E203 (13.64%) (e203-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 100,000 Max Cl/Cd: 54.97 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e203-il-100000-n5.txt Download as CSV file: xf-e203-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5730 0.07002 0.06456 -0.0677 1.0000 0.0276
-11.250 -0.5950 0.06431 0.05876 -0.0711 1.0000 0.0275
-11.000 -0.6157 0.05958 0.05392 -0.0734 1.0000 0.0274
-10.750 -0.6363 0.05575 0.04998 -0.0743 1.0000 0.0274
-10.500 -0.6576 0.05284 0.04696 -0.0732 1.0000 0.0273
-10.250 -0.6784 0.05051 0.04451 -0.0703 1.0000 0.0273
-10.000 -0.6924 0.04795 0.04175 -0.0677 1.0000 0.0274
-9.750 -0.7022 0.04546 0.03903 -0.0650 1.0000 0.0274
-9.500 -0.7079 0.04309 0.03640 -0.0623 1.0000 0.0276
-9.250 -0.7094 0.04070 0.03382 -0.0598 1.0000 0.0278
-9.000 -0.7075 0.03855 0.03151 -0.0574 1.0000 0.0281
-8.750 -0.7033 0.03672 0.02953 -0.0551 1.0000 0.0285
-8.500 -0.6767 0.03446 0.02704 -0.0569 0.9947 0.0293
-8.250 -0.6465 0.03242 0.02479 -0.0591 0.9879 0.0303
-8.000 -0.6142 0.03077 0.02287 -0.0613 0.9814 0.0322
-7.750 -0.5834 0.02918 0.02103 -0.0629 0.9736 0.0342
-7.500 -0.5523 0.02769 0.01930 -0.0643 0.9661 0.0356
-7.250 -0.5222 0.02604 0.01763 -0.0657 0.9583 0.0373
-7.000 -0.4940 0.02482 0.01633 -0.0667 0.9487 0.0394
-6.750 -0.4609 0.02364 0.01503 -0.0684 0.9419 0.0426
-6.500 -0.4330 0.02256 0.01384 -0.0691 0.9315 0.0471
-6.250 -0.4030 0.02156 0.01278 -0.0702 0.9225 0.0553
-6.000 -0.3713 0.02038 0.01162 -0.0716 0.9148 0.0709
-5.750 -0.3435 0.01941 0.01069 -0.0722 0.9043 0.0965
-5.500 -0.3130 0.01850 0.00992 -0.0734 0.8955 0.1362
-5.250 -0.2835 0.01750 0.00926 -0.0747 0.8865 0.2034
-5.000 -0.2560 0.01670 0.00877 -0.0753 0.8761 0.2741
-4.750 -0.2249 0.01622 0.00843 -0.0761 0.8676 0.3343
-4.500 -0.1946 0.01601 0.00824 -0.0766 0.8577 0.3842
-4.250 -0.1648 0.01591 0.00807 -0.0768 0.8477 0.4209
-4.000 -0.1329 0.01582 0.00786 -0.0774 0.8392 0.4499
-3.750 -0.1042 0.01576 0.00768 -0.0775 0.8289 0.4726
-3.500 -0.0750 0.01571 0.00750 -0.0776 0.8194 0.4922
-3.250 -0.0446 0.01564 0.00733 -0.0778 0.8111 0.5096
-3.000 -0.0173 0.01560 0.00720 -0.0776 0.8011 0.5250
-2.750 0.0117 0.01555 0.00705 -0.0777 0.7927 0.5398
-2.500 0.0399 0.01551 0.00691 -0.0776 0.7839 0.5537
-2.250 0.0677 0.01548 0.00679 -0.0775 0.7753 0.5670
-2.000 0.0962 0.01543 0.00667 -0.0775 0.7676 0.5788
-1.750 0.1230 0.01540 0.00661 -0.0772 0.7591 0.5901
-1.500 0.1516 0.01537 0.00649 -0.0772 0.7521 0.6018
-1.250 0.1781 0.01537 0.00645 -0.0770 0.7438 0.6137
-1.000 0.2065 0.01534 0.00637 -0.0769 0.7372 0.6254
-0.750 0.2326 0.01535 0.00637 -0.0766 0.7293 0.6361
-0.500 0.2607 0.01533 0.00632 -0.0765 0.7228 0.6474
-0.250 0.2872 0.01536 0.00634 -0.0763 0.7154 0.6593
0.000 0.3146 0.01537 0.00633 -0.0761 0.7090 0.6719
0.250 0.3409 0.01540 0.00638 -0.0758 0.7023 0.6843
0.500 0.3674 0.01543 0.00643 -0.0755 0.6956 0.6980
0.750 0.3945 0.01546 0.00648 -0.0752 0.6898 0.7130
1.000 0.4199 0.01552 0.00660 -0.0747 0.6828 0.7297
1.250 0.4472 0.01554 0.00664 -0.0744 0.6775 0.7483
1.500 0.4713 0.01561 0.00682 -0.0736 0.6705 0.7691
1.750 0.4970 0.01565 0.00692 -0.0730 0.6647 0.7935
2.000 0.5219 0.01570 0.00706 -0.0722 0.6587 0.8217
2.250 0.5473 0.01575 0.00724 -0.0715 0.6523 0.8549
2.500 0.5795 0.01577 0.00731 -0.0721 0.6473 0.8937
2.750 0.6158 0.01589 0.00754 -0.0739 0.6398 0.9404
