E212 (10.55%) (e212-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 200,000 Max Cl/Cd: 75.47 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e212-il-200000-n5.txt Download as CSV file: xf-e212-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E212 (10.55%)
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5504 0.07506 0.07130 -0.0483 1.0000 0.0144
-10.250 -0.5748 0.06689 0.06310 -0.0529 1.0000 0.0143
-10.000 -0.5970 0.06009 0.05626 -0.0569 1.0000 0.0142
-9.750 -0.6233 0.05428 0.05038 -0.0601 1.0000 0.0141
-9.500 -0.6488 0.05061 0.04667 -0.0605 1.0000 0.0140
-9.250 -0.6662 0.04613 0.04199 -0.0629 1.0000 0.0140
-9.000 -0.6741 0.04229 0.03788 -0.0636 1.0000 0.0140
-8.750 -0.6743 0.03866 0.03391 -0.0640 1.0000 0.0140
-8.500 -0.6615 0.03485 0.02964 -0.0660 0.9988 0.0140
-8.250 -0.6347 0.03136 0.02564 -0.0695 0.9960 0.0141
-8.000 -0.6061 0.02872 0.02258 -0.0720 0.9935 0.0142
-7.750 -0.5772 0.02663 0.02013 -0.0739 0.9908 0.0144
-7.500 -0.5476 0.02457 0.01783 -0.0757 0.9883 0.0147
-7.250 -0.5164 0.02300 0.01610 -0.0775 0.9862 0.0150
-7.000 -0.4848 0.02170 0.01468 -0.0792 0.9840 0.0154
-6.750 -0.4554 0.02060 0.01346 -0.0803 0.9805 0.0159
-6.500 -0.4237 0.01962 0.01236 -0.0817 0.9776 0.0166
-6.250 -0.3901 0.01880 0.01141 -0.0835 0.9751 0.0180
-6.000 -0.3553 0.01795 0.01045 -0.0855 0.9731 0.0190
-5.750 -0.3266 0.01713 0.00955 -0.0862 0.9684 0.0200
-5.500 -0.2933 0.01646 0.00876 -0.0877 0.9650 0.0215
-5.250 -0.2579 0.01587 0.00804 -0.0895 0.9623 0.0236
-5.000 -0.2255 0.01524 0.00739 -0.0908 0.9586 0.0279
-4.750 -0.1942 0.01457 0.00678 -0.0919 0.9540 0.0454
-4.500 -0.1595 0.01390 0.00629 -0.0937 0.9508 0.0866
-4.250 -0.1233 0.01337 0.00592 -0.0959 0.9484 0.1295
-4.000 -0.0944 0.01295 0.00565 -0.0964 0.9424 0.1703
-3.750 -0.0606 0.01252 0.00539 -0.0979 0.9383 0.2208
-3.500 -0.0244 0.01216 0.00515 -0.0998 0.9354 0.2635
-3.250 0.0060 0.01190 0.00494 -0.1004 0.9295 0.2965
-3.000 0.0392 0.01163 0.00474 -0.1015 0.9244 0.3287
-2.750 0.0755 0.01136 0.00451 -0.1032 0.9211 0.3598
-2.500 0.1059 0.01116 0.00435 -0.1037 0.9142 0.3872
-2.250 0.1403 0.01094 0.00418 -0.1049 0.9089 0.4159
-2.000 0.1787 0.01071 0.00400 -0.1070 0.9051 0.4451
-1.750 0.2083 0.01056 0.00390 -0.1072 0.8959 0.4709
-1.500 0.2467 0.01034 0.00374 -0.1093 0.8908 0.4981
-1.250 0.2776 0.01021 0.00365 -0.1097 0.8809 0.5227
-1.000 0.3133 0.01005 0.00354 -0.1112 0.8730 0.5480
-0.750 0.3475 0.00991 0.00344 -0.1123 0.8631 0.5721
-0.500 0.3803 0.00980 0.00338 -0.1130 0.8519 0.5958
-0.250 0.4135 0.00970 0.00332 -0.1139 0.8399 0.6190
0.000 0.4460 0.00962 0.00327 -0.1146 0.8265 0.6422
0.250 0.4772 0.00958 0.00325 -0.1150 0.8115 0.6645
0.500 0.5071 0.00955 0.00324 -0.1151 0.7952 0.6867
0.750 0.5360 0.00956 0.00326 -0.1150 0.7778 0.7087
1.000 0.5637 0.00959 0.00330 -0.1147 0.7595 0.7298
1.250 0.5907 0.00964 0.00334 -0.1142 0.7408 0.7512
1.500 0.6164 0.00971 0.00340 -0.1134 0.7211 0.7722
1.750 0.6412 0.00979 0.00348 -0.1124 0.7007 0.7935
2.000 0.6656 0.00990 0.00356 -0.1114 0.6799 0.8151
2.250 0.6883 0.01000 0.00365 -0.1100 0.6582 0.8371
