E222 (10.17%) (e222-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E222 (10.17%) (e222-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.89 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e222-il-1000000-n5.txt Download as CSV file: xf-e222-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E222 (10.17%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6757 0.06607 0.06422 -0.0478 1.0000 0.0066
-11.500 -0.7267 0.05077 0.04874 -0.0588 1.0000 0.0065
-11.250 -0.7558 0.04225 0.04006 -0.0662 1.0000 0.0065
-11.000 -0.7947 0.03811 0.03580 -0.0656 1.0000 0.0064
-10.750 -0.7864 0.03384 0.03125 -0.0703 0.9975 0.0065
-10.500 -0.7684 0.03053 0.02766 -0.0739 0.9950 0.0065
-10.250 -0.7492 0.02796 0.02483 -0.0760 0.9926 0.0066
-10.000 -0.7276 0.02600 0.02265 -0.0773 0.9899 0.0066
-9.750 -0.7033 0.02419 0.02063 -0.0788 0.9876 0.0067
-9.500 -0.6770 0.02258 0.01882 -0.0803 0.9859 0.0067
-9.250 -0.6484 0.02133 0.01741 -0.0818 0.9845 0.0068
-9.000 -0.6262 0.01855 0.01431 -0.0829 0.9822 0.0069
-8.750 -0.6040 0.01713 0.01272 -0.0828 0.9780 0.0071
-8.500 -0.5760 0.01615 0.01165 -0.0837 0.9754 0.0074
-8.250 -0.5459 0.01543 0.01084 -0.0848 0.9734 0.0075
-8.000 -0.5150 0.01461 0.00994 -0.0860 0.9718 0.0077
-7.750 -0.4869 0.01391 0.00916 -0.0865 0.9690 0.0078
-7.500 -0.4614 0.01327 0.00845 -0.0863 0.9639 0.0080
-7.250 -0.4313 0.01264 0.00774 -0.0872 0.9607 0.0083
-7.000 -0.3994 0.01203 0.00704 -0.0883 0.9581 0.0085
-6.750 -0.3716 0.01153 0.00649 -0.0885 0.9525 0.0088
-6.500 -0.3408 0.01101 0.00591 -0.0894 0.9476 0.0091
-6.250 -0.3085 0.01056 0.00539 -0.0905 0.9428 0.0094
-6.000 -0.2786 0.01014 0.00490 -0.0911 0.9354 0.0096
-5.750 -0.2474 0.00976 0.00445 -0.0919 0.9282 0.0098
-5.500 -0.2180 0.00943 0.00406 -0.0923 0.9186 0.0099
-5.250 -0.1892 0.00915 0.00371 -0.0926 0.9085 0.0101
-5.000 -0.1609 0.00890 0.00339 -0.0927 0.8977 0.0102
-4.750 -0.1334 0.00858 0.00298 -0.0927 0.8862 0.0105
-4.500 -0.1062 0.00829 0.00259 -0.0925 0.8739 0.0114
-4.250 -0.0790 0.00809 0.00233 -0.0924 0.8616 0.0120
-4.000 -0.0517 0.00794 0.00211 -0.0922 0.8489 0.0126
-3.750 -0.0246 0.00781 0.00192 -0.0920 0.8359 0.0134
-3.500 0.0026 0.00772 0.00175 -0.0918 0.8223 0.0142
-3.250 0.0297 0.00764 0.00160 -0.0916 0.8087 0.0151
-3.000 0.0567 0.00754 0.00147 -0.0914 0.7946 0.0198
-2.750 0.0834 0.00730 0.00130 -0.0912 0.7804 0.0545
-2.500 0.1100 0.00708 0.00118 -0.0911 0.7659 0.0956
-2.250 0.1366 0.00683 0.00107 -0.0909 0.7512 0.1507
-2.000 0.1635 0.00669 0.00100 -0.0908 0.7361 0.1904
-1.750 0.1903 0.00654 0.00094 -0.0907 0.7208 0.2367
-1.500 0.2170 0.00636 0.00089 -0.0906 0.7049 0.2963
-1.250 0.2439 0.00628 0.00087 -0.0904 0.6888 0.3360
-1.000 0.2707 0.00617 0.00085 -0.0903 0.6726 0.3907
-0.750 0.2977 0.00612 0.00085 -0.0902 0.6562 0.4284
-0.500 0.3249 0.00610 0.00086 -0.0900 0.6396 0.4587
-0.250 0.3520 0.00610 0.00087 -0.0899 0.6225 0.4875
0.000 0.3790 0.00612 0.00089 -0.0897 0.6043 0.5154
0.250 0.4059 0.00616 0.00093 -0.0895 0.5857 0.5423
0.500 0.4329 0.00619 0.00097 -0.0893 0.5673 0.5697
0.750 0.4599 0.00623 0.00102 -0.0892 0.5485 0.5979
1.000 0.4867 0.00629 0.00108 -0.0890 0.5297 0.6243
1.250 0.5136 0.00636 0.00115 -0.0888 0.5109 0.6494
1.500 0.5404 0.00644 0.00122 -0.0886 0.4909 0.6735
2.000 0.5934 0.00665 0.00140 -0.0880 0.4484 0.7218
