 0.01656 0.00946 -0.0325 0.0395 1.0000
9.250 1.1596 0.01718 0.01007 -0.0307 0.0312 1.0000
9.500 1.1745 0.01779 0.01068 -0.0289 0.0248 1.0000
9.750 1.1855 0.01846 0.01134 -0.0264 0.0188 1.0000
10.000 1.1941 0.01922 0.01209 -0.0236 0.0135 1.0000
10.250 1.2023 0.02003 0.01291 -0.0210 0.0102 1.0000
10.500 1.2112 0.02086 0.01378 -0.0186 0.0086 1.0000
10.750 1.2204 0.02172 0.01472 -0.0164 0.0077 1.0000
11.000 1.2286 0.02269 0.01576 -0.0143 0.0071 1.0000
11.250 1.2344 0.02389 0.01703 -0.0122 0.0063 1.0000
11.500 1.2408 0.02514 0.01836 -0.0104 0.0061 1.0000
11.750 1.2466 0.02654 0.01985 -0.0089 0.0057 1.0000
12.000 1.2532 0.02797 0.02137 -0.0076 0.0055 1.0000
12.250 1.2603 0.02943 0.02291 -0.0066 0.0053 1.0000
12.500 1.2647 0.03122 0.02480 -0.0057 0.0051 1.0000
12.750 1.2677 0.03326 0.02695 -0.0049 0.0049 1.0000
13.000 1.2718 0.03526 0.02903 -0.0044 0.0047 1.0000
13.250 1.2752 0.03739 0.03127 -0.0040 0.0045 1.0000
13.500 1.2752 0.03997 0.03394 -0.0037 0.0044 1.0000
13.750 1.2761 0.04251 0.03659 -0.0036 0.0043 1.0000
14.000 1.2745 0.04541 0.03958 -0.0036 0.0042 1.0000
14.250 1.2727 0.04839 0.04267 -0.0037 0.0041 1.0000
14.500 1.2674 0.05187 0.04626 -0.0041 0.0040 1.0000
14.750 1.2637 0.05527 0.04977 -0.0046 0.0040 1.0000
15.000 1.2556 0.05934 0.05396 -0.0054 0.0039 1.0000
15.250 1.2511 0.06310 0.05782 -0.0063 0.0038 1.0000
15.500 1.2473 0.06691 0.06174 -0.0073 0.0038 1.0000
15.750 1.2420 0.07103 0.06597 -0.0085 0.0038 1.0000
16.000 1.2387 0.07498 0.07004 -0.0098 0.0037 1.0000
16.250 1.2320 0.07958 0.07475 -0.0114 0.0037 1.0000
16.500 1.2275 0.08391 0.07919 -0.0130 0.0037 1.0000
16.750 1.2192 0.08900 0.08441 -0.0150 0.0037 1.0000
17.000 1.2143 0.09365 0.08917 -0.0169 0.0036 1.0000
17.250 1.2056 0.09907 0.09471 -0.0193 0.0036 1.0000
17.500 1.1996 0.10410 0.09986 -0.0215 0.0036 1.0000
17.750 1.1923 0.10950 0.10540 -0.0241 0.0035 1.0000
18.000 1.1839 0.11520 0.11121 -0.0268 0.0035 1.0000
18.250 1.1759 0.12094 0.11706 -0.0297 0.0035 1.0000
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Polar data table (+)
Polar graphs
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