2.500 0.7106 0.01012 0.00374 -0.1085 0.6361 0.8610
2.750 0.7314 0.01023 0.00383 -0.1067 0.6133 0.8873
3.000 0.7516 0.01033 0.00390 -0.1048 0.5904 0.9203
3.250 0.7781 0.01042 0.00394 -0.1043 0.5653 1.0000
3.500 0.8040 0.01070 0.00411 -0.1040 0.5399 1.0000
3.750 0.8293 0.01100 0.00432 -0.1035 0.5135 1.0000
4.000 0.8543 0.01132 0.00454 -0.1030 0.4864 1.0000
4.250 0.8787 0.01166 0.00478 -0.1024 0.4586 1.0000
4.500 0.9028 0.01203 0.00506 -0.1017 0.4303 1.0000
4.750 0.9265 0.01242 0.00535 -0.1010 0.4019 1.0000
5.000 0.9500 0.01284 0.00567 -0.1003 0.3742 1.0000
5.500 0.9958 0.01376 0.00641 -0.0986 0.3151 1.0000
5.750 1.0180 0.01429 0.00682 -0.0978 0.2834 1.0000
6.000 1.0398 0.01485 0.00726 -0.0968 0.2515 1.0000
6.250 1.0604 0.01552 0.00776 -0.0958 0.2145 1.0000
6.500 1.0804 0.01627 0.00832 -0.0947 0.1761 1.0000
6.750 1.1006 0.01701 0.00890 -0.0936 0.1443 1.0000
7.000 1.1212 0.01772 0.00950 -0.0926 0.1197 1.0000
7.250 1.1411 0.01847 0.01016 -0.0915 0.0965 1.0000
7.500 1.1601 0.01931 0.01088 -0.0903 0.0740 1.0000
7.750 1.1789 0.02014 0.01163 -0.0890 0.0546 1.0000
8.000 1.1963 0.02109 0.01249 -0.0875 0.0369 1.0000
8.250 1.2127 0.02211 0.01346 -0.0859 0.0254 1.0000
8.500 1.2291 0.02310 0.01446 -0.0842 0.0200 1.0000
8.750 1.2452 0.02401 0.01548 -0.0824 0.0176 1.0000
9.250 1.2722 0.02602 0.01768 -0.0782 0.0153 1.0000
9.500 1.2846 0.02706 0.01884 -0.0760 0.0146 1.0000
9.750 1.2959 0.02816 0.02004 -0.0738 0.0138 1.0000
10.000 1.3057 0.02936 0.02135 -0.0715 0.0130 1.0000
10.250 1.3115 0.03086 0.02296 -0.0689 0.0125 1.0000
10.500 1.3196 0.03222 0.02445 -0.0666 0.0121 1.0000
10.750 1.3261 0.03374 0.02611 -0.0643 0.0118 1.0000
11.000 1.3312 0.03541 0.02793 -0.0621 0.0115 1.0000
11.250 1.3355 0.03723 0.02989 -0.0600 0.0113 1.0000
11.500 1.3389 0.03921 0.03201 -0.0581 0.0111 1.0000
11.750 1.3417 0.04133 0.03428 -0.0564 0.0109 1.0000
12.000 1.3439 0.04362 0.03671 -0.0549 0.0107 1.0000
12.250 1.3453 0.04609 0.03933 -0.0536 0.0106 1.0000
12.500 1.3460 0.04874 0.04215 -0.0526 0.0104 1.0000
12.750 1.3459 0.05160 0.04515 -0.0518 0.0103 1.0000
13.000 1.3450 0.05467 0.04839 -0.0513 0.0102 1.0000
13.250 1.3432 0.05798 0.05186 -0.0511 0.0101 1.0000
13.500 1.3405 0.06155 0.05559 -0.0511 0.0100 1.0000
13.750 1.3365 0.06540 0.05961 -0.0515 0.0099 1.0000
14.000 1.3314 0.06958 0.06397 -0.0523 0.0098 1.0000
14.250 1.3252 0.07410 0.06866 -0.0534 0.0098 1.0000
14.500 1.3178 0.07897 0.07372 -0.0549 0.0097 1.0000
14.750 1.3093 0.08425 0.07919 -0.0569 0.0097 1.0000
15.000 1.2997 0.08996 0.08509 -0.0593 0.0097 1.0000
15.250 1.2888 0.09614 0.09147 -0.0623 0.0096 1.0000
15.500 1.2768 0.10281 0.09834 -0.0658 0.0096 1.0000
15.750 1.2637 0.11001 0.10574 -0.0699 0.0096 1.0000
16.000 1.2496 0.11777 0.11371 -0.0745 0.0096 1.0000
16.250 1.2337 0.12631 0.12247 -0.0799 0.0097 1.0000
16.500 1.2158 0.13586 0.13224 -0.0862 0.0098 1.0000
16.750 1.1934 0.14728 0.14389 -0.0938 0.0099 1.0000
17.000 1.1588 0.16346 0.16036 -0.1047 0.0101 1.0000
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Polar data table (+)
Polar graphs
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