3.000 0.6590 0.01597 0.00765 -0.0773 0.6340 0.9982
3.250 0.6830 0.01621 0.00789 -0.0769 0.6273 1.0000
3.500 0.7081 0.01641 0.00809 -0.0765 0.6209 1.0000
3.750 0.7336 0.01663 0.00833 -0.0763 0.6146 1.0000
4.000 0.7578 0.01686 0.00860 -0.0757 0.6072 1.0000
4.250 0.7838 0.01705 0.00879 -0.0754 0.6004 1.0000
4.500 0.8076 0.01727 0.00907 -0.0748 0.5919 1.0000
4.750 0.8325 0.01746 0.00932 -0.0743 0.5838 1.0000
5.000 0.8576 0.01763 0.00953 -0.0738 0.5751 1.0000
5.250 0.8806 0.01785 0.00984 -0.0729 0.5654 1.0000
5.500 0.9056 0.01799 0.01001 -0.0723 0.5559 1.0000
5.750 0.9294 0.01813 0.01025 -0.0715 0.5450 1.0000
6.000 0.9514 0.01832 0.01054 -0.0705 0.5328 1.0000
6.250 0.9737 0.01849 0.01080 -0.0694 0.5200 1.0000
6.500 0.9956 0.01866 0.01105 -0.0683 0.5062 1.0000
6.750 1.0169 0.01883 0.01130 -0.0670 0.4906 1.0000
7.000 1.0374 0.01902 0.01157 -0.0656 0.4733 1.0000
7.250 1.0566 0.01925 0.01186 -0.0640 0.4535 1.0000
7.500 1.0741 0.01954 0.01220 -0.0622 0.4302 1.0000
7.750 1.0901 0.01991 0.01258 -0.0602 0.4029 1.0000
8.000 1.1037 0.02039 0.01301 -0.0578 0.3703 1.0000
8.250 1.1139 0.02106 0.01358 -0.0550 0.3316 1.0000
8.500 1.1198 0.02197 0.01429 -0.0518 0.2912 1.0000
8.750 1.1213 0.02303 0.01515 -0.0480 0.2557 1.0000
9.000 1.1221 0.02425 0.01622 -0.0444 0.2245 1.0000
9.250 1.1229 0.02560 0.01744 -0.0411 0.1958 1.0000
9.500 1.1242 0.02703 0.01878 -0.0382 0.1709 1.0000
9.750 1.1254 0.02858 0.02025 -0.0356 0.1487 1.0000
10.000 1.1256 0.03031 0.02189 -0.0332 0.1289 1.0000
10.250 1.1264 0.03212 0.02363 -0.0312 0.1098 1.0000
10.500 1.1271 0.03406 0.02552 -0.0294 0.0924 1.0000
10.750 1.1276 0.03614 0.02750 -0.0279 0.0770 1.0000
11.000 1.1294 0.03821 0.02955 -0.0267 0.0650 1.0000
11.250 1.1313 0.04037 0.03174 -0.0256 0.0552 1.0000
11.500 1.1323 0.04271 0.03410 -0.0245 0.0473 1.0000
11.750 1.1312 0.04533 0.03669 -0.0237 0.0413 1.0000
12.000 1.1328 0.04778 0.03928 -0.0230 0.0363 1.0000
12.250 1.1309 0.05066 0.04220 -0.0224 0.0331 1.0000
12.500 1.1295 0.05359 0.04524 -0.0219 0.0303 1.0000
12.750 1.1295 0.05643 0.04822 -0.0215 0.0281 1.0000
13.000 1.1291 0.05940 0.05128 -0.0214 0.0262 1.0000
13.250 1.1265 0.06268 0.05462 -0.0214 0.0249 1.0000
13.500 1.1273 0.06567 0.05777 -0.0213 0.0237 1.0000
13.750 1.1290 0.06866 0.06093 -0.0215 0.0220 1.0000
14.000 1.1297 0.07183 0.06423 -0.0218 0.0209 1.0000
14.250 1.1297 0.07516 0.06768 -0.0222 0.0201 1.0000
14.500 1.1293 0.07861 0.07123 -0.0229 0.0195 1.0000
14.750 1.1280 0.08225 0.07495 -0.0236 0.0189 1.0000
15.000 1.1283 0.08576 0.07857 -0.0241 0.0185 1.0000
15.250 1.1286 0.08944 0.08245 -0.0248 0.0182 1.0000
15.500 1.1270 0.09354 0.08677 -0.0258 0.0178 1.0000
15.750 1.1241 0.09793 0.09137 -0.0271 0.0175 1.0000
16.000 1.1188 0.10284 0.09650 -0.0289 0.0173 1.0000
16.250 1.1114 0.10829 0.10217 -0.0312 0.0170 1.0000
16.500 1.1024 0.11420 0.10830 -0.0340 0.0169 1.0000
16.750 1.0911 0.12076 0.11508 -0.0374 0.0169 1.0000
17.000 1.0771 0.12821 0.12275 -0.0416 0.0168 1.0000
17.250 1.0614 0.13642 0.13116 -0.0465 0.0169 1.0000
17.500 1.0420 0.14611 0.14106 -0.0526 0.0171 1.0000
17.750 1.0182 0.15780 0.15294 -0.0601 0.0173 1.0000
18.000 0.9904 0.17194 0.16721 -0.0688 0.0178 1.0000
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Polar data table (+)
Polar graphs
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