E193 (10.22%) (e193-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 200,000 Max Cl/Cd: 82.26 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e193-il-200000.txt Download as CSV file: xf-e193-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E193 (10.22%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3614 0.08676 0.08353 -0.0434 1.0000 0.0506
-8.000 -0.3770 0.08405 0.08093 -0.0447 1.0000 0.0508
-7.750 -0.3878 0.08060 0.07755 -0.0474 1.0000 0.0510
-7.500 -0.4030 0.07795 0.07494 -0.0471 1.0000 0.0511
-7.250 -0.4069 0.07226 0.06931 -0.0484 0.9971 0.0518
-7.000 -0.3841 0.06969 0.06679 -0.0472 0.9933 0.0533
-6.750 -0.3549 0.06554 0.06258 -0.0527 0.9865 0.0554
-6.500 -0.3166 0.05666 0.05330 -0.0702 0.9740 0.0628
-6.250 -0.2941 0.04938 0.04582 -0.0768 0.9636 0.0652
-6.000 -0.2606 0.04613 0.04257 -0.0803 0.9588 0.0675
-5.750 -0.2318 0.04099 0.03675 -0.0863 0.9458 0.0779
-5.500 -0.2068 0.02920 0.02370 -0.0872 0.9337 0.0406
-5.250 -0.1764 0.02623 0.02043 -0.0883 0.9233 0.0392
-5.000 -0.1477 0.02250 0.01623 -0.0890 0.9133 0.0370
-4.750 -0.1192 0.01998 0.01324 -0.0888 0.9016 0.0356
-4.500 -0.0916 0.01824 0.01114 -0.0883 0.8888 0.0354
-4.250 -0.0644 0.01692 0.00959 -0.0878 0.8763 0.0360
-4.000 -0.0378 0.01587 0.00838 -0.0871 0.8643 0.0375
-3.750 -0.0112 0.01514 0.00747 -0.0864 0.8530 0.0398
-3.500 0.0133 0.01419 0.00650 -0.0857 0.8420 0.0456
-3.250 0.0381 0.01349 0.00572 -0.0849 0.8303 0.0532
-3.000 0.0620 0.01242 0.00490 -0.0840 0.8201 0.1132
-2.750 0.0870 0.01187 0.00462 -0.0836 0.8111 0.2000
-2.500 0.1109 0.01138 0.00449 -0.0831 0.8008 0.3059
-2.250 0.1340 0.01087 0.00442 -0.0823 0.7920 0.4360
-2.000 0.1568 0.01044 0.00435 -0.0812 0.7837 0.5579
-1.750 0.1771 0.01000 0.00435 -0.0792 0.7750 0.6970
-1.500 0.2062 0.00961 0.00436 -0.0781 0.7682 0.8754
-1.250 0.2760 0.00955 0.00417 -0.0862 0.7606 0.9837
-1.000 0.3211 0.00956 0.00395 -0.0900 0.7535 1.0000
-0.750 0.3445 0.00966 0.00393 -0.0892 0.7453 1.0000
-0.500 0.3690 0.00977 0.00387 -0.0886 0.7385 1.0000
-0.250 0.3930 0.00989 0.00389 -0.0879 0.7307 1.0000
0.000 0.4180 0.01002 0.00388 -0.0873 0.7243 1.0000
0.250 0.4423 0.01016 0.00394 -0.0867 0.7170 1.0000
0.500 0.4675 0.01029 0.00397 -0.0861 0.7105 1.0000
0.750 0.4924 0.01045 0.00406 -0.0855 0.7040 1.0000
1.000 0.5176 0.01059 0.00413 -0.0850 0.6973 1.0000
1.250 0.5433 0.01076 0.00422 -0.0846 0.6915 1.0000
1.500 0.5682 0.01091 0.00436 -0.0840 0.6845 1.0000
1.750 0.5946 0.01108 0.00443 -0.0837 0.6791 1.0000
2.000 0.6194 0.01125 0.00463 -0.0832 0.6720 1.0000
2.250 0.6456 0.01141 0.00475 -0.0828 0.6661 1.0000
2.500 0.6711 0.01160 0.00493 -0.0824 0.6597 1.0000
2.750 0.6969 0.01176 0.00508 -0.0819 0.6530 1.0000
3.000 0.7232 0.01194 0.00523 -0.0816 0.6470 1.0000
3.250 0.7484 0.01210 0.00544 -0.0811 0.6393 1.0000
