E222 (10.17%) (e222-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E222 (10.17%) (e222-il) Reynolds number: 500,000 Max Cl/Cd: 101.71 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e222-il-500000.txt Download as CSV file: xf-e222-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E222 (10.17%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3580 0.08272 0.08059 -0.0375 1.0000 0.0272
-9.500 -0.3626 0.07860 0.07649 -0.0381 1.0000 0.0281
-9.250 -0.3699 0.07406 0.07198 -0.0388 1.0000 0.0287
-9.000 -0.3807 0.06895 0.06691 -0.0399 1.0000 0.0296
-8.750 -0.3941 0.06379 0.06178 -0.0408 1.0000 0.0299
-8.250 -0.5668 0.05544 0.05329 -0.0507 1.0000 0.0257
-8.000 -0.5791 0.05224 0.05000 -0.0497 1.0000 0.0259
-7.750 -0.5577 0.04808 0.04568 -0.0552 0.9969 0.0268
-6.750 -0.4615 0.02060 0.01547 -0.0708 0.9830 0.0192
-6.500 -0.4331 0.01901 0.01369 -0.0714 0.9789 0.0195
-6.250 -0.4007 0.01724 0.01165 -0.0726 0.9762 0.0191
-6.000 -0.3668 0.01585 0.01011 -0.0740 0.9741 0.0191
-5.750 -0.3317 0.01467 0.00883 -0.0758 0.9724 0.0194
-5.500 -0.2951 0.01372 0.00781 -0.0778 0.9711 0.0200
-5.250 -0.2685 0.01298 0.00701 -0.0777 0.9649 0.0206
-5.000 -0.2338 0.01229 0.00625 -0.0793 0.9621 0.0213
-4.750 -0.1971 0.01167 0.00558 -0.0812 0.9601 0.0222
-4.500 -0.1591 0.01118 0.00503 -0.0834 0.9585 0.0238
-4.250 -0.1286 0.01060 0.00436 -0.0840 0.9535 0.0254
-4.000 -0.0939 0.01011 0.00385 -0.0853 0.9498 0.0294
-3.750 -0.0577 0.00938 0.00333 -0.0872 0.9471 0.0743
-3.500 -0.0217 0.00864 0.00296 -0.0893 0.9446 0.1673
-3.250 0.0069 0.00818 0.00274 -0.0896 0.9376 0.2359
-3.000 0.0405 0.00773 0.00253 -0.0910 0.9326 0.3048
-2.750 0.0724 0.00741 0.00234 -0.0919 0.9263 0.3562
-2.500 0.1033 0.00712 0.00220 -0.0925 0.9186 0.4098
-2.250 0.1332 0.00682 0.00210 -0.0929 0.9099 0.4775
-2.000 0.1643 0.00658 0.00199 -0.0935 0.9015 0.5340
-1.750 0.1921 0.00644 0.00193 -0.0933 0.8902 0.5711
-1.500 0.2205 0.00634 0.00187 -0.0933 0.8789 0.6051
-1.250 0.2486 0.00624 0.00182 -0.0931 0.8673 0.6387
-1.000 0.2763 0.00617 0.00179 -0.0929 0.8551 0.6710
-0.750 0.3036 0.00612 0.00177 -0.0925 0.8422 0.7015
-0.500 0.3304 0.00609 0.00176 -0.0921 0.8287 0.7303
-0.250 0.3568 0.00608 0.00176 -0.0915 0.8145 0.7575
0.000 0.3829 0.00608 0.00177 -0.0909 0.8000 0.7841
0.250 0.4084 0.00609 0.00180 -0.0901 0.7851 0.8092
0.500 0.4336 0.00611 0.00183 -0.0893 0.7697 0.8329
0.750 0.4583 0.00615 0.00186 -0.0883 0.7536 0.8563
1.000 0.4820 0.00619 0.00190 -0.0872 0.7372 0.8782
1.250 0.5052 0.00623 0.00193 -0.0858 0.7202 0.9012
1.500 0.5268 0.00627 0.00196 -0.0842 0.7035 0.9247
1.750 0.5497 0.00630 0.00196 -0.0828 0.6863 0.9507
2.000 0.5821 0.00637 0.00196 -0.0836 0.6677 0.9770
2.250 0.6162 0.00646 0.00200 -0.0850 0.6471 1.0000
2.500 0.6422 0.00662 0.00206 -0.0847 0.6269 1.0000
