E221 (9.39%) (e221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E221 (9.39%) (e221-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.14 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e221-il-1000000-n5.txt Download as CSV file: xf-e221-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E221 (9.39%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5669 0.09883 0.09724 0.0039 1.0000 0.0036
-10.000 -0.5722 0.09311 0.09154 0.0011 1.0000 0.0036
-9.000 -0.7749 0.03227 0.02980 -0.0237 1.0000 0.0033
-8.750 -0.7749 0.02721 0.02423 -0.0217 1.0000 0.0035
-8.500 -0.7647 0.02398 0.02061 -0.0200 1.0000 0.0035
-8.250 -0.7482 0.02196 0.01831 -0.0187 1.0000 0.0036
-8.000 -0.7229 0.02011 0.01619 -0.0191 0.9752 0.0037
-7.750 -0.6972 0.01864 0.01442 -0.0192 0.9268 0.0038
-7.500 -0.6789 0.01772 0.01319 -0.0174 0.8841 0.0039
-7.250 -0.6581 0.01679 0.01200 -0.0161 0.8556 0.0040
-7.000 -0.6360 0.01588 0.01085 -0.0151 0.8330 0.0040
-6.750 -0.6122 0.01525 0.01004 -0.0144 0.8134 0.0041
-6.500 -0.5884 0.01451 0.00911 -0.0136 0.7965 0.0041
-6.250 -0.5639 0.01390 0.00835 -0.0130 0.7806 0.0042
-6.000 -0.5408 0.01292 0.00716 -0.0121 0.7665 0.0043
-5.750 -0.5166 0.01221 0.00632 -0.0115 0.7531 0.0046
-5.250 -0.4654 0.01136 0.00528 -0.0105 0.7278 0.0050
-5.000 -0.4396 0.01095 0.00478 -0.0101 0.7164 0.0052
-4.750 -0.4136 0.01057 0.00430 -0.0097 0.7056 0.0054
-4.500 -0.3873 0.01024 0.00388 -0.0093 0.6947 0.0057
-4.250 -0.3608 0.00995 0.00351 -0.0089 0.6840 0.0060
-4.000 -0.3341 0.00969 0.00319 -0.0086 0.6736 0.0063
-3.750 -0.3072 0.00948 0.00291 -0.0083 0.6636 0.0066
-3.500 -0.2804 0.00923 0.00257 -0.0080 0.6533 0.0070
-3.250 -0.2534 0.00901 0.00229 -0.0077 0.6434 0.0078
-3.000 -0.2263 0.00884 0.00208 -0.0075 0.6338 0.0087
-2.750 -0.1990 0.00869 0.00187 -0.0073 0.6238 0.0108
-2.500 -0.1720 0.00848 0.00168 -0.0071 0.6140 0.0205
-2.250 -0.1452 0.00826 0.00152 -0.0068 0.6046 0.0418
-2.000 -0.1184 0.00807 0.00139 -0.0066 0.5945 0.0669
-1.750 -0.0916 0.00786 0.00126 -0.0064 0.5845 0.1013
-1.500 -0.0651 0.00761 0.00116 -0.0062 0.5747 0.1520
-1.250 -0.0391 0.00732 0.00106 -0.0059 0.5645 0.2184
-1.000 -0.0125 0.00711 0.00099 -0.0056 0.5538 0.2747
-0.750 0.0137 0.00687 0.00093 -0.0054 0.5436 0.3426
-0.500 0.0400 0.00667 0.00088 -0.0051 0.5329 0.4035
-0.250 0.0661 0.00647 0.00084 -0.0048 0.5221 0.4691
0.000 0.0920 0.00626 0.00081 -0.0044 0.5113 0.5393
0.250 0.1171 0.00602 0.00079 -0.0039 0.5005 0.6225
0.500 0.1411 0.00576 0.00078 -0.0030 0.4898 0.7124
0.750 0.1639 0.00548 0.00079 -0.0018 0.4789 0.8050
1.000 0.1892 0.00527 0.00086 -0.0010 0.4674 0.8998
1.250 0.2320 0.00538 0.00099 -0.0040 0.4537 0.9468
1.500 0.2647 0.00550 0.00105 -0.0050 0.4410 0.9609
2.000 0.3283 0.00575 0.00118 -0.0066 0.4143 0.9753
2.250 0.3625 0.00587 0.00125 -0.0080 0.4007 0.9796
2.500 0.3925 0.00601 0.00133 -0.0084 0.3870 0.9844
2.750 0.4311 0.00614 0.00139 -0.0108 0.3717 0.9865
3.000 0.4681 0.00627 0.00146 -0.0129 0.3553 0.9891
3.250 0.5040 0.00642 0.00155 -0.0147 0.3388 0.9921
3.500 0.5380 0.00661 0.00165 -0.0162 0.3195 0.9947
3.750 0.5745 0.00674 0.00173 -0.0182 0.3012 0.9964
4.000 0.6089 0.00692 0.00183 -0.0198 0.2808 0.9981
