E221 (9.39%) (e221-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E221 (9.39%) (e221-il) Reynolds number: 500,000 Max Cl/Cd: 79.22 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e221-il-500000-n5.txt Download as CSV file: xf-e221-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5607 0.08428 0.08214 -0.0042 1.0000 0.0057
-9.000 -0.5704 0.07804 0.07594 -0.0080 1.0000 0.0057
-8.750 -0.5849 0.07130 0.06925 -0.0133 1.0000 0.0058
-8.500 -0.6012 0.06496 0.06290 -0.0184 1.0000 0.0055
-8.250 -0.6177 0.05556 0.05336 -0.0234 1.0000 0.0054
-8.000 -0.6343 0.04511 0.04259 -0.0251 1.0000 0.0053
-7.750 -0.6549 0.03329 0.03006 -0.0233 1.0000 0.0053
-7.500 -0.6513 0.02796 0.02416 -0.0212 1.0000 0.0055
-7.250 -0.6390 0.02461 0.02036 -0.0194 1.0000 0.0056
-7.000 -0.6201 0.02203 0.01737 -0.0184 0.9906 0.0057
-6.750 -0.5892 0.02029 0.01530 -0.0196 0.9602 0.0060
-6.500 -0.5605 0.01883 0.01352 -0.0200 0.9245 0.0063
-6.250 -0.5382 0.01788 0.01227 -0.0188 0.8906 0.0065
-6.000 -0.5167 0.01694 0.01104 -0.0174 0.8643 0.0066
-5.750 -0.4943 0.01600 0.00986 -0.0162 0.8426 0.0066
-5.500 -0.4716 0.01497 0.00862 -0.0151 0.8237 0.0067
-5.250 -0.4492 0.01385 0.00730 -0.0140 0.8068 0.0070
-5.000 -0.4255 0.01309 0.00639 -0.0132 0.7914 0.0073
-4.750 -0.4009 0.01254 0.00572 -0.0125 0.7770 0.0077
-4.500 -0.3757 0.01208 0.00515 -0.0119 0.7634 0.0081
-4.250 -0.3502 0.01168 0.00464 -0.0113 0.7507 0.0086
-4.000 -0.3243 0.01132 0.00417 -0.0108 0.7384 0.0091
-3.750 -0.2981 0.01102 0.00375 -0.0104 0.7265 0.0097
-3.500 -0.2720 0.01069 0.00333 -0.0099 0.7149 0.0112
-3.250 -0.2455 0.01043 0.00300 -0.0095 0.7039 0.0130
-3.000 -0.2189 0.01018 0.00269 -0.0091 0.6931 0.0165
-2.750 -0.1928 0.00987 0.00241 -0.0088 0.6825 0.0347
-2.500 -0.1664 0.00960 0.00220 -0.0084 0.6717 0.0590
-2.250 -0.1407 0.00925 0.00201 -0.0081 0.6617 0.1073
-2.000 -0.1149 0.00892 0.00185 -0.0077 0.6514 0.1642
-1.750 -0.0894 0.00855 0.00171 -0.0074 0.6411 0.2389
-1.500 -0.0637 0.00824 0.00159 -0.0070 0.6310 0.3076
-1.250 -0.0384 0.00793 0.00149 -0.0066 0.6211 0.3856
-0.750 0.0107 0.00725 0.00133 -0.0054 0.6005 0.5646
-0.500 0.0339 0.00691 0.00128 -0.0043 0.5905 0.6597
-0.250 0.0557 0.00653 0.00125 -0.0029 0.5802 0.7667
0.000 0.0863 0.00625 0.00132 -0.0029 0.5690 0.8843
0.250 0.1413 0.00638 0.00143 -0.0085 0.5558 0.9352
0.500 0.1762 0.00650 0.00148 -0.0098 0.5442 0.9537
0.750 0.2087 0.00662 0.00151 -0.0107 0.5321 0.9660
1.000 0.2426 0.00674 0.00155 -0.0119 0.5198 0.9746
1.500 0.3148 0.00694 0.00161 -0.0154 0.4936 0.9861
1.750 0.3542 0.00703 0.00162 -0.0179 0.4793 0.9907
2.000 0.3912 0.00713 0.00166 -0.0200 0.4651 0.9949
2.750 0.4873 0.00739 0.00175 -0.0229 0.4215 1.0000
3.000 0.5128 0.00749 0.00182 -0.0225 0.4082 1.0000
3.250 0.5381 0.00762 0.00190 -0.0220 0.3936 1.0000
3.500 0.5634 0.00776 0.00199 -0.0215 0.3786 1.0000
3.750 0.5885 0.00791 0.00210 -0.0210 0.3627 1.0000
4.000 0.6137 0.00808 0.00222 -0.0205 0.3453 1.0000
4.250 0.6387 0.00825 0.00236 -0.0200 0.3280 1.0000
4.500 0.6635 0.00846 0.00251 -0.0195 0.3093 1.0000
