EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.42 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1211-il-1000000.txt Download as CSV file: xf-e1211-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1211 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7522 0.08761 0.08428 -0.0529 1.0000 0.0218
-15.750 -0.7581 0.08354 0.08016 -0.0548 1.0000 0.0219
-15.500 -0.7702 0.07869 0.07527 -0.0573 1.0000 0.0220
-15.250 -0.7889 0.07308 0.06961 -0.0603 1.0000 0.0222
-15.000 -0.8127 0.06710 0.06355 -0.0635 1.0000 0.0222
-14.750 -0.8488 0.05994 0.05629 -0.0675 1.0000 0.0221
-14.500 -0.9120 0.04995 0.04615 -0.0732 1.0000 0.0218
-14.250 -1.0800 0.02760 0.02325 -0.0876 1.0000 0.0210
-14.000 -1.0862 0.02544 0.02098 -0.0863 1.0000 0.0211
-13.750 -1.0829 0.02398 0.01943 -0.0847 1.0000 0.0213
-13.500 -1.0746 0.02284 0.01823 -0.0830 1.0000 0.0215
-13.250 -1.0413 0.02173 0.01704 -0.0856 0.9980 0.0219
-13.000 -1.0082 0.02027 0.01550 -0.0886 0.9951 0.0226
-12.750 -0.9718 0.01916 0.01435 -0.0916 0.9925 0.0232
-12.500 -0.9397 0.01824 0.01339 -0.0932 0.9888 0.0239
-12.250 -0.9059 0.01745 0.01255 -0.0950 0.9842 0.0248
-12.000 -0.8692 0.01656 0.01162 -0.0975 0.9801 0.0261
-11.750 -0.8442 0.01580 0.01084 -0.0973 0.9683 0.0277
-11.500 -0.8159 0.01501 0.01003 -0.0978 0.9511 0.0303
-11.250 -0.7659 0.01393 0.00898 -0.1029 0.9362 0.0380
-11.000 -0.7109 0.01293 0.00794 -0.1089 0.9034 0.0507
-10.750 -0.6841 0.01252 0.00739 -0.1088 0.8564 0.0583
-10.500 -0.6611 0.01221 0.00697 -0.1078 0.8231 0.0649
-10.250 -0.6376 0.01193 0.00660 -0.1069 0.7963 0.0705
-9.750 -0.5879 0.01144 0.00597 -0.1055 0.7537 0.0811
-9.500 -0.5620 0.01123 0.00569 -0.1049 0.7354 0.0863
-9.250 -0.5360 0.01099 0.00542 -0.1044 0.7189 0.0915
-9.000 -0.5094 0.01084 0.00519 -0.1039 0.7036 0.0960
-8.750 -0.4829 0.01065 0.00496 -0.1034 0.6880 0.1010
-8.500 -0.4556 0.01049 0.00476 -0.1030 0.6741 0.1055
-8.250 -0.4285 0.01035 0.00457 -0.1026 0.6610 0.1105
-8.000 -0.4010 0.01022 0.00440 -0.1023 0.6477 0.1150
-7.750 -0.3733 0.01009 0.00424 -0.1020 0.6355 0.1201
-7.500 -0.3456 0.01001 0.00409 -0.1016 0.6231 0.1244
-7.250 -0.3175 0.00989 0.00396 -0.1013 0.6122 0.1290
-6.750 -0.2613 0.00973 0.00372 -0.1008 0.5899 0.1367
-6.500 -0.2333 0.00969 0.00362 -0.1005 0.5788 0.1408
-6.250 -0.2045 0.00965 0.00354 -0.1003 0.5693 0.1441
-5.750 -0.1478 0.00951 0.00335 -0.0998 0.5497 0.1519
-5.500 -0.1194 0.00951 0.00329 -0.0995 0.5400 0.1553
-5.250 -0.0905 0.00949 0.00321 -0.0993 0.5314 0.1580
-5.000 -0.0623 0.00941 0.00312 -0.0991 0.5218 0.1625
