E220 (11.48%) (e220-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.91 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e220-il-1000000.txt Download as CSV file: xf-e220-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E220 (11.48%)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4970 0.08230 0.08014 -0.0234 0.7728 0.0098
-9.500 -0.4990 0.07843 0.07626 -0.0256 0.7649 0.0100
-9.250 -0.5600 0.05837 0.05617 -0.0406 0.7580 0.0097
-9.000 -0.5980 0.05075 0.04834 -0.0397 0.7509 0.0097
-8.750 -0.6044 0.04848 0.04595 -0.0382 0.7443 0.0098
-8.500 -0.6148 0.04397 0.04122 -0.0365 0.7391 0.0099
-8.250 -0.6136 0.04095 0.03802 -0.0350 0.7337 0.0100
-8.000 -0.6552 0.02820 0.02429 -0.0280 0.7297 0.0076
-7.750 -0.6568 0.02235 0.01766 -0.0239 0.7255 0.0073
-7.500 -0.6384 0.02060 0.01563 -0.0225 0.7210 0.0074
-7.250 -0.6192 0.01883 0.01358 -0.0212 0.7166 0.0074
-7.000 -0.5975 0.01761 0.01216 -0.0202 0.7126 0.0075
-6.750 -0.5748 0.01646 0.01084 -0.0193 0.7088 0.0076
-6.500 -0.5506 0.01574 0.01002 -0.0187 0.7049 0.0079
-6.250 -0.5269 0.01484 0.00897 -0.0179 0.7010 0.0081
-6.000 -0.5025 0.01416 0.00816 -0.0173 0.6973 0.0083
-5.750 -0.4783 0.01333 0.00724 -0.0165 0.6941 0.0086
-5.500 -0.4537 0.01266 0.00647 -0.0159 0.6907 0.0088
-5.250 -0.4284 0.01217 0.00589 -0.0153 0.6872 0.0091
-5.000 -0.4056 0.01131 0.00489 -0.0143 0.6838 0.0098
-4.750 -0.3800 0.01088 0.00442 -0.0139 0.6809 0.0107
-4.500 -0.3536 0.01056 0.00407 -0.0135 0.6778 0.0115
-4.250 -0.3271 0.01027 0.00373 -0.0132 0.6746 0.0124
-4.000 -0.3012 0.00989 0.00328 -0.0128 0.6715 0.0140
-3.750 -0.2746 0.00966 0.00301 -0.0125 0.6684 0.0168
-3.500 -0.2481 0.00933 0.00269 -0.0122 0.6658 0.0229
-3.250 -0.2215 0.00904 0.00243 -0.0119 0.6628 0.0348
-3.000 -0.1954 0.00871 0.00223 -0.0116 0.6598 0.0618
-2.750 -0.1691 0.00845 0.00206 -0.0113 0.6569 0.0945
-2.500 -0.1433 0.00817 0.00192 -0.0111 0.6539 0.1391
-2.250 -0.1175 0.00782 0.00179 -0.0108 0.6514 0.1980
-2.000 -0.0919 0.00747 0.00168 -0.0104 0.6484 0.2669
-1.750 -0.0664 0.00715 0.00158 -0.0101 0.6456 0.3364
-1.500 -0.0418 0.00678 0.00149 -0.0096 0.6427 0.4252
-1.250 -0.0189 0.00637 0.00142 -0.0087 0.6396 0.5386
-1.000 0.0034 0.00593 0.00136 -0.0076 0.6370 0.6465
-0.750 0.0241 0.00551 0.00131 -0.0060 0.6339 0.7534
-0.500 0.0467 0.00516 0.00130 -0.0046 0.6307 0.8521
-0.250 0.1049 0.00523 0.00153 -0.0109 0.6270 0.9329
0.000 0.1385 0.00537 0.00164 -0.0120 0.6235 0.9486
0.250 0.1679 0.00548 0.00173 -0.0121 0.6198 0.9588
0.500 0.2075 0.00559 0.00180 -0.0146 0.6162 0.9631
0.750 0.2348 0.00573 0.00188 -0.0143 0.6125 0.9707
1.000 0.2798 0.00583 0.00195 -0.0180 0.6083 0.9729
1.250 0.3203 0.00588 0.00199 -0.0208 0.6038 0.9755
1.500 0.3574 0.00596 0.00203 -0.0228 0.5994 0.9788
1.750 0.3879 0.00609 0.00213 -0.0233 0.5952 0.9834
2.000 0.4301 0.00608 0.00213 -0.0265 0.5901 0.9850
2.250 0.4706 0.00610 0.00212 -0.0293 0.5844 0.9871
2.500 0.5095 0.00612 0.00213 -0.0318 0.5789 0.9897
2.750 0.5462 0.00613 0.00215 -0.0338 0.5724 0.9927
3.000 0.5834 0.00614 0.00213 -0.0359 0.5661 0.9950
3.250 0.6220 0.00607 0.00207 -0.0384 0.5581 0.9971
3.500 0.6595 0.00604 0.00204 -0.0406 0.5487 0.9992
3.750 0.6901 0.00606 0.00203 -0.0413 0.5390 1.0000