2.750 0.6684 0.00679 0.00214 -0.0844 0.6059 1.0000
3.000 0.6943 0.00696 0.00224 -0.0840 0.5842 1.0000
3.250 0.7202 0.00715 0.00236 -0.0837 0.5620 1.0000
3.500 0.7456 0.00737 0.00248 -0.0832 0.5382 1.0000
3.750 0.7711 0.00759 0.00262 -0.0828 0.5130 1.0000
4.000 0.7964 0.00783 0.00277 -0.0823 0.4881 1.0000
4.250 0.8214 0.00810 0.00295 -0.0818 0.4622 1.0000
5.000 0.8948 0.00905 0.00358 -0.0801 0.3723 1.0000
5.250 0.9188 0.00943 0.00385 -0.0795 0.3401 1.0000
5.500 0.9419 0.00988 0.00414 -0.0787 0.3035 1.0000
5.750 0.9642 0.01042 0.00447 -0.0779 0.2608 1.0000
6.000 0.9871 0.01091 0.00481 -0.0772 0.2258 1.0000
6.250 1.0095 0.01145 0.00520 -0.0764 0.1919 1.0000
6.500 1.0314 0.01204 0.00562 -0.0756 0.1569 1.0000
6.750 1.0529 0.01267 0.00607 -0.0747 0.1242 1.0000
7.000 1.0743 0.01329 0.00655 -0.0737 0.0970 1.0000
7.250 1.0958 0.01389 0.00706 -0.0728 0.0749 1.0000
7.500 1.1154 0.01468 0.00767 -0.0717 0.0484 1.0000
7.750 1.1312 0.01585 0.00863 -0.0698 0.0196 1.0000
8.000 1.1499 0.01671 0.00950 -0.0683 0.0151 1.0000
8.250 1.1706 0.01733 0.01019 -0.0671 0.0136 1.0000
8.500 1.1899 0.01805 0.01096 -0.0658 0.0123 1.0000
8.750 1.2057 0.01905 0.01206 -0.0640 0.0114 1.0000
9.000 1.2205 0.02006 0.01318 -0.0620 0.0110 1.0000
9.250 1.2362 0.02093 0.01414 -0.0602 0.0107 1.0000
9.500 1.2493 0.02188 0.01518 -0.0579 0.0104 1.0000
9.750 1.2603 0.02285 0.01624 -0.0553 0.0101 1.0000
10.000 1.2698 0.02391 0.01740 -0.0527 0.0098 1.0000
10.250 1.2782 0.02509 0.01868 -0.0499 0.0096 1.0000
10.500 1.2862 0.02633 0.02004 -0.0473 0.0094 1.0000
10.750 1.2932 0.02769 0.02150 -0.0448 0.0092 1.0000
11.000 1.2997 0.02915 0.02307 -0.0424 0.0091 1.0000
11.250 1.3052 0.03078 0.02479 -0.0401 0.0089 1.0000
11.500 1.3103 0.03255 0.02669 -0.0379 0.0088 1.0000
11.750 1.3148 0.03447 0.02874 -0.0359 0.0087 1.0000
12.000 1.3182 0.03660 0.03100 -0.0340 0.0086 1.0000
12.250 1.3210 0.03888 0.03344 -0.0323 0.0086 1.0000
12.500 1.3223 0.04142 0.03615 -0.0308 0.0086 1.0000
12.750 1.3221 0.04418 0.03909 -0.0294 0.0086 1.0000
13.000 1.3202 0.04716 0.04226 -0.0283 0.0087 1.0000
13.250 1.3158 0.05051 0.04581 -0.0276 0.0087 1.0000
13.500 1.3100 0.05409 0.04959 -0.0272 0.0086 1.0000
13.750 1.3001 0.05845 0.05419 -0.0273 0.0087 1.0000
14.000 1.2920 0.06258 0.05848 -0.0280 0.0086 1.0000
14.250 1.2790 0.06777 0.06389 -0.0293 0.0087 1.0000
14.500 1.2678 0.07284 0.06912 -0.0311 0.0086 1.0000
14.750 1.2490 0.07971 0.07625 -0.0340 0.0088 1.0000
15.000 1.2303 0.08696 0.08372 -0.0376 0.0089 1.0000
15.250 1.2009 0.09702 0.09407 -0.0435 0.0091 1.0000
15.500 1.1667 0.10914 0.10647 -0.0510 0.0094 1.0000
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Polar data table (+)
Polar graphs
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