E209 (13.72%) (e209-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 100,000 Max Cl/Cd: 51.5 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e209-il-100000-n5.txt Download as CSV file: xf-e209-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5507 0.09120 0.08598 -0.0424 1.0000 0.0247
-12.000 -0.5763 0.08149 0.07623 -0.0486 1.0000 0.0242
-11.750 -0.6059 0.07242 0.06705 -0.0549 1.0000 0.0239
-11.500 -0.6313 0.06535 0.05987 -0.0598 1.0000 0.0237
-11.250 -0.6519 0.05994 0.05432 -0.0630 1.0000 0.0235
-11.000 -0.6729 0.05529 0.04948 -0.0649 1.0000 0.0235
-10.750 -0.6909 0.05171 0.04572 -0.0650 1.0000 0.0235
-10.500 -0.7093 0.04879 0.04261 -0.0631 1.0000 0.0236
-10.250 -0.7249 0.04630 0.03992 -0.0599 1.0000 0.0237
-10.000 -0.7334 0.04371 0.03707 -0.0572 1.0000 0.0239
-9.750 -0.7385 0.04108 0.03411 -0.0543 1.0000 0.0244
-9.500 -0.7377 0.03875 0.03143 -0.0517 1.0000 0.0249
-9.250 -0.7331 0.03662 0.02909 -0.0493 1.0000 0.0256
-9.000 -0.7249 0.03511 0.02755 -0.0473 1.0000 0.0267
-8.750 -0.7156 0.03389 0.02625 -0.0453 1.0000 0.0282
-8.500 -0.7054 0.03243 0.02460 -0.0431 1.0000 0.0298
-8.250 -0.6938 0.03089 0.02286 -0.0409 1.0000 0.0311
-8.000 -0.6813 0.02945 0.02120 -0.0387 1.0000 0.0323
-7.750 -0.6706 0.02809 0.01985 -0.0366 1.0000 0.0340
-7.500 -0.6590 0.02718 0.01891 -0.0345 1.0000 0.0363
-7.250 -0.6341 0.02602 0.01760 -0.0347 0.9961 0.0398
-7.000 -0.6004 0.02456 0.01604 -0.0367 0.9879 0.0431
-6.750 -0.5663 0.02348 0.01491 -0.0389 0.9790 0.0491
-6.500 -0.5324 0.02226 0.01363 -0.0409 0.9700 0.0558
-6.250 -0.5016 0.02121 0.01250 -0.0420 0.9583 0.0656
-6.000 -0.4714 0.02016 0.01152 -0.0432 0.9462 0.0829
-5.750 -0.4404 0.01920 0.01063 -0.0444 0.9340 0.1083
-5.500 -0.4090 0.01831 0.00986 -0.0458 0.9221 0.1466
-5.250 -0.3788 0.01734 0.00915 -0.0469 0.9096 0.2051
-5.000 -0.3486 0.01643 0.00856 -0.0480 0.8969 0.2769
-4.750 -0.3182 0.01583 0.00822 -0.0487 0.8836 0.3463
-4.500 -0.2871 0.01555 0.00798 -0.0492 0.8694 0.4030
-4.250 -0.2558 0.01539 0.00775 -0.0497 0.8550 0.4435
-4.000 -0.2251 0.01528 0.00754 -0.0500 0.8405 0.4745
-3.750 -0.1950 0.01519 0.00732 -0.0501 0.8259 0.5000
-3.500 -0.1659 0.01511 0.00713 -0.0501 0.8114 0.5203
-3.250 -0.1374 0.01505 0.00696 -0.0499 0.7974 0.5389
-3.000 -0.1093 0.01499 0.00679 -0.0497 0.7837 0.5560
-2.750 -0.0816 0.01495 0.00663 -0.0494 0.7708 0.5720
-2.500 -0.0539 0.01490 0.00648 -0.0491 0.7587 0.5869
-2.250 -0.0261 0.01486 0.00634 -0.0489 0.7475 0.6010
-2.000 0.0007 0.01482 0.00623 -0.0485 0.7357 0.6145
-1.750 0.0276 0.01480 0.00613 -0.0482 0.7249 0.6277
-1.500 0.0549 0.01477 0.00602 -0.0479 0.7151 0.6408
-1.250 0.0819 0.01475 0.00593 -0.0476 0.7051 0.6538
-1.000 0.1086 0.01474 0.00588 -0.0473 0.6955 0.6665
-0.750 0.1360 0.01473 0.00581 -0.0470 0.6872 0.6789
-0.500 0.1625 0.01472 0.00580 -0.0466 0.6777 0.6918
-0.250 0.1896 0.01473 0.00577 -0.0463 0.6697 0.7052
0.000 0.2165 0.01474 0.00578 -0.0461 0.6613 0.7197
0.250 0.2432 0.01477 0.00580 -0.0457 0.6534 0.7352
0.500 0.2699 0.01479 0.00583 -0.0453 0.6457 0.7522
0.750 0.2963 0.01483 0.00589 -0.0449 0.6382 0.7710
1.000 0.3230 0.01487 0.00596 -0.0444 0.6307 0.7917
1.250 0.3500 0.01492 0.00606 -0.0440 0.6237 0.8144
1.500 0.3782 0.01499 0.00617 -0.0439 0.6164 0.8396
1.750 0.4088 0.01507 0.00629 -0.0442 0.6095 0.8669
2.000 0.4430 0.01518 0.00644 -0.0454 0.6021 0.8944
2.250 0.4813 0.01530 0.00656 -0.0474 0.5953 0.9206
2.500 0.5202 0.01544 0.00674 -0.0498 0.5876 0.9464