4.000 0.7157 0.00610 0.00207 -0.0410 0.5281 1.0000
4.250 0.7413 0.00616 0.00212 -0.0407 0.5156 1.0000
4.500 0.7666 0.00625 0.00218 -0.0403 0.4999 1.0000
4.750 0.7918 0.00639 0.00226 -0.0399 0.4773 1.0000
5.000 0.8164 0.00661 0.00238 -0.0395 0.4478 1.0000
5.250 0.8404 0.00693 0.00256 -0.0390 0.4108 1.0000
5.500 0.8643 0.00726 0.00276 -0.0386 0.3760 1.0000
5.750 0.8875 0.00766 0.00301 -0.0380 0.3386 1.0000
6.000 0.9096 0.00818 0.00332 -0.0374 0.2914 1.0000
6.250 0.9315 0.00868 0.00363 -0.0367 0.2510 1.0000
6.500 0.9528 0.00921 0.00399 -0.0359 0.2121 1.0000
6.750 0.9742 0.00969 0.00432 -0.0351 0.1813 1.0000
7.000 0.9952 0.01016 0.00468 -0.0342 0.1553 1.0000
7.250 1.0154 0.01067 0.00506 -0.0332 0.1296 1.0000
7.500 1.0352 0.01118 0.00547 -0.0321 0.1068 1.0000
7.750 1.0545 0.01168 0.00589 -0.0309 0.0881 1.0000
8.000 1.0735 0.01217 0.00631 -0.0296 0.0724 1.0000
8.250 1.0914 0.01271 0.00677 -0.0282 0.0579 1.0000
8.500 1.1082 0.01329 0.00728 -0.0266 0.0445 1.0000
8.750 1.1239 0.01389 0.00782 -0.0249 0.0323 1.0000
9.000 1.1381 0.01453 0.00842 -0.0229 0.0231 1.0000
9.250 1.1507 0.01521 0.00907 -0.0206 0.0179 1.0000
9.500 1.1659 0.01567 0.00958 -0.0186 0.0167 1.0000
9.750 1.1782 0.01624 0.01018 -0.0163 0.0151 1.0000
10.000 1.1867 0.01694 0.01091 -0.0134 0.0135 1.0000
10.250 1.1895 0.01758 0.01161 -0.0094 0.0127 1.0000
10.500 1.1933 0.01804 0.01212 -0.0057 0.0120 1.0000
10.750 1.1972 0.01874 0.01288 -0.0024 0.0115 1.0000
11.000 1.2038 0.01952 0.01371 0.0001 0.0109 1.0000
11.250 1.2090 0.02053 0.01476 0.0025 0.0101 1.0000
11.500 1.2086 0.02205 0.01637 0.0051 0.0092 1.0000
11.750 1.2190 0.02297 0.01734 0.0065 0.0087 1.0000
12.000 1.2265 0.02415 0.01860 0.0080 0.0085 1.0000
12.250 1.2372 0.02515 0.01964 0.0092 0.0079 1.0000
12.500 1.2450 0.02642 0.02097 0.0104 0.0075 1.0000
12.750 1.2514 0.02784 0.02244 0.0116 0.0070 1.0000
13.000 1.2545 0.02959 0.02426 0.0128 0.0067 1.0000
13.250 1.2492 0.03212 0.02691 0.0143 0.0062 1.0000
13.500 1.2530 0.03394 0.02881 0.0153 0.0061 1.0000
13.750 1.2605 0.03545 0.03041 0.0160 0.0059 1.0000
14.000 1.2683 0.03696 0.03198 0.0166 0.0055 1.0000
14.250 1.2728 0.03881 0.03391 0.0172 0.0053 1.0000
14.500 1.2770 0.04073 0.03590 0.0177 0.0051 1.0000
14.750 1.2810 0.04270 0.03793 0.0181 0.0050 1.0000
15.000 1.2840 0.04488 0.04017 0.0184 0.0047 1.0000
15.250 1.2852 0.04730 0.04266 0.0185 0.0045 1.0000
15.500 1.2730 0.05134 0.04682 0.0185 0.0042 1.0000
15.750 1.2721 0.05423 0.04980 0.0183 0.0043 1.0000
16.000 1.2585 0.05876 0.05448 0.0178 0.0042 1.0000
16.250 1.2483 0.06312 0.05897 0.0171 0.0040 1.0000
16.500 1.2382 0.06753 0.06349 0.0162 0.0041 1.0000
16.750 1.2435 0.07010 0.06614 0.0154 0.0039 1.0000
17.000 1.2351 0.07455 0.07071 0.0142 0.0040 1.0000
17.250 1.2237 0.07960 0.07588 0.0127 0.0039 1.0000
17.500 1.2205 0.08355 0.07993 0.0113 0.0039 1.0000
17.750 1.2089 0.08893 0.08544 0.0094 0.0038 1.0000
18.000 1.1958 0.09466 0.09130 0.0072 0.0037 1.0000
18.250 1.1873 0.09980 0.09654 0.0051 0.0036 1.0000
18.500 1.1690 0.10656 0.10343 0.0024 0.0038 1.0000
18.750 1.1591 0.11224 0.10922 -0.0002 0.0036 1.0000
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Polar data table (+)
Polar graphs
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