E64 (8.45%) (e64-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 200,000 Max Cl/Cd: 88.43 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e64-il-200000.txt Download as CSV file: xf-e64-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4007 0.08933 0.08601 -0.0308 1.0000 0.0449
-7.500 -0.4165 0.08751 0.08428 -0.0294 1.0000 0.0456
-7.250 -0.4328 0.08552 0.08239 -0.0290 1.0000 0.0461
-7.000 -0.4416 0.08213 0.07905 -0.0333 1.0000 0.0466
-6.750 -0.4438 0.07766 0.07456 -0.0388 1.0000 0.0469
-6.500 -0.4429 0.07333 0.07014 -0.0424 1.0000 0.0470
-6.250 -0.4484 0.06802 0.06493 -0.0405 1.0000 0.0481
-6.000 -0.4458 0.06597 0.06292 -0.0380 1.0000 0.0490
-5.750 -0.4405 0.06354 0.06050 -0.0373 1.0000 0.0500
-5.500 -0.4217 0.05986 0.05676 -0.0406 0.9982 0.0523
-5.250 -0.3702 0.04926 0.04543 -0.0585 0.9933 0.0606
-5.000 -0.3450 0.04595 0.04224 -0.0603 0.9897 0.0625
-4.750 -0.3105 0.04264 0.03877 -0.0645 0.9862 0.0671
-4.500 -0.2718 0.03771 0.03338 -0.0706 0.9827 0.0762
-4.250 -0.2208 0.02682 0.02094 -0.0746 0.9822 0.0343
-4.000 -0.1844 0.02326 0.01684 -0.0769 0.9796 0.0320
-3.750 -0.1464 0.02154 0.01470 -0.0788 0.9764 0.0336
-3.500 -0.1076 0.01967 0.01249 -0.0808 0.9741 0.0332
-3.250 -0.0677 0.01825 0.01085 -0.0830 0.9722 0.0335
-3.000 -0.0367 0.01724 0.00975 -0.0836 0.9665 0.0345
-2.750 0.0013 0.01611 0.00857 -0.0856 0.9629 0.0377
-2.500 0.0425 0.01536 0.00782 -0.0884 0.9601 0.0521
-2.250 0.0772 0.01394 0.00723 -0.0905 0.9557 0.2462
-2.000 0.1115 0.01323 0.00722 -0.0924 0.9505 0.4301
-1.750 0.1491 0.01269 0.00724 -0.0943 0.9471 0.5935
-1.500 0.1771 0.01236 0.00722 -0.0940 0.9403 0.7029
-1.250 0.2064 0.01200 0.00713 -0.0935 0.9349 0.8100
-1.000 0.2449 0.01160 0.00687 -0.0946 0.9321 0.9539
-0.750 0.2784 0.01152 0.00664 -0.0959 0.9237 1.0000
-0.500 0.3214 0.01137 0.00636 -0.0989 0.9200 1.0000
-0.250 0.3585 0.01126 0.00615 -0.1007 0.9141 1.0000
0.000 0.3970 0.01110 0.00590 -0.1027 0.9083 1.0000
0.250 0.4409 0.01085 0.00558 -0.1056 0.9049 1.0000
0.500 0.4722 0.01075 0.00543 -0.1061 0.8961 1.0000
0.750 0.5127 0.01049 0.00513 -0.1083 0.8911 1.0000
1.000 0.5436 0.01037 0.00498 -0.1086 0.8814 1.0000
1.250 0.5831 0.01010 0.00467 -0.1105 0.8754 1.0000
1.500 0.6122 0.00999 0.00457 -0.1104 0.8635 1.0000
1.750 0.6422 0.00989 0.00445 -0.1104 0.8516 1.0000
2.000 0.6725 0.00979 0.00434 -0.1105 0.8390 1.0000
2.250 0.7021 0.00972 0.00425 -0.1104 0.8252 1.0000
2.500 0.7310 0.00967 0.00421 -0.1102 0.8098 1.0000
2.750 0.7595 0.00966 0.00417 -0.1099 0.7930 1.0000
3.000 0.7878 0.00967 0.00415 -0.1096 0.7753 1.0000
3.250 0.8134 0.00975 0.00422 -0.1088 0.7541 1.0000
3.500 0.8405 0.00983 0.00427 -0.1083 0.7327 1.0000
3.750 0.8655 0.00996 0.00438 -0.1074 0.7074 1.0000
4.000 0.8902 0.01013 0.00450 -0.1064 0.6803 1.0000
4.250 0.9144 0.01034 0.00464 -0.1054 0.6506 1.0000
4.500 0.9379 0.01061 0.00485 -0.1043 0.6185 1.0000
4.750 0.9604 0.01092 0.00507 -0.1030 0.5822 1.0000
5.000 0.9816 0.01131 0.00533 -0.1015 0.5402 1.0000
5.250 1.0014 0.01180 0.00563 -0.0998 0.4914 1.0000
5.500 1.0196 0.01240 0.00601 -0.0980 0.4350 1.0000
5.750 1.0363 0.01315 0.00645 -0.0960 0.3721 1.0000
6.000 1.0531 0.01397 0.00697 -0.0941 0.3092 1.0000
6.250 1.0701 0.01484 0.00756 -0.0924 0.2507 1.0000
6.500 1.0869 0.01581 0.00824 -0.0908 0.1931 1.0000
6.750 1.1045 0.01677 0.00896 -0.0893 0.1459 1.0000
7.000 1.1185 0.01818 0.00996 -0.0874 0.0814 1.0000
7.250 1.1285 0.02015 0.01163 -0.0844 0.0414 1.0000
7.500 1.1418 0.02161 0.01311 -0.0821 0.0347 1.0000
7.750 1.1592 0.02262 0.01422 -0.0803 0.0310 1.0000
8.000 1.1741 0.02387 0.01557 -0.0783 0.0287 1.0000
8.250 1.1862 0.02563 0.01737 -0.0760 0.0272 1.0000
8.500 1.2018 0.02781 0.01962 -0.0742 0.0262 1.0000
8.750 1.2221 0.02948 0.02144 -0.0730 0.0256 1.0000
9.000 1.2442 0.03152 0.02365 -0.0721 0.0252 1.0000
9.250 1.2667 0.03394 0.02629 -0.0713 0.0249 1.0000
9.500 1.2866 0.03650 0.02914 -0.0702 0.0246 1.0000
9.750 1.3023 0.03887 0.03184 -0.0685 0.0239 1.0000
10.000 1.3146 0.04136 0.03465 -0.0666 0.0233 1.0000
10.250 1.3223 0.04472 0.03841 -0.0641 0.0234 1.0000
10.500 1.3237 0.04845 0.04255 -0.0611 0.0237 1.0000
10.750 1.3183 0.05219 0.04666 -0.0575 0.0241 1.0000
11.000 1.3075 0.05588 0.05067 -0.0536 0.0245 1.0000
11.250 1.2932 0.05970 0.05476 -0.0500 0.0249 1.0000
11.500 1.2763 0.06381 0.05914 -0.0472 0.0253 1.0000
11.750 1.2576 0.06842 0.06397 -0.0452 0.0256 1.0000
12.000 1.1352 0.06867 0.06472 -0.0377 0.0253 1.0000
12.250 1.1083 0.07488 0.07114 -0.0382 0.0254 1.0000
12.500 1.0802 0.08145 0.07791 -0.0398 0.0255 1.0000
12.750 1.0500 0.08840 0.08505 -0.0423 0.0257 1.0000
13.000 1.0164 0.09520 0.09202 -0.0455 0.0260 1.0000
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Polar data table (+)
Polar graphs
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