E205 (10.48%) (e205-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 200,000 Max Cl/Cd: 74.02 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e205-il-200000-n5.txt Download as CSV file: xf-e205-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4235 0.08575 0.08227 -0.0308 1.0000 0.0189
-9.000 -0.4255 0.08170 0.07826 -0.0326 1.0000 0.0186
-8.750 -0.4298 0.07729 0.07390 -0.0347 1.0000 0.0184
-8.500 -0.4375 0.07261 0.06930 -0.0373 1.0000 0.0182
-8.250 -0.4504 0.06785 0.06461 -0.0403 1.0000 0.0180
-8.000 -0.4610 0.06184 0.05861 -0.0442 1.0000 0.0178
-7.750 -0.4703 0.05574 0.05243 -0.0465 1.0000 0.0175
-7.500 -0.4814 0.04928 0.04580 -0.0471 1.0000 0.0173
-7.250 -0.4775 0.04120 0.03727 -0.0503 0.9897 0.0171
-7.000 -0.4603 0.03444 0.02987 -0.0533 0.9749 0.0171
-6.750 -0.4383 0.03008 0.02493 -0.0547 0.9593 0.0175
-6.500 -0.4121 0.02709 0.02138 -0.0557 0.9431 0.0184
-6.250 -0.3839 0.02467 0.01847 -0.0565 0.9253 0.0188
-6.000 -0.3545 0.02250 0.01587 -0.0573 0.9061 0.0189
-5.750 -0.3245 0.02078 0.01376 -0.0579 0.8860 0.0190
-5.500 -0.2966 0.01942 0.01209 -0.0578 0.8641 0.0192
-5.250 -0.2703 0.01817 0.01060 -0.0574 0.8426 0.0195
-5.000 -0.2460 0.01696 0.00919 -0.0567 0.8217 0.0201
-4.750 -0.2219 0.01610 0.00817 -0.0559 0.8021 0.0207
-4.500 -0.1976 0.01545 0.00737 -0.0551 0.7842 0.0215
-4.250 -0.1730 0.01491 0.00667 -0.0543 0.7675 0.0225
-4.000 -0.1480 0.01451 0.00613 -0.0537 0.7519 0.0242
-3.750 -0.1228 0.01414 0.00561 -0.0530 0.7377 0.0262
-3.500 -0.0978 0.01370 0.00502 -0.0524 0.7246 0.0279
-3.250 -0.0724 0.01334 0.00456 -0.0518 0.7122 0.0308
-3.000 -0.0466 0.01301 0.00413 -0.0512 0.7004 0.0376
-2.750 -0.0213 0.01262 0.00378 -0.0507 0.6896 0.0638
-2.500 0.0041 0.01228 0.00354 -0.0502 0.6796 0.1048
-2.250 0.0290 0.01191 0.00335 -0.0498 0.6699 0.1671
-2.000 0.0536 0.01150 0.00320 -0.0494 0.6606 0.2474
-1.500 0.1005 0.01062 0.00301 -0.0479 0.6437 0.4623
-1.250 0.1223 0.01017 0.00295 -0.0466 0.6361 0.5854
-1.000 0.1434 0.00968 0.00295 -0.0448 0.6285 0.7320
-0.750 0.1902 0.00946 0.00302 -0.0478 0.6206 0.8827
-0.500 0.2441 0.00955 0.00298 -0.0529 0.6127 0.9475
-0.250 0.2846 0.00964 0.00296 -0.0554 0.6050 0.9748
0.000 0.3287 0.00970 0.00287 -0.0589 0.5978 0.9911
0.250 0.3691 0.00973 0.00280 -0.0617 0.5904 1.0000
0.500 0.3934 0.00982 0.00278 -0.0610 0.5840 1.0000
0.750 0.4180 0.00989 0.00279 -0.0604 0.5775 1.0000
1.000 0.4426 0.00998 0.00281 -0.0597 0.5712 1.0000
1.250 0.4673 0.01008 0.00284 -0.0591 0.5653 1.0000
1.500 0.4920 0.01017 0.00289 -0.0585 0.5587 1.0000
1.750 0.5167 0.01030 0.00294 -0.0578 0.5533 1.0000
2.000 0.5417 0.01039 0.00303 -0.0573 0.5466 1.0000
2.250 0.5665 0.01052 0.00311 -0.0567 0.5408 1.0000
2.500 0.5914 0.01064 0.00323 -0.0561 0.5348 1.0000
2.750 0.6163 0.01076 0.00334 -0.0555 0.5285 1.0000
3.000 0.6412 0.01090 0.00345 -0.0549 0.5227 1.0000
3.250 0.6661 0.01102 0.00359 -0.0543 0.5158 1.0000
3.500 0.6909 0.01118 0.00373 -0.0537 0.5099 1.0000
3.750 0.7157 0.01130 0.00390 -0.0531 0.5022 1.0000
4.000 0.7402 0.01145 0.00404 -0.0524 0.4951 1.0000
4.250 0.7648 0.01159 0.00421 -0.0518 0.4862 1.0000
