E10(08%) (e228-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E10(08%) (e228-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.6 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e228-il-1000000.txt Download as CSV file: xf-e228-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E10(08%)
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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9630 0.08256 0.08059 -0.0007 1.0000 0.0049
-14.000 -1.0187 0.06649 0.06423 -0.0114 1.0000 0.0047
-13.750 -1.0558 0.05549 0.05298 -0.0191 1.0000 0.0047
-13.500 -1.0683 0.04981 0.04715 -0.0228 1.0000 0.0047
-13.250 -1.0752 0.04567 0.04290 -0.0252 1.0000 0.0048
-13.000 -1.1045 0.03956 0.03651 -0.0269 1.0000 0.0047
-12.750 -1.1152 0.03643 0.03322 -0.0264 1.0000 0.0047
-12.500 -1.1182 0.03440 0.03109 -0.0251 1.0000 0.0048
-12.250 -1.1263 0.03215 0.02867 -0.0226 1.0000 0.0048
-12.000 -1.1241 0.03089 0.02731 -0.0202 1.0000 0.0049
-11.750 -1.1201 0.02978 0.02611 -0.0175 1.0000 0.0050
-11.500 -1.1150 0.02831 0.02449 -0.0151 1.0000 0.0051
-11.250 -1.1026 0.02724 0.02331 -0.0136 1.0000 0.0053
-11.000 -1.0905 0.02593 0.02186 -0.0120 1.0000 0.0054
-10.750 -1.0751 0.02489 0.02070 -0.0106 1.0000 0.0057
-10.500 -1.0599 0.02365 0.01932 -0.0092 1.0000 0.0059
-10.250 -1.0430 0.02253 0.01807 -0.0080 1.0000 0.0061
-10.000 -1.0251 0.02144 0.01684 -0.0068 1.0000 0.0063
-9.750 -1.0043 0.02073 0.01603 -0.0059 1.0000 0.0064
-9.500 -0.9918 0.01869 0.01378 -0.0040 1.0000 0.0068
-9.250 -0.9743 0.01744 0.01240 -0.0027 1.0000 0.0073
-9.000 -0.9519 0.01684 0.01177 -0.0020 1.0000 0.0076
-8.750 -0.9295 0.01618 0.01105 -0.0013 1.0000 0.0079
-8.500 -0.9066 0.01558 0.01039 -0.0006 1.0000 0.0084
-8.250 -0.8831 0.01506 0.00981 0.0000 1.0000 0.0089
-8.000 -0.8589 0.01460 0.00930 0.0005 1.0000 0.0094
-7.750 -0.8363 0.01394 0.00856 0.0013 1.0000 0.0099
-7.500 -0.8165 0.01289 0.00741 0.0026 1.0000 0.0110
-7.250 -0.7922 0.01250 0.00700 0.0031 1.0000 0.0120
-7.000 -0.7676 0.01218 0.00667 0.0036 1.0000 0.0130
-6.750 -0.7436 0.01185 0.00631 0.0043 1.0000 0.0138
-6.500 -0.7226 0.01136 0.00576 0.0055 1.0000 0.0145
-6.250 -0.6939 0.01066 0.00498 0.0051 0.9958 0.0164
-6.000 -0.6602 0.01027 0.00457 0.0036 0.9898 0.0183
-5.750 -0.6257 0.00996 0.00422 0.0021 0.9838 0.0198
-5.500 -0.5942 0.00955 0.00376 0.0013 0.9748 0.0230
-5.250 -0.5655 0.00918 0.00341 0.0011 0.9640 0.0306
-5.000 -0.5420 0.00867 0.00305 0.0019 0.9510 0.0628
-4.750 -0.5194 0.00828 0.00279 0.0030 0.9383 0.0940
-4.500 -0.4960 0.00798 0.00258 0.0039 0.9263 0.1220
-4.250 -0.4721 0.00769 0.00237 0.0048 0.9145 0.1534
-4.000 -0.4473 0.00741 0.00219 0.0054 0.9026 0.1847
-3.750 -0.4225 0.00713 0.00201 0.0060 0.8910 0.2208
-3.500 -0.3972 0.00687 0.00185 0.0066 0.8793 0.2572
-3.250 -0.3715 0.00667 0.00172 0.0070 0.8675 0.2884
-3.000 -0.3459 0.00645 0.00158 0.0075 0.8554 0.3264
