EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 668 AIRFOIL (e668-il) Reynolds number: 100,000 Max Cl/Cd: 47.17 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e668-il-100000-n5.txt Download as CSV file: xf-e668-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 668 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1942 0.09818 0.09296 -0.0998 0.9449 0.0232
-10.500 -0.1923 0.09285 0.08765 -0.1035 0.9426 0.0226
-10.250 -0.2086 0.08376 0.07861 -0.1087 0.9380 0.0211
-10.000 -0.2114 0.07782 0.07269 -0.1128 0.9345 0.0210
-9.750 -0.2154 0.07043 0.06529 -0.1188 0.9312 0.0207
-9.500 -0.2218 0.06326 0.05807 -0.1260 0.9274 0.0203
-9.250 -0.2443 0.05841 0.05312 -0.1288 0.9206 0.0200
-9.000 -0.2650 0.05398 0.04850 -0.1308 0.9149 0.0198
-8.750 -0.2877 0.05185 0.04623 -0.1278 0.9081 0.0197
-8.500 -0.3059 0.04890 0.04302 -0.1254 0.9024 0.0197
-8.250 -0.3093 0.04539 0.03912 -0.1248 0.8989 0.0196
-8.000 -0.3197 0.04343 0.03688 -0.1208 0.8933 0.0196
-7.750 -0.3247 0.04124 0.03435 -0.1174 0.8885 0.0198
-7.500 -0.3171 0.03825 0.03084 -0.1160 0.8853 0.0202
-7.250 -0.2998 0.03550 0.02754 -0.1156 0.8831 0.0207
-7.000 -0.2839 0.03355 0.02522 -0.1144 0.8807 0.0214
-6.750 -0.2869 0.03315 0.02476 -0.1096 0.8750 0.0220
-6.500 -0.2689 0.03215 0.02356 -0.1086 0.8719 0.0239
-6.250 -0.2453 0.03078 0.02192 -0.1084 0.8698 0.0264
-6.000 -0.2198 0.02967 0.02067 -0.1085 0.8681 0.0288
-5.750 -0.1933 0.02845 0.01930 -0.1087 0.8667 0.0317
-5.500 -0.1924 0.02832 0.01912 -0.1043 0.8609 0.0345
-5.250 -0.1771 0.02773 0.01847 -0.1025 0.8572 0.0385
-5.000 -0.1533 0.02701 0.01767 -0.1022 0.8548 0.0452
-4.750 -0.1253 0.02625 0.01689 -0.1027 0.8530 0.0547
-4.500 -0.0950 0.02553 0.01615 -0.1036 0.8515 0.0691
-4.250 -0.0640 0.02481 0.01548 -0.1046 0.8502 0.0922
-4.000 -0.0707 0.02503 0.01576 -0.0990 0.8421 0.1050
-3.750 -0.0451 0.02451 0.01542 -0.0991 0.8394 0.1487
-3.500 -0.0162 0.02393 0.01511 -0.0999 0.8375 0.2188
-3.250 0.0146 0.02332 0.01487 -0.1010 0.8360 0.3151
-3.000 0.0460 0.02270 0.01469 -0.1021 0.8347 0.4334
-2.750 0.0409 0.02300 0.01528 -0.0966 0.8262 0.4968
-2.500 0.0610 0.02285 0.01555 -0.0946 0.8232 0.6089
-2.250 0.0827 0.02299 0.01587 -0.0922 0.8210 0.6893
-2.000 0.1108 0.02319 0.01600 -0.0914 0.8194 0.7411
-1.750 0.1067 0.02388 0.01666 -0.0859 0.8103 0.7675
-1.500 0.1305 0.02409 0.01675 -0.0846 0.8071 0.7967
-1.250 0.1564 0.02419 0.01674 -0.0835 0.8050 0.8199
-1.000 0.1607 0.02467 0.01718 -0.0793 0.7976 0.8386
-0.750 0.1777 0.02484 0.01726 -0.0770 0.7929 0.8569
-0.500 0.2012 0.02481 0.01715 -0.0755 0.7902 0.8737
-0.250 0.2283 0.02468 0.01693 -0.0746 0.7883 0.8899
0.000 0.2253 0.02517 0.01741 -0.0695 0.7782 0.9063
0.250 0.2513 0.02505 0.01722 -0.0687 0.7752 0.9222
0.500 0.2844 0.02489 0.01698 -0.0692 0.7732 0.9373
1.000 0.3401 0.02534 0.01736 -0.0705 0.7612 0.9672
1.250 0.3859 0.02525 0.01721 -0.0741 0.7592 0.9770
1.500 0.4313 0.02508 0.01697 -0.0775 0.7575 0.9857
1.750 0.4377 0.02555 0.01744 -0.0751 0.7465 1.0000
2.000 0.4704 0.02534 0.01718 -0.0760 0.7438 1.0000
2.500 0.5123 0.02559 0.01739 -0.0748 0.7302 1.0000
2.750 0.5476 0.02531 0.01709 -0.0761 0.7276 1.0000
3.000 0.5602 0.02579 0.01757 -0.0745 0.7168 1.0000
3.250 0.5966 0.02544 0.01723 -0.0758 0.7142 1.0000
3.500 0.6111 0.02593 0.01773 -0.0745 0.7033 1.0000