4.250 0.6418 0.00712 0.00195 -0.0211 0.2578 0.9995
4.500 0.6694 0.00751 0.00213 -0.0213 0.2148 1.0000
4.750 0.6935 0.00785 0.00234 -0.0208 0.1840 1.0000
5.000 0.7177 0.00816 0.00254 -0.0202 0.1594 1.0000
5.250 0.7418 0.00847 0.00275 -0.0196 0.1387 1.0000
5.500 0.7660 0.00875 0.00297 -0.0190 0.1208 1.0000
5.750 0.7896 0.00910 0.00323 -0.0184 0.1008 1.0000
6.000 0.8131 0.00945 0.00350 -0.0177 0.0821 1.0000
6.250 0.8359 0.00987 0.00382 -0.0170 0.0623 1.0000
6.500 0.8588 0.01028 0.00415 -0.0162 0.0459 1.0000
6.750 0.8814 0.01069 0.00449 -0.0154 0.0333 1.0000
7.000 0.9029 0.01123 0.00494 -0.0145 0.0172 1.0000
7.250 0.9253 0.01163 0.00533 -0.0136 0.0122 1.0000
7.500 0.9481 0.01196 0.00568 -0.0128 0.0110 1.0000
7.750 0.9707 0.01231 0.00605 -0.0119 0.0102 1.0000
8.000 0.9928 0.01269 0.00647 -0.0110 0.0095 1.0000
8.250 1.0145 0.01310 0.00694 -0.0101 0.0089 1.0000
8.500 1.0359 0.01354 0.00742 -0.0090 0.0085 1.0000
8.750 1.0575 0.01392 0.00785 -0.0081 0.0083 1.0000
9.000 1.0785 0.01434 0.00832 -0.0071 0.0081 1.0000
9.250 1.0991 0.01479 0.00882 -0.0060 0.0078 1.0000
9.500 1.1192 0.01528 0.00938 -0.0049 0.0075 1.0000
9.750 1.1387 0.01579 0.00995 -0.0037 0.0073 1.0000
10.000 1.1577 0.01634 0.01056 -0.0024 0.0071 1.0000
10.250 1.1761 0.01692 0.01120 -0.0011 0.0069 1.0000
10.500 1.1936 0.01754 0.01188 0.0002 0.0067 1.0000
10.750 1.2103 0.01820 0.01261 0.0017 0.0065 1.0000
11.000 1.2258 0.01892 0.01341 0.0033 0.0063 1.0000
11.250 1.2388 0.01980 0.01436 0.0051 0.0061 1.0000
11.500 1.2448 0.02111 0.01579 0.0077 0.0057 1.0000
11.750 1.2578 0.02181 0.01656 0.0095 0.0057 1.0000
12.000 1.2630 0.02269 0.01753 0.0124 0.0056 1.0000
12.250 1.2690 0.02359 0.01851 0.0148 0.0056 1.0000
12.500 1.2760 0.02460 0.01959 0.0167 0.0055 1.0000
12.750 1.2826 0.02578 0.02087 0.0182 0.0054 1.0000
13.000 1.2890 0.02712 0.02230 0.0193 0.0052 1.0000
13.250 1.2927 0.02884 0.02412 0.0202 0.0052 1.0000
13.500 1.2981 0.03056 0.02594 0.0207 0.0050 1.0000
13.750 1.3047 0.03227 0.02772 0.0209 0.0049 1.0000
14.000 1.3067 0.03456 0.03012 0.0209 0.0048 1.0000
14.250 1.3071 0.03716 0.03282 0.0207 0.0047 1.0000
14.500 1.3068 0.03994 0.03571 0.0202 0.0046 1.0000
14.750 1.3044 0.04309 0.03897 0.0195 0.0045 1.0000
15.000 1.3061 0.04583 0.04179 0.0187 0.0044 1.0000
15.250 1.3000 0.04966 0.04573 0.0175 0.0044 1.0000
15.500 1.2932 0.05367 0.04985 0.0161 0.0044 1.0000
15.750 1.2915 0.05714 0.05340 0.0148 0.0043 1.0000
16.000 1.2815 0.06182 0.05820 0.0129 0.0042 1.0000
16.250 1.2699 0.06698 0.06348 0.0107 0.0042 1.0000
16.500 1.2626 0.07172 0.06830 0.0085 0.0041 1.0000
16.750 1.2461 0.07797 0.07469 0.0056 0.0041 1.0000
17.000 1.2369 0.08329 0.08009 0.0031 0.0041 1.0000
17.250 1.2187 0.09024 0.08717 -0.0003 0.0041 1.0000
17.500 1.2034 0.09692 0.09396 -0.0036 0.0041 1.0000
17.750 1.1879 0.10385 0.10099 -0.0071 0.0040 1.0000
18.000 1.1725 0.11086 0.10811 -0.0106 0.0040 1.0000
18.250 1.1563 0.11822 0.11557 -0.0144 0.0041 1.0000
18.500 1.1387 0.12606 0.12353 -0.0185 0.0041 1.0000
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Polar data table (+)
Polar graphs
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