EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E662 AIRFOIL (e662-il) Reynolds number: 200,000 Max Cl/Cd: 71.37 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e662-il-200000.txt Download as CSV file: xf-e662-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E662 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1066 0.09996 0.09617 -0.1224 0.9489 0.0575
-10.750 -0.1155 0.09367 0.08992 -0.1343 0.9468 0.0596
-10.500 -0.1088 0.08754 0.08379 -0.1374 0.9459 0.0607
-10.250 -0.0986 0.08598 0.08223 -0.1346 0.9426 0.0618
-10.000 -0.0878 0.08380 0.08004 -0.1346 0.9400 0.0631
-9.750 -0.0796 0.08093 0.07717 -0.1361 0.9378 0.0653
-9.500 -0.0756 0.07697 0.07321 -0.1398 0.9356 0.0676
-9.250 -0.0941 0.06834 0.06457 -0.1528 0.9321 0.0713
-9.000 -0.1247 0.06741 0.06366 -0.1480 0.9246 0.0712
-8.750 -0.1619 0.06535 0.06151 -0.1464 0.9188 0.0717
-8.500 -0.1910 0.06579 0.06202 -0.1378 0.9124 0.0713
-8.250 -0.2219 0.06592 0.06218 -0.1299 0.9062 0.0709
-7.000 -0.2940 0.05634 0.05219 -0.1119 0.8868 0.0762
-6.000 -0.3059 0.04183 0.03562 -0.0973 0.8717 0.0487
-5.750 -0.3227 0.04086 0.03471 -0.0905 0.8657 0.0475
-5.500 -0.3054 0.03772 0.03126 -0.0898 0.8626 0.0457
-5.250 -0.2779 0.03487 0.02795 -0.0901 0.8606 0.0436
-5.000 -0.2459 0.03285 0.02551 -0.0908 0.8590 0.0428
-4.750 -0.2108 0.03143 0.02383 -0.0921 0.8576 0.0433
-4.500 -0.1726 0.03049 0.02272 -0.0940 0.8564 0.0454
-4.250 -0.1804 0.03073 0.02290 -0.0883 0.8490 0.0463
-4.000 -0.1536 0.03008 0.02213 -0.0882 0.8460 0.0474
-3.750 -0.1207 0.02930 0.02127 -0.0890 0.8439 0.0486
-3.500 -0.0864 0.02818 0.02021 -0.0904 0.8424 0.0518
-3.250 -0.0477 0.02760 0.01963 -0.0925 0.8411 0.0568
-3.000 -0.0533 0.02804 0.02003 -0.0874 0.8324 0.0594
-2.750 -0.0215 0.02743 0.01946 -0.0885 0.8297 0.0715
-2.500 0.0166 0.02602 0.01878 -0.0914 0.8280 0.2009
-2.250 0.0532 0.02417 0.01870 -0.0943 0.8268 0.5903
-2.000 0.0448 0.02499 0.01999 -0.0869 0.8187 0.7208
-1.750 0.0662 0.02560 0.02054 -0.0847 0.8145 0.7810
-1.500 0.0875 0.02619 0.02108 -0.0816 0.8120 0.8156
-1.250 0.0904 0.02686 0.02173 -0.0767 0.8045 0.8329
-1.000 0.0999 0.02718 0.02202 -0.0720 0.7993 0.8499
-0.750 0.1214 0.02722 0.02198 -0.0694 0.7968 0.8652
-0.500 0.1231 0.02762 0.02235 -0.0644 0.7890 0.8788
-0.250 0.1351 0.02760 0.02228 -0.0606 0.7839 0.8932
0.000 0.1564 0.02737 0.02198 -0.0581 0.7815 0.9070
0.250 0.1726 0.02695 0.02151 -0.0541 0.7798 0.9247
0.500 0.1556 0.02710 0.02169 -0.0460 0.7681 0.9432
0.750 0.1904 0.02681 0.02134 -0.0459 0.7663 0.9659
1.000 0.2360 0.02666 0.02110 -0.0491 0.7652 0.9709
1.250 0.2789 0.02644 0.02080 -0.0519 0.7643 0.9724
1.500 0.2930 0.02700 0.02134 -0.0512 0.7528 0.9761
1.750 0.3359 0.02672 0.02100 -0.0540 0.7514 0.9772
2.000 0.3787 0.02638 0.02061 -0.0567 0.7503 0.9782
2.250 0.3924 0.02687 0.02110 -0.0557 0.7394 0.9823
2.500 0.4326 0.02648 0.02067 -0.0579 0.7376 0.9835
2.750 0.4759 0.02604 0.02021 -0.0606 0.7364 0.9841
3.000 0.5207 0.02550 0.01965 -0.0634 0.7356 0.9848