4.750 0.6881 0.00869 0.00270 -0.0190 0.2897 1.0000
5.000 0.7122 0.00899 0.00290 -0.0184 0.2635 1.0000
5.250 0.7358 0.00936 0.00314 -0.0178 0.2316 1.0000
5.500 0.7587 0.00981 0.00342 -0.0171 0.1954 1.0000
5.750 0.7815 0.01027 0.00375 -0.0164 0.1637 1.0000
6.000 0.8048 0.01064 0.00405 -0.0157 0.1428 1.0000
6.250 0.8277 0.01104 0.00438 -0.0150 0.1233 1.0000
6.500 0.8500 0.01152 0.00475 -0.0142 0.1004 1.0000
6.750 0.8721 0.01199 0.00514 -0.0133 0.0805 1.0000
7.000 0.8938 0.01248 0.00558 -0.0125 0.0636 1.0000
7.250 0.9152 0.01301 0.00603 -0.0115 0.0472 1.0000
7.500 0.9355 0.01363 0.00657 -0.0105 0.0310 1.0000
7.750 0.9558 0.01424 0.00713 -0.0094 0.0192 1.0000
8.000 0.9764 0.01478 0.00768 -0.0084 0.0152 1.0000
8.250 0.9970 0.01532 0.00827 -0.0073 0.0135 1.0000
8.500 1.0171 0.01590 0.00890 -0.0061 0.0124 1.0000
8.750 1.0374 0.01642 0.00951 -0.0050 0.0119 1.0000
9.000 1.0569 0.01699 0.01017 -0.0038 0.0115 1.0000
9.250 1.0758 0.01760 0.01086 -0.0026 0.0110 1.0000
9.500 1.0938 0.01826 0.01160 -0.0013 0.0105 1.0000
9.750 1.1111 0.01896 0.01239 0.0001 0.0100 1.0000
10.000 1.1268 0.01975 0.01326 0.0016 0.0096 1.0000
10.250 1.1407 0.02066 0.01426 0.0034 0.0093 1.0000
10.500 1.1520 0.02172 0.01541 0.0053 0.0090 1.0000
10.750 1.1589 0.02302 0.01682 0.0078 0.0087 1.0000
11.000 1.1657 0.02412 0.01803 0.0102 0.0085 1.0000
11.250 1.1699 0.02516 0.01916 0.0130 0.0085 1.0000
11.500 1.1750 0.02630 0.02041 0.0152 0.0083 1.0000
11.750 1.1799 0.02761 0.02185 0.0169 0.0082 1.0000
12.000 1.1825 0.02930 0.02365 0.0183 0.0081 1.0000
12.250 1.1861 0.03107 0.02554 0.0193 0.0079 1.0000
12.500 1.1902 0.03293 0.02751 0.0198 0.0078 1.0000
12.750 1.1939 0.03496 0.02966 0.0201 0.0075 1.0000
13.000 1.1921 0.03770 0.03253 0.0203 0.0074 1.0000
13.250 1.1960 0.03993 0.03486 0.0201 0.0071 1.0000
13.500 1.1946 0.04284 0.03790 0.0197 0.0070 1.0000
13.750 1.1925 0.04594 0.04112 0.0191 0.0070 1.0000
14.000 1.1901 0.04920 0.04450 0.0182 0.0068 1.0000
14.250 1.1860 0.05279 0.04822 0.0172 0.0067 1.0000
14.500 1.1813 0.05656 0.05211 0.0159 0.0067 1.0000
14.750 1.1766 0.06048 0.05613 0.0143 0.0065 1.0000
15.000 1.1695 0.06481 0.06059 0.0126 0.0065 1.0000
15.250 1.1610 0.06956 0.06545 0.0106 0.0064 1.0000
15.500 1.1522 0.07452 0.07056 0.0084 0.0064 1.0000
15.750 1.1448 0.07953 0.07566 0.0058 0.0063 1.0000
16.000 1.1334 0.08527 0.08155 0.0031 0.0063 1.0000
16.250 1.1241 0.09092 0.08730 0.0002 0.0062 1.0000
16.500 1.1132 0.09702 0.09349 -0.0030 0.0061 1.0000
16.750 1.1007 0.10352 0.10013 -0.0063 0.0061 1.0000
17.000 1.0881 0.11025 0.10698 -0.0098 0.0061 1.0000
17.250 1.0759 0.11713 0.11397 -0.0135 0.0060 1.0000
17.500 1.0638 0.12419 0.12115 -0.0173 0.0060 1.0000
17.750 1.0485 0.13216 0.12925 -0.0216 0.0061 1.0000
18.000 1.0363 0.13958 0.13675 -0.0257 0.0059 1.0000
18.250 1.0237 0.14749 0.14478 -0.0301 0.0060 1.0000
18.500 1.0097 0.15590 0.15328 -0.0349 0.0060 1.0000
18.750 0.9876 0.16718 0.16471 -0.0411 0.0061 1.0000
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Polar data table (+)
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