3.750 0.6468 0.02553 0.01734 -0.0757 0.7002 1.0000
4.250 0.6986 0.02549 0.01738 -0.0756 0.6859 1.0000
4.500 0.7176 0.02581 0.01774 -0.0747 0.6755 1.0000
4.750 0.7514 0.02530 0.01727 -0.0754 0.6711 1.0000
5.000 0.7715 0.02555 0.01759 -0.0746 0.6605 1.0000
5.250 0.8062 0.02495 0.01703 -0.0753 0.6556 1.0000
5.750 0.8559 0.02488 0.01710 -0.0746 0.6353 1.0000
6.000 0.8853 0.02455 0.01684 -0.0746 0.6255 1.0000
6.250 0.9096 0.02455 0.01691 -0.0741 0.6125 1.0000
6.500 0.9374 0.02436 0.01679 -0.0740 0.5996 1.0000
6.750 0.9678 0.02402 0.01651 -0.0741 0.5858 1.0000
7.000 0.9988 0.02368 0.01621 -0.0742 0.5703 1.0000
7.250 1.0295 0.02339 0.01594 -0.0743 0.5518 1.0000
7.750 1.0845 0.02331 0.01584 -0.0738 0.5072 1.0000
8.000 1.1089 0.02351 0.01598 -0.0732 0.4817 1.0000
8.250 1.1280 0.02399 0.01640 -0.0721 0.4556 1.0000
8.500 1.1442 0.02464 0.01700 -0.0707 0.4288 1.0000
8.750 1.1586 0.02540 0.01769 -0.0692 0.4022 1.0000
9.000 1.1708 0.02630 0.01851 -0.0674 0.3757 1.0000
9.250 1.1817 0.02731 0.01947 -0.0657 0.3499 1.0000
9.500 1.1915 0.02840 0.02049 -0.0638 0.3251 1.0000
9.750 1.2005 0.02959 0.02162 -0.0620 0.3003 1.0000
10.000 1.2087 0.03086 0.02285 -0.0602 0.2768 1.0000
10.250 1.2160 0.03222 0.02416 -0.0585 0.2537 1.0000
10.500 1.2231 0.03366 0.02555 -0.0567 0.2320 1.0000
10.750 1.2297 0.03517 0.02702 -0.0551 0.2107 1.0000
11.000 1.2353 0.03680 0.02861 -0.0535 0.1914 1.0000
11.250 1.2413 0.03847 0.03027 -0.0520 0.1729 1.0000
11.500 1.2469 0.04021 0.03201 -0.0505 0.1557 1.0000
11.750 1.2521 0.04205 0.03385 -0.0492 0.1402 1.0000
12.000 1.2567 0.04399 0.03580 -0.0479 0.1262 1.0000
12.250 1.2610 0.04602 0.03785 -0.0467 0.1141 1.0000
12.500 1.2643 0.04820 0.04005 -0.0455 0.1032 1.0000
12.750 1.2669 0.05054 0.04242 -0.0445 0.0937 1.0000
13.000 1.2710 0.05279 0.04477 -0.0436 0.0846 1.0000
13.250 1.2731 0.05531 0.04735 -0.0428 0.0774 1.0000
13.500 1.2742 0.05801 0.05011 -0.0421 0.0709 1.0000
13.750 1.2765 0.06068 0.05289 -0.0415 0.0650 1.0000
14.000 1.2763 0.06368 0.05597 -0.0411 0.0603 1.0000
14.250 1.2774 0.06664 0.05905 -0.0408 0.0558 1.0000
14.500 1.2777 0.06977 0.06230 -0.0407 0.0520 1.0000
14.750 1.2758 0.07322 0.06581 -0.0407 0.0489 1.0000
15.000 1.2770 0.07641 0.06920 -0.0407 0.0455 1.0000
15.250 1.2756 0.07998 0.07287 -0.0411 0.0429 1.0000
15.500 1.2740 0.08365 0.07663 -0.0415 0.0407 1.0000
15.750 1.2741 0.08721 0.08040 -0.0420 0.0382 1.0000
16.000 1.2721 0.09111 0.08441 -0.0429 0.0361 1.0000
16.250 1.2691 0.09513 0.08848 -0.0439 0.0346 1.0000
16.500 1.2681 0.09911 0.09271 -0.0449 0.0327 1.0000
16.750 1.2655 0.10334 0.09714 -0.0462 0.0310 1.0000
17.000 1.2620 0.10775 0.10166 -0.0479 0.0296 1.0000
17.250 1.2593 0.11196 0.10589 -0.0495 0.0285 1.0000
17.500 1.2538 0.11705 0.11127 -0.0516 0.0272 1.0000
17.750 1.2481 0.12219 0.11664 -0.0539 0.0260 1.0000
18.000 1.2425 0.12736 0.12196 -0.0566 0.0250 1.0000
18.250 1.2382 0.13228 0.12698 -0.0593 0.0241 1.0000
18.500 1.2346 0.13704 0.13178 -0.0619 0.0233 1.0000
18.750 1.2235 0.14388 0.13890 -0.0659 0.0227 1.0000
19.000 1.2116 0.15105 0.14632 -0.0704 0.0222 1.0000
19.250 1.1985 0.15876 0.15424 -0.0753 0.0218 1.0000
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Polar data table (+)
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