4.500 0.7892 0.01173 0.00440 -0.0511 0.4776 1.0000
4.750 0.8134 0.01189 0.00456 -0.0504 0.4687 1.0000
5.000 0.8377 0.01204 0.00476 -0.0497 0.4584 1.0000
5.250 0.8618 0.01220 0.00496 -0.0490 0.4482 1.0000
5.500 0.8856 0.01238 0.00516 -0.0482 0.4375 1.0000
5.750 0.9092 0.01257 0.00539 -0.0474 0.4253 1.0000
6.000 0.9327 0.01277 0.00563 -0.0466 0.4118 1.0000
6.250 0.9558 0.01299 0.00588 -0.0458 0.3966 1.0000
6.500 0.9787 0.01323 0.00616 -0.0449 0.3794 1.0000
6.750 1.0008 0.01352 0.00646 -0.0439 0.3586 1.0000
7.000 1.0218 0.01388 0.00682 -0.0428 0.3325 1.0000
7.250 1.0412 0.01436 0.00721 -0.0415 0.3000 1.0000
7.500 1.0582 0.01503 0.00772 -0.0399 0.2587 1.0000
7.750 1.0719 0.01596 0.00840 -0.0380 0.2098 1.0000
8.000 1.0845 0.01701 0.00920 -0.0360 0.1656 1.0000
8.250 1.0978 0.01798 0.01003 -0.0341 0.1326 1.0000
8.500 1.1099 0.01901 0.01089 -0.0321 0.1014 1.0000
8.750 1.1225 0.01996 0.01174 -0.0302 0.0795 1.0000
9.000 1.1341 0.02092 0.01262 -0.0281 0.0608 1.0000
9.250 1.1448 0.02190 0.01355 -0.0259 0.0466 1.0000
9.500 1.1535 0.02287 0.01451 -0.0235 0.0353 1.0000
9.750 1.1580 0.02397 0.01561 -0.0204 0.0255 1.0000
10.000 1.1615 0.02522 0.01686 -0.0176 0.0194 1.0000
10.250 1.1647 0.02658 0.01827 -0.0150 0.0154 1.0000
10.500 1.1688 0.02800 0.01979 -0.0129 0.0141 1.0000
10.750 1.1740 0.02944 0.02134 -0.0112 0.0124 1.0000
11.000 1.1776 0.03111 0.02312 -0.0097 0.0116 1.0000
11.250 1.1799 0.03303 0.02514 -0.0084 0.0110 1.0000
11.500 1.1790 0.03536 0.02760 -0.0074 0.0104 1.0000
11.750 1.1807 0.03758 0.02994 -0.0066 0.0102 1.0000
12.000 1.1814 0.04001 0.03251 -0.0061 0.0099 1.0000
12.250 1.1820 0.04254 0.03518 -0.0057 0.0097 1.0000
12.500 1.1819 0.04522 0.03799 -0.0055 0.0095 1.0000
12.750 1.1808 0.04810 0.04101 -0.0055 0.0093 1.0000
13.000 1.1797 0.05103 0.04407 -0.0055 0.0092 1.0000
13.250 1.1779 0.05412 0.04728 -0.0057 0.0090 1.0000
13.500 1.1760 0.05728 0.05058 -0.0059 0.0088 1.0000
13.750 1.1736 0.06057 0.05402 -0.0063 0.0087 1.0000
14.000 1.1720 0.06386 0.05744 -0.0067 0.0086 1.0000
14.250 1.1694 0.06737 0.06108 -0.0074 0.0085 1.0000
14.500 1.1669 0.07099 0.06483 -0.0081 0.0083 1.0000
14.750 1.1645 0.07471 0.06869 -0.0089 0.0083 1.0000
15.000 1.1616 0.07858 0.07270 -0.0100 0.0082 1.0000
15.250 1.1583 0.08263 0.07689 -0.0112 0.0081 1.0000
15.500 1.1534 0.08710 0.08149 -0.0128 0.0079 1.0000
15.750 1.1485 0.09167 0.08622 -0.0144 0.0079 1.0000
16.000 1.1429 0.09651 0.09120 -0.0164 0.0078 1.0000
16.250 1.1366 0.10160 0.09642 -0.0187 0.0077 1.0000
16.500 1.1290 0.10709 0.10207 -0.0212 0.0076 1.0000
16.750 1.1211 0.11277 0.10791 -0.0240 0.0076 1.0000
17.000 1.1122 0.11879 0.11404 -0.0271 0.0074 1.0000
17.250 1.1027 0.12528 0.12073 -0.0306 0.0075 1.0000
17.500 1.0932 0.13184 0.12741 -0.0343 0.0073 1.0000
17.750 1.0826 0.13894 0.13466 -0.0384 0.0073 1.0000
18.000 1.0707 0.14658 0.14245 -0.0429 0.0073 1.0000
18.250 1.0574 0.15505 0.15109 -0.0480 0.0073 1.0000
18.500 1.0271 0.16953 0.16587 -0.0565 0.0078 1.0000
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Polar data table (+)
Polar graphs
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