2.250 0.6196 0.00677 0.00152 -0.0877 0.4267 0.7466
2.750 0.6715 0.00705 0.00176 -0.0869 0.3818 0.7933
3.000 0.6973 0.00720 0.00189 -0.0865 0.3592 0.8149
3.250 0.7224 0.00739 0.00204 -0.0860 0.3344 0.8362
3.500 0.7474 0.00758 0.00220 -0.0854 0.3115 0.8577
3.750 0.7718 0.00775 0.00235 -0.0847 0.2908 0.8797
4.000 0.7951 0.00796 0.00253 -0.0837 0.2667 0.9028
4.250 0.8163 0.00826 0.00273 -0.0824 0.2321 0.9280
4.500 0.8374 0.00862 0.00295 -0.0810 0.1913 0.9619
4.750 0.8651 0.00903 0.00319 -0.0813 0.1572 1.0000
5.000 0.8905 0.00934 0.00342 -0.0809 0.1376 1.0000
5.250 0.9147 0.00976 0.00371 -0.0804 0.1110 1.0000
5.500 0.9386 0.01022 0.00402 -0.0798 0.0847 1.0000
5.750 0.9624 0.01067 0.00435 -0.0792 0.0630 1.0000
6.000 0.9865 0.01109 0.00467 -0.0787 0.0460 1.0000
6.250 1.0101 0.01154 0.00503 -0.0781 0.0315 1.0000
6.500 1.0329 0.01207 0.00548 -0.0773 0.0157 1.0000
6.750 1.0558 0.01259 0.00594 -0.0765 0.0076 1.0000
7.000 1.0799 0.01297 0.00633 -0.0759 0.0061 1.0000
7.250 1.1042 0.01331 0.00671 -0.0754 0.0056 1.0000
7.500 1.1282 0.01367 0.00710 -0.0748 0.0052 1.0000
7.750 1.1516 0.01407 0.00754 -0.0741 0.0049 1.0000
8.000 1.1747 0.01449 0.00800 -0.0734 0.0046 1.0000
8.250 1.1972 0.01495 0.00849 -0.0726 0.0044 1.0000
8.500 1.2189 0.01547 0.00906 -0.0716 0.0041 1.0000
8.750 1.2397 0.01606 0.00970 -0.0705 0.0039 1.0000
9.000 1.2589 0.01678 0.01051 -0.0692 0.0037 1.0000
9.250 1.2791 0.01735 0.01115 -0.0681 0.0036 1.0000
9.500 1.2990 0.01792 0.01176 -0.0669 0.0036 1.0000
9.750 1.3182 0.01851 0.01242 -0.0656 0.0035 1.0000
10.000 1.3364 0.01914 0.01311 -0.0642 0.0034 1.0000
10.250 1.3533 0.01983 0.01387 -0.0626 0.0033 1.0000
10.500 1.3679 0.02054 0.01465 -0.0606 0.0032 1.0000
10.750 1.3802 0.02128 0.01547 -0.0583 0.0032 1.0000
11.000 1.3915 0.02208 0.01636 -0.0558 0.0031 1.0000
11.250 1.4018 0.02295 0.01731 -0.0533 0.0030 1.0000
11.500 1.4110 0.02389 0.01834 -0.0508 0.0029 1.0000
11.750 1.4205 0.02483 0.01936 -0.0485 0.0028 1.0000
12.000 1.4286 0.02588 0.02050 -0.0462 0.0028 1.0000
12.250 1.4362 0.02701 0.02170 -0.0439 0.0027 1.0000
12.500 1.4429 0.02823 0.02302 -0.0418 0.0026 1.0000
12.750 1.4486 0.02958 0.02446 -0.0397 0.0026 1.0000
13.000 1.4533 0.03108 0.02604 -0.0378 0.0025 1.0000
13.250 1.4566 0.03277 0.02783 -0.0361 0.0025 1.0000
13.500 1.4581 0.03471 0.02989 -0.0345 0.0025 1.0000
13.750 1.4582 0.03689 0.03218 -0.0331 0.0024 1.0000
14.000 1.4582 0.03924 0.03464 -0.0321 0.0024 1.0000
14.250 1.4567 0.04188 0.03739 -0.0313 0.0024 1.0000
14.500 1.4530 0.04494 0.04057 -0.0309 0.0023 1.0000
14.750 1.4481 0.04836 0.04412 -0.0310 0.0023 1.0000
15.000 1.4414 0.05221 0.04810 -0.0314 0.0023 1.0000
15.250 1.4342 0.05641 0.05242 -0.0324 0.0023 1.0000
15.500 1.4251 0.06113 0.05728 -0.0338 0.0023 1.0000
15.750 1.4140 0.06647 0.06277 -0.0358 0.0023 1.0000
16.000 1.4007 0.07250 0.06894 -0.0384 0.0023 1.0000
16.250 1.3867 0.07896 0.07554 -0.0414 0.0023 1.0000
16.500 1.3725 0.08580 0.08252 -0.0449 0.0023 1.0000
16.750 1.3565 0.09327 0.09014 -0.0488 0.0023 1.0000
17.000 1.3389 0.10132 0.09833 -0.0532 0.0023 1.0000
17.250 1.3227 0.10939 0.10654 -0.0576 0.0023 1.0000
17.500 1.3037 0.11824 0.11553 -0.0627 0.0023 1.0000
17.750 1.2869 0.12681 0.12422 -0.0676 0.0023 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E222 (10.17%) (e222-il)