3.500 0.7750 0.01226 0.00556 -0.0808 0.6329 1.0000
3.750 0.7999 0.01240 0.00576 -0.0802 0.6245 1.0000
4.000 0.8261 0.01254 0.00588 -0.0798 0.6172 1.0000
4.250 0.8514 0.01265 0.00606 -0.0792 0.6084 1.0000
4.500 0.8768 0.01278 0.00622 -0.0787 0.5998 1.0000
4.750 0.9030 0.01286 0.00628 -0.0782 0.5910 1.0000
5.000 0.9274 0.01296 0.00649 -0.0775 0.5808 1.0000
5.250 0.9527 0.01305 0.00663 -0.0769 0.5710 1.0000
5.500 0.9785 0.01312 0.00668 -0.0763 0.5610 1.0000
5.750 1.0024 0.01318 0.00686 -0.0755 0.5488 1.0000
6.000 1.0265 0.01325 0.00702 -0.0747 0.5360 1.0000
6.250 1.0502 0.01330 0.00715 -0.0737 0.5215 1.0000
6.500 1.0733 0.01335 0.00723 -0.0727 0.5043 1.0000
6.750 1.0948 0.01340 0.00735 -0.0713 0.4799 1.0000
7.000 1.1146 0.01355 0.00747 -0.0697 0.4477 1.0000
7.250 1.1327 0.01387 0.00771 -0.0680 0.4052 1.0000
7.500 1.1476 0.01448 0.00811 -0.0658 0.3494 1.0000
7.750 1.1563 0.01557 0.00880 -0.0629 0.2780 1.0000
8.000 1.1633 0.01688 0.00973 -0.0600 0.2154 1.0000
8.250 1.1696 0.01825 0.01079 -0.0571 0.1601 1.0000
8.500 1.1735 0.01974 0.01195 -0.0539 0.1085 1.0000
8.750 1.1683 0.02167 0.01346 -0.0494 0.0574 1.0000
9.000 1.1628 0.02353 0.01517 -0.0448 0.0392 1.0000
9.250 1.1653 0.02497 0.01670 -0.0416 0.0342 1.0000
9.500 1.1679 0.02649 0.01828 -0.0388 0.0313 1.0000
10.000 1.1688 0.03026 0.02221 -0.0337 0.0282 1.0000
10.250 1.1746 0.03194 0.02402 -0.0319 0.0271 1.0000
10.500 1.1810 0.03368 0.02583 -0.0303 0.0257 1.0000
10.750 1.1881 0.03538 0.02759 -0.0289 0.0243 1.0000
11.000 1.1947 0.03729 0.02953 -0.0276 0.0233 1.0000
11.250 1.2061 0.03957 0.03182 -0.0259 0.0224 1.0000
11.500 1.2230 0.04147 0.03384 -0.0246 0.0220 1.0000
11.750 1.2402 0.04341 0.03593 -0.0236 0.0218 1.0000
12.000 1.2543 0.04563 0.03836 -0.0225 0.0215 1.0000
12.250 1.2670 0.04821 0.04121 -0.0214 0.0214 1.0000
12.500 1.2748 0.05117 0.04443 -0.0202 0.0213 1.0000
12.750 1.2785 0.05448 0.04801 -0.0192 0.0214 1.0000
13.000 1.2771 0.05815 0.05195 -0.0181 0.0215 1.0000
13.250 1.2723 0.06222 0.05628 -0.0174 0.0217 1.0000
13.500 1.2649 0.06679 0.06110 -0.0169 0.0219 1.0000
13.750 1.2592 0.07203 0.06658 -0.0167 0.0223 1.0000
14.000 1.2494 0.07548 0.07022 -0.0168 0.0224 1.0000
14.250 1.2371 0.07934 0.07431 -0.0174 0.0226 1.0000
14.500 1.2205 0.08425 0.07944 -0.0187 0.0227 1.0000
14.750 1.2024 0.08955 0.08498 -0.0206 0.0229 1.0000
15.000 1.1650 0.09824 0.09408 -0.0250 0.0238 1.0000
15.250 1.1183 0.11032 0.10654 -0.0322 0.0247 1.0000
15.500 1.0857 0.12136 0.11779 -0.0393 0.0252 1.0000
15.750 1.0503 0.13481 0.13140 -0.0484 0.0256 1.0000
16.000 1.0023 0.15558 0.15228 -0.0616 0.0270 1.0000
16.250 0.9891 0.16590 0.16257 -0.0669 0.0285 1.0000
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Polar data table (+)
Polar graphs
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