2.750 0.5598 0.01558 0.00685 -0.0523 0.5810 0.9700
3.000 0.6014 0.01573 0.00705 -0.0554 0.5730 0.9900
3.250 0.6336 0.01589 0.00717 -0.0566 0.5669 1.0000
3.500 0.6537 0.01611 0.00743 -0.0554 0.5594 1.0000
3.750 0.6765 0.01630 0.00760 -0.0546 0.5536 1.0000
4.000 0.6975 0.01655 0.00790 -0.0535 0.5461 1.0000
4.250 0.7208 0.01676 0.00810 -0.0527 0.5396 1.0000
4.500 0.7427 0.01701 0.00840 -0.0517 0.5318 1.0000
4.750 0.7663 0.01721 0.00862 -0.0509 0.5244 1.0000
5.000 0.7882 0.01745 0.00894 -0.0499 0.5155 1.0000
5.250 0.8125 0.01762 0.00910 -0.0492 0.5078 1.0000
5.500 0.8340 0.01786 0.00945 -0.0481 0.4978 1.0000
5.750 0.8568 0.01807 0.00974 -0.0472 0.4883 1.0000
6.000 0.8803 0.01824 0.00993 -0.0463 0.4788 1.0000
6.250 0.9016 0.01847 0.01028 -0.0452 0.4673 1.0000
6.500 0.9232 0.01868 0.01058 -0.0441 0.4554 1.0000
6.750 0.9448 0.01889 0.01088 -0.0430 0.4428 1.0000
7.000 0.9658 0.01910 0.01117 -0.0417 0.4292 1.0000
7.250 0.9862 0.01933 0.01149 -0.0404 0.4140 1.0000
7.500 1.0058 0.01959 0.01183 -0.0390 0.3973 1.0000
7.750 1.0244 0.01989 0.01217 -0.0374 0.3787 1.0000
8.000 1.0417 0.02025 0.01260 -0.0357 0.3573 1.0000
8.250 1.0572 0.02069 0.01303 -0.0338 0.3327 1.0000
8.500 1.0710 0.02125 0.01357 -0.0317 0.3045 1.0000
8.750 1.0818 0.02197 0.01421 -0.0292 0.2730 1.0000
9.000 1.0894 0.02288 0.01499 -0.0264 0.2408 1.0000
9.250 1.0936 0.02396 0.01593 -0.0234 0.2112 1.0000
9.500 1.0944 0.02512 0.01700 -0.0199 0.1871 1.0000
9.750 1.0952 0.02641 0.01821 -0.0167 0.1653 1.0000
10.000 1.0951 0.02785 0.01958 -0.0138 0.1471 1.0000
10.250 1.0959 0.02937 0.02108 -0.0113 0.1306 1.0000
10.500 1.0958 0.03107 0.02276 -0.0091 0.1163 1.0000
10.750 1.0953 0.03295 0.02462 -0.0073 0.1050 1.0000
11.000 1.0941 0.03503 0.02670 -0.0058 0.0945 1.0000
11.250 1.0950 0.03710 0.02883 -0.0046 0.0850 1.0000
11.500 1.0945 0.03940 0.03116 -0.0037 0.0776 1.0000
11.750 1.0933 0.04189 0.03368 -0.0030 0.0709 1.0000
12.000 1.0935 0.04436 0.03622 -0.0025 0.0649 1.0000
12.250 1.0927 0.04701 0.03895 -0.0021 0.0600 1.0000
12.500 1.0911 0.04981 0.04179 -0.0018 0.0557 1.0000
12.750 1.0921 0.05243 0.04453 -0.0017 0.0512 1.0000
13.000 1.0899 0.05544 0.04757 -0.0018 0.0479 1.0000
13.250 1.0899 0.05828 0.05049 -0.0017 0.0448 1.0000
13.500 1.0905 0.06114 0.05348 -0.0018 0.0415 1.0000
13.750 1.0895 0.06425 0.05666 -0.0022 0.0391 1.0000
14.000 1.0869 0.06760 0.06003 -0.0027 0.0368 1.0000
14.250 1.0889 0.07053 0.06316 -0.0029 0.0346 1.0000
14.500 1.0880 0.07394 0.06669 -0.0037 0.0323 1.0000
14.750 1.0865 0.07745 0.07029 -0.0046 0.0308 1.0000
15.000 1.0832 0.08126 0.07412 -0.0057 0.0293 1.0000
15.250 1.0828 0.08487 0.07791 -0.0065 0.0280 1.0000
15.500 1.0811 0.08878 0.08205 -0.0076 0.0267 1.0000
15.750 1.0778 0.09302 0.08646 -0.0091 0.0256 1.0000
16.000 1.0732 0.09757 0.09115 -0.0109 0.0244 1.0000
16.250 1.0687 0.10217 0.09585 -0.0129 0.0236 1.0000
16.500 1.0646 0.10672 0.10047 -0.0150 0.0229 1.0000
16.750 1.0599 0.11144 0.10525 -0.0171 0.0221 1.0000
17.000 1.0495 0.11773 0.11180 -0.0203 0.0216 1.0000
17.250 1.0395 0.12410 0.11837 -0.0236 0.0214 1.0000
17.500 1.0261 0.13145 0.12594 -0.0277 0.0211 1.0000
17.750 1.0110 0.13950 0.13418 -0.0324 0.0210 1.0000
18.000 0.9914 0.14915 0.14402 -0.0383 0.0210 1.0000
18.250 0.9666 0.16096 0.15600 -0.0454 0.0212 1.0000
18.500 0.9359 0.17575 0.17088 -0.0539 0.0217 1.0000
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Polar data table (+)
Polar graphs
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