EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E662 AIRFOIL (e662-il) Reynolds number: 200,000 Max Cl/Cd: 66.87 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e662-il-200000-n5.txt Download as CSV file: xf-e662-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1008 0.08675 0.08228 -0.1385 0.8878 0.0196
-11.500 -0.0978 0.08293 0.07845 -0.1407 0.8853 0.0194
-11.250 -0.1036 0.07766 0.07320 -0.1432 0.8822 0.0194
-11.000 -0.1136 0.07142 0.06698 -0.1464 0.8791 0.0193
-10.750 -0.1235 0.06507 0.06064 -0.1502 0.8761 0.0190
-10.500 -0.1670 0.05212 0.04750 -0.1596 0.8715 0.0186
-10.250 -0.1931 0.04750 0.04274 -0.1605 0.8674 0.0184
-10.000 -0.2171 0.04389 0.03895 -0.1593 0.8636 0.0184
-9.750 -0.2396 0.04086 0.03570 -0.1564 0.8601 0.0184
-9.500 -0.2575 0.03844 0.03302 -0.1528 0.8572 0.0184
-9.250 -0.2684 0.03577 0.03001 -0.1496 0.8543 0.0186
-9.000 -0.2721 0.03353 0.02743 -0.1466 0.8515 0.0188
-8.750 -0.2704 0.03146 0.02495 -0.1439 0.8491 0.0193
-8.500 -0.2629 0.02967 0.02280 -0.1419 0.8470 0.0199
-8.250 -0.2482 0.02832 0.02133 -0.1408 0.8453 0.0204
-8.000 -0.2312 0.02709 0.01991 -0.1398 0.8435 0.0209
-7.750 -0.2121 0.02581 0.01839 -0.1391 0.8420 0.0213
-7.500 -0.1911 0.02465 0.01703 -0.1385 0.8408 0.0217
-7.250 -0.1720 0.02369 0.01589 -0.1374 0.8393 0.0223
-7.000 -0.1537 0.02288 0.01495 -0.1361 0.8374 0.0228
-6.750 -0.1342 0.02211 0.01407 -0.1349 0.8353 0.0234
-6.500 -0.1133 0.02151 0.01334 -0.1340 0.8333 0.0244
-6.250 -0.0921 0.02087 0.01260 -0.1331 0.8317 0.0253
-6.000 -0.0708 0.02022 0.01194 -0.1324 0.8301 0.0263
-5.750 -0.0482 0.01967 0.01136 -0.1318 0.8285 0.0272
-5.500 -0.0245 0.01916 0.01080 -0.1314 0.8271 0.0281
-5.250 -0.0001 0.01870 0.01027 -0.1312 0.8259 0.0294
-5.000 0.0211 0.01838 0.00988 -0.1303 0.8242 0.0307
-4.750 0.0365 0.01818 0.00968 -0.1283 0.8213 0.0321
-4.500 0.0557 0.01797 0.00948 -0.1271 0.8188 0.0351
-4.000 0.1016 0.01744 0.00891 -0.1260 0.8148 0.0461
-3.750 0.1269 0.01707 0.00861 -0.1259 0.8132 0.0639
-3.500 0.1533 0.01672 0.00837 -0.1261 0.8118 0.0970
-3.250 0.1806 0.01633 0.00816 -0.1265 0.8105 0.1485
-3.000 0.1987 0.01603 0.00819 -0.1254 0.8077 0.2225
-2.750 0.2135 0.01558 0.00828 -0.1239 0.8040 0.3483
-2.500 0.2323 0.01475 0.00838 -0.1230 0.8013 0.5677
-2.250 0.2456 0.01505 0.00916 -0.1188 0.7990 0.6977
-2.000 0.2740 0.01524 0.00927 -0.1187 0.7973 0.7370
-1.750 0.3029 0.01545 0.00939 -0.1186 0.7959 0.7607
-1.500 0.3321 0.01565 0.00950 -0.1185 0.7946 0.7768
-1.250 0.3376 0.01617 0.01003 -0.1144 0.7883 0.7879
-1.000 0.3577 0.01642 0.01025 -0.1126 0.7852 0.7978
-0.750 0.3807 0.01660 0.01040 -0.1111 0.7830 0.8093
-0.500 0.4043 0.01677 0.01052 -0.1096 0.7812 0.8224
-0.250 0.4335 0.01682 0.01050 -0.1095 0.7798 0.8333
0.000 0.4288 0.01730 0.01105 -0.1032 0.7721 0.8394
0.250 0.4555 0.01727 0.01097 -0.1031 0.7692 0.8440
0.500 0.4897 0.01714 0.01077 -0.1047 0.7672 0.8475
0.750 0.5216 0.01697 0.01055 -0.1054 0.7656 0.8494
1.250 0.5509 0.01723 0.01082 -0.1008 0.7549 0.8553
1.500 0.5831 0.01707 0.01063 -0.1018 0.7526 0.8573
1.750 0.6191 0.01684 0.01037 -0.1035 0.7508 0.8591
2.250 0.6524 0.01699 0.01054 -0.0999 0.7392 0.8641
2.500 0.6864 0.01671 0.01026 -0.1011 0.7368 0.8653
3.000 0.7152 0.01677 0.01037 -0.0964 0.7241 0.8700