-4.750 -0.0337 0.00939 0.00308 -0.0989 0.5134 0.1659
-4.500 -0.0048 0.00938 0.00303 -0.0987 0.5052 0.1686
-4.250 0.0236 0.00942 0.00299 -0.0984 0.4962 0.1704
-4.000 0.0523 0.00930 0.00287 -0.0983 0.4890 0.1745
-3.750 0.0806 0.00928 0.00283 -0.0980 0.4803 0.1776
-3.500 0.1094 0.00928 0.00279 -0.0978 0.4729 0.1805
-3.250 0.1382 0.00928 0.00276 -0.0977 0.4657 0.1830
-3.000 0.1667 0.00933 0.00274 -0.0974 0.4574 0.1848
-2.750 0.1954 0.00925 0.00265 -0.0973 0.4510 0.1884
-2.500 0.2238 0.00922 0.00261 -0.0971 0.4433 0.1918
-2.250 0.2522 0.00925 0.00260 -0.0968 0.4357 0.1949
-2.000 0.2811 0.00924 0.00258 -0.0967 0.4299 0.1976
-1.750 0.3097 0.00928 0.00257 -0.0965 0.4229 0.1998
-1.500 0.3380 0.00932 0.00256 -0.0963 0.4159 0.2019
-1.250 0.3667 0.00926 0.00252 -0.0961 0.4098 0.2068
-1.000 0.3949 0.00928 0.00252 -0.0959 0.4030 0.2102
-0.750 0.4232 0.00932 0.00254 -0.0957 0.3967 0.2135
-0.500 0.4520 0.00934 0.00254 -0.0955 0.3915 0.2163
-0.250 0.4803 0.00940 0.00256 -0.0953 0.3849 0.2185
0.000 0.5082 0.00942 0.00256 -0.0951 0.3784 0.2240
0.250 0.5369 0.00942 0.00258 -0.0949 0.3737 0.2286
0.500 0.5651 0.00946 0.00261 -0.0947 0.3682 0.2327
0.750 0.5928 0.00957 0.00266 -0.0944 0.3616 0.2356
1.000 0.6213 0.00956 0.00268 -0.0943 0.3573 0.2416
1.250 0.6496 0.00959 0.00272 -0.0941 0.3523 0.2480
1.500 0.6773 0.00967 0.00278 -0.0938 0.3469 0.2534
1.750 0.7049 0.00975 0.00284 -0.0936 0.3417 0.2602
2.000 0.7333 0.00976 0.00290 -0.0934 0.3380 0.2688
2.250 0.7612 0.00982 0.00296 -0.0932 0.3333 0.2767
2.500 0.7884 0.00989 0.00305 -0.0929 0.3280 0.2902
2.750 0.8159 0.00996 0.00314 -0.0926 0.3235 0.3047
3.000 0.8439 0.00998 0.00322 -0.0925 0.3202 0.3225
3.250 0.8715 0.01002 0.00331 -0.0922 0.3162 0.3445
3.500 0.8984 0.01009 0.00343 -0.0919 0.3117 0.3715
3.750 0.9249 0.01018 0.00357 -0.0915 0.3068 0.4046
4.000 0.9526 0.01015 0.00368 -0.0914 0.3040 0.4479
4.250 0.9798 0.01015 0.00380 -0.0911 0.3005 0.4983
4.500 1.0063 0.01017 0.00396 -0.0908 0.2967 0.5575
4.750 1.0318 0.01021 0.00414 -0.0903 0.2924 0.6279
5.000 1.0572 0.01017 0.00433 -0.0897 0.2892 0.7179
5.250 1.0798 0.00998 0.00451 -0.0884 0.2867 0.8461
5.500 1.1090 0.00990 0.00463 -0.0883 0.2833 1.0000
5.750 1.1350 0.01008 0.00477 -0.0879 0.2796 1.0000
6.000 1.1602 0.01031 0.00495 -0.0873 0.2755 1.0000
6.250 1.1860 0.01049 0.00512 -0.0868 0.2726 1.0000
6.500 1.2126 0.01062 0.00526 -0.0865 0.2704 1.0000
6.750 1.2385 0.01078 0.00541 -0.0860 0.2675 1.0000
7.000 1.2637 0.01098 0.00559 -0.0855 0.2645 1.0000
7.250 1.2879 0.01122 0.00579 -0.0847 0.2609 1.0000