3.250 0.5384 0.02604 0.02020 -0.0632 0.7244 0.9881
3.500 0.5808 0.02542 0.01959 -0.0656 0.7230 0.9889
3.750 0.6249 0.02472 0.01889 -0.0682 0.7221 0.9899
4.000 0.6694 0.02394 0.01813 -0.0708 0.7213 0.9908
4.250 0.7143 0.02305 0.01727 -0.0733 0.7207 0.9915
4.500 0.7276 0.02348 0.01774 -0.0721 0.7088 0.9975
4.750 0.7717 0.02245 0.01675 -0.0744 0.7080 0.9989
5.000 0.8182 0.02135 0.01569 -0.0771 0.7074 1.0000
5.750 0.8646 0.02049 0.01495 -0.0711 0.6833 1.0000
6.000 0.9093 0.01932 0.01383 -0.0734 0.6810 1.0000
6.250 0.9591 0.01806 0.01262 -0.0764 0.6788 1.0000
6.500 0.9762 0.01804 0.01267 -0.0751 0.6668 1.0000
6.750 1.0039 0.01773 0.01241 -0.0752 0.6559 1.0000
7.000 1.0433 0.01698 0.01170 -0.0769 0.6457 1.0000
7.250 1.0791 0.01649 0.01123 -0.0781 0.6322 1.0000
7.500 1.1073 0.01636 0.01111 -0.0784 0.6144 1.0000
7.750 1.1373 0.01625 0.01097 -0.0789 0.5948 1.0000
8.000 1.1648 0.01632 0.01098 -0.0791 0.5730 1.0000
8.250 1.1847 0.01670 0.01130 -0.0783 0.5486 1.0000
8.500 1.2024 0.01722 0.01175 -0.0772 0.5236 1.0000
8.750 1.2186 0.01786 0.01228 -0.0760 0.4984 1.0000
9.000 1.2306 0.01868 0.01305 -0.0744 0.4726 1.0000
9.250 1.2414 0.01961 0.01390 -0.0726 0.4466 1.0000
9.500 1.2511 0.02063 0.01482 -0.0708 0.4210 1.0000
9.750 1.2593 0.02176 0.01588 -0.0689 0.3950 1.0000
10.000 1.2673 0.02296 0.01701 -0.0671 0.3695 1.0000
10.250 1.2742 0.02427 0.01822 -0.0653 0.3447 1.0000
10.500 1.2807 0.02564 0.01951 -0.0635 0.3198 1.0000
10.750 1.2876 0.02705 0.02087 -0.0619 0.2963 1.0000
11.000 1.2933 0.02858 0.02231 -0.0601 0.2733 1.0000
11.250 1.2998 0.03012 0.02380 -0.0586 0.2509 1.0000
11.500 1.3049 0.03180 0.02540 -0.0570 0.2295 1.0000
11.750 1.3105 0.03351 0.02705 -0.0556 0.2090 1.0000
12.000 1.3156 0.03531 0.02880 -0.0542 0.1892 1.0000
12.250 1.3193 0.03728 0.03069 -0.0528 0.1708 1.0000
12.500 1.3236 0.03926 0.03263 -0.0515 0.1529 1.0000
12.750 1.3282 0.04128 0.03462 -0.0504 0.1359 1.0000
13.000 1.3323 0.04341 0.03670 -0.0494 0.1205 1.0000
13.250 1.3362 0.04561 0.03887 -0.0484 0.1068 1.0000
13.500 1.3403 0.04785 0.04112 -0.0476 0.0958 1.0000
13.750 1.3428 0.05031 0.04356 -0.0467 0.0865 1.0000
14.000 1.3461 0.05276 0.04603 -0.0460 0.0779 1.0000
14.250 1.3506 0.05517 0.04853 -0.0455 0.0696 1.0000
14.500 1.3509 0.05807 0.05144 -0.0449 0.0626 1.0000
14.750 1.3516 0.06100 0.05439 -0.0446 0.0551 1.0000
15.000 1.3527 0.06401 0.05750 -0.0443 0.0477 1.0000
15.250 1.3479 0.06778 0.06130 -0.0440 0.0414 1.0000
15.500 1.3412 0.07191 0.06544 -0.0440 0.0364 1.0000
15.750 1.3378 0.07575 0.06941 -0.0441 0.0319 1.0000
16.000 1.3324 0.07991 0.07360 -0.0444 0.0293 1.0000
16.250 1.3286 0.08390 0.07769 -0.0446 0.0272 1.0000
16.500 1.3285 0.08753 0.08145 -0.0452 0.0252 1.0000
16.750 1.3272 0.09131 0.08531 -0.0459 0.0237 1.0000
17.000 1.3242 0.09519 0.08919 -0.0465 0.0223 1.0000
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Polar data table (+)
Polar graphs
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