3.250 0.7514 0.01643 0.01003 -0.0980 0.7215 0.8714
3.500 0.7533 0.01687 0.01053 -0.0938 0.7111 0.8748
3.750 0.7881 0.01654 0.01020 -0.0951 0.7076 0.8759
4.000 0.7943 0.01695 0.01067 -0.0917 0.6971 0.8783
4.250 0.8279 0.01655 0.01027 -0.0926 0.6930 0.8796
4.500 0.8377 0.01688 0.01067 -0.0898 0.6818 0.8820
4.750 0.8611 0.01685 0.01067 -0.0892 0.6731 0.8836
5.000 0.8935 0.01651 0.01035 -0.0900 0.6654 0.8847
5.250 0.9165 0.01654 0.01041 -0.0894 0.6544 0.8865
5.500 0.9462 0.01634 0.01022 -0.0898 0.6433 0.8881
5.750 0.9782 0.01609 0.00996 -0.0906 0.6305 0.8896
6.000 1.0089 0.01595 0.00979 -0.0912 0.6153 0.8910
6.250 1.0363 0.01590 0.00971 -0.0912 0.5973 0.8923
6.500 1.0612 0.01594 0.00968 -0.0908 0.5771 0.8936
6.750 1.0813 0.01617 0.00985 -0.0896 0.5559 0.8953
7.000 1.0983 0.01653 0.01014 -0.0881 0.5328 0.8973
7.250 1.1132 0.01701 0.01054 -0.0862 0.5104 0.8995
7.500 1.1261 0.01759 0.01104 -0.0842 0.4873 0.9022
7.750 1.1381 0.01826 0.01164 -0.0822 0.4644 0.9050
8.000 1.1480 0.01898 0.01229 -0.0798 0.4417 0.9074
8.250 1.1569 0.01977 0.01303 -0.0774 0.4191 0.9100
8.500 1.1657 0.02062 0.01382 -0.0751 0.3963 0.9128
8.750 1.1747 0.02154 0.01468 -0.0729 0.3740 0.9157
9.000 1.1844 0.02250 0.01558 -0.0710 0.3522 0.9187
9.250 1.1919 0.02353 0.01654 -0.0688 0.3305 0.9217
9.500 1.2003 0.02452 0.01751 -0.0667 0.3093 0.9253
9.750 1.2081 0.02561 0.01855 -0.0647 0.2886 0.9295
10.250 1.2240 0.02787 0.02073 -0.0610 0.2475 0.9391
10.500 1.2315 0.02912 0.02193 -0.0592 0.2282 0.9452
10.750 1.2404 0.03033 0.02313 -0.0577 0.2092 0.9534
11.000 1.2482 0.03153 0.02432 -0.0562 0.1918 0.9748
11.250 1.2579 0.03287 0.02564 -0.0552 0.1752 1.0000
11.500 1.2678 0.03434 0.02709 -0.0542 0.1597 1.0000
11.750 1.2776 0.03586 0.02859 -0.0533 0.1451 1.0000
12.000 1.2872 0.03742 0.03014 -0.0525 0.1320 1.0000
12.250 1.2962 0.03906 0.03178 -0.0516 0.1191 1.0000
12.500 1.3041 0.04082 0.03354 -0.0507 0.1061 1.0000
12.750 1.3114 0.04267 0.03536 -0.0499 0.0935 1.0000
13.000 1.3180 0.04462 0.03729 -0.0491 0.0815 1.0000
13.250 1.3242 0.04665 0.03930 -0.0484 0.0703 1.0000
13.500 1.3303 0.04874 0.04139 -0.0477 0.0617 1.0000
13.750 1.3361 0.05089 0.04356 -0.0471 0.0546 1.0000
14.000 1.3433 0.05297 0.04571 -0.0466 0.0489 1.0000
14.250 1.3478 0.05536 0.04815 -0.0462 0.0436 1.0000
14.500 1.3535 0.05767 0.05054 -0.0458 0.0385 1.0000
14.750 1.3572 0.06025 0.05317 -0.0455 0.0337 1.0000
15.000 1.3600 0.06300 0.05597 -0.0453 0.0293 1.0000
15.250 1.3627 0.06581 0.05889 -0.0452 0.0257 1.0000
15.500 1.3631 0.06898 0.06212 -0.0452 0.0227 1.0000
15.750 1.3639 0.07219 0.06545 -0.0453 0.0200 1.0000
16.000 1.3625 0.07574 0.06909 -0.0455 0.0179 1.0000
16.250 1.3604 0.07948 0.07294 -0.0460 0.0164 1.0000
16.500 1.3584 0.08331 0.07691 -0.0466 0.0150 1.0000
16.750 1.3546 0.08747 0.08120 -0.0474 0.0140 1.0000
17.000 1.3499 0.09187 0.08572 -0.0485 0.0132 1.0000
17.250 1.3465 0.09615 0.09015 -0.0496 0.0125 1.0000
17.500 1.3419 0.10070 0.09485 -0.0510 0.0119 1.0000
17.750 1.3371 0.10536 0.09964 -0.0527 0.0113 1.0000
18.000 1.3309 0.11034 0.10475 -0.0546 0.0110 1.0000
18.250 1.3234 0.11562 0.11016 -0.0568 0.0106 1.0000
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Polar data table (+)
Polar graphs
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