7.500 1.3112 0.01149 0.00604 -0.0839 0.2572 1.0000
7.750 1.3370 0.01163 0.00619 -0.0835 0.2553 1.0000
8.000 1.3620 0.01180 0.00637 -0.0829 0.2529 1.0000
8.250 1.3860 0.01201 0.00658 -0.0822 0.2502 1.0000
8.500 1.4089 0.01225 0.00681 -0.0813 0.2473 1.0000
8.750 1.4302 0.01256 0.00708 -0.0802 0.2440 1.0000
9.000 1.4515 0.01284 0.00736 -0.0790 0.2413 1.0000
9.250 1.4745 0.01301 0.00756 -0.0781 0.2395 1.0000
9.500 1.4956 0.01320 0.00778 -0.0769 0.2372 1.0000
9.750 1.5151 0.01345 0.00803 -0.0755 0.2348 1.0000
10.000 1.5330 0.01374 0.00832 -0.0738 0.2323 1.0000
10.250 1.5493 0.01410 0.00867 -0.0719 0.2295 1.0000
10.500 1.5640 0.01452 0.00909 -0.0698 0.2265 1.0000
10.750 1.5844 0.01475 0.00936 -0.0686 0.2251 1.0000
11.000 1.6038 0.01502 0.00966 -0.0673 0.2232 1.0000
11.250 1.6214 0.01536 0.01002 -0.0658 0.2210 1.0000
11.500 1.6376 0.01576 0.01043 -0.0642 0.2188 1.0000
11.750 1.6517 0.01624 0.01092 -0.0623 0.2163 1.0000
12.000 1.6621 0.01689 0.01157 -0.0601 0.2131 1.0000
12.250 1.6770 0.01739 0.01210 -0.0585 0.2113 1.0000
12.500 1.6940 0.01782 0.01257 -0.0573 0.2096 1.0000
12.750 1.7093 0.01834 0.01313 -0.0559 0.2076 1.0000
13.000 1.7223 0.01899 0.01381 -0.0543 0.2053 1.0000
13.250 1.7330 0.01979 0.01463 -0.0527 0.2030 1.0000
13.500 1.7404 0.02083 0.01567 -0.0509 0.2003 1.0000
13.750 1.7474 0.02196 0.01683 -0.0492 0.1979 1.0000
14.000 1.7618 0.02270 0.01764 -0.0482 0.1966 1.0000
14.250 1.7748 0.02358 0.01857 -0.0473 0.1949 1.0000
14.500 1.7856 0.02462 0.01965 -0.0462 0.1930 1.0000
14.750 1.7940 0.02587 0.02094 -0.0451 0.1909 1.0000
15.000 1.7997 0.02738 0.02248 -0.0441 0.1887 1.0000
15.250 1.8013 0.02925 0.02437 -0.0429 0.1861 1.0000
15.500 1.8063 0.03093 0.02611 -0.0421 0.1842 1.0000
15.750 1.8163 0.03226 0.02751 -0.0415 0.1828 1.0000
16.000 1.8251 0.03372 0.02903 -0.0410 0.1808 1.0000
16.250 1.8296 0.03558 0.03094 -0.0404 0.1787 1.0000
16.500 1.8302 0.03785 0.03325 -0.0399 0.1761 1.0000
16.750 1.8255 0.04068 0.03610 -0.0395 0.1733 1.0000
17.000 1.8250 0.04318 0.03865 -0.0392 0.1712 1.0000
17.250 1.8321 0.04500 0.04055 -0.0391 0.1693 1.0000
17.500 1.8340 0.04740 0.04302 -0.0391 0.1670 1.0000
17.750 1.8305 0.05043 0.04609 -0.0392 0.1641 1.0000
18.000 1.8243 0.05381 0.04952 -0.0394 0.1620 1.0000
18.250 1.8157 0.05754 0.05330 -0.0398 0.1591 1.0000
18.500 1.8189 0.06003 0.05586 -0.0401 0.1572 1.0000
18.750 1.8165 0.06319 0.05909 -0.0406 0.1549 1.0000
19.000 1.8104 0.06685 0.06280 -0.0414 0.1522 1.0000
19.250 1.7994 0.07121 0.06721 -0.0423 0.1496 1.0000
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