-2.750 -0.3205 0.00618 0.00146 0.0080 0.8429 0.3769
-2.500 -0.2942 0.00600 0.00136 0.0083 0.8301 0.4116
-2.250 -0.2680 0.00582 0.00126 0.0087 0.8172 0.4500
-2.000 -0.2417 0.00565 0.00118 0.0090 0.8041 0.4873
-1.750 -0.2152 0.00552 0.00110 0.0094 0.7906 0.5221
-1.500 -0.1886 0.00539 0.00104 0.0097 0.7768 0.5559
-1.250 -0.1621 0.00528 0.00099 0.0101 0.7622 0.5890
-1.000 -0.1355 0.00517 0.00094 0.0104 0.7472 0.6224
-0.750 -0.1090 0.00508 0.00091 0.0108 0.7319 0.6552
-0.500 -0.0826 0.00500 0.00088 0.0112 0.7161 0.6875
-0.250 -0.0562 0.00493 0.00086 0.0116 0.6997 0.7199
0.000 -0.0298 0.00487 0.00085 0.0120 0.6829 0.7507
0.250 -0.0034 0.00482 0.00085 0.0124 0.6655 0.7808
0.500 0.0229 0.00479 0.00086 0.0129 0.6474 0.8094
0.750 0.0493 0.00478 0.00088 0.0134 0.6289 0.8364
1.000 0.0757 0.00478 0.00091 0.0138 0.6099 0.8618
1.250 0.1025 0.00480 0.00094 0.0143 0.5896 0.8854
1.500 0.1297 0.00485 0.00100 0.0146 0.5690 0.9073
1.750 0.1580 0.00493 0.00106 0.0146 0.5465 0.9268
2.000 0.1884 0.00506 0.00114 0.0142 0.5228 0.9422
2.250 0.2199 0.00522 0.00123 0.0135 0.4980 0.9541
2.500 0.2534 0.00539 0.00133 0.0123 0.4712 0.9620
2.750 0.2835 0.00558 0.00143 0.0119 0.4444 0.9705
3.000 0.3195 0.00578 0.00153 0.0101 0.4160 0.9741
3.250 0.3541 0.00600 0.00165 0.0086 0.3859 0.9783
3.500 0.3856 0.00623 0.00178 0.0077 0.3560 0.9831
3.750 0.4226 0.00645 0.00190 0.0056 0.3247 0.9850
4.000 0.4585 0.00672 0.00204 0.0037 0.2884 0.9874
4.250 0.4934 0.00701 0.00220 0.0020 0.2525 0.9903
4.500 0.5268 0.00733 0.00237 0.0006 0.2169 0.9933
4.750 0.5622 0.00764 0.00255 -0.0012 0.1845 0.9952
5.000 0.5976 0.00798 0.00275 -0.0032 0.1500 0.9972
5.250 0.6321 0.00837 0.00298 -0.0049 0.1155 0.9991
5.500 0.6615 0.00875 0.00323 -0.0056 0.0885 1.0000
5.750 0.6841 0.00905 0.00346 -0.0047 0.0718 1.0000
6.000 0.7065 0.00939 0.00373 -0.0038 0.0567 1.0000
6.250 0.7288 0.00975 0.00402 -0.0029 0.0433 1.0000
6.500 0.7513 0.01007 0.00431 -0.0020 0.0344 1.0000
6.750 0.7737 0.01042 0.00463 -0.0010 0.0266 1.0000
7.000 0.7958 0.01082 0.00500 -0.0001 0.0194 1.0000
7.250 0.8172 0.01132 0.00549 0.0010 0.0132 1.0000
7.500 0.8385 0.01185 0.00604 0.0022 0.0104 1.0000
7.750 0.8603 0.01228 0.00650 0.0033 0.0092 1.0000
8.000 0.8804 0.01294 0.00722 0.0046 0.0080 1.0000
8.250 0.9005 0.01357 0.00793 0.0059 0.0074 1.0000
8.500 0.9217 0.01404 0.00845 0.0070 0.0070 1.0000
8.750 0.9424 0.01457 0.00904 0.0081 0.0065 1.0000
9.000 0.9622 0.01517 0.00972 0.0093 0.0063 1.0000
9.250 0.9816 0.01582 0.01043 0.0106 0.0060 1.0000
9.500 1.0003 0.01651 0.01120 0.0120 0.0058 1.0000
9.750 1.0174 0.01736 0.01213 0.0135 0.0056 1.0000
10.000 1.0321 0.01841 0.01328 0.0153 0.0054 1.0000
10.250 1.0441 0.01972 0.01471 0.0174 0.0052 1.0000
10.500 1.0507 0.02155 0.01673 0.0201 0.0051 1.0000
10.750 1.0624 0.02278 0.01809 0.0220 0.0050 1.0000
11.000 1.0718 0.02417 0.01962 0.0241 0.0050 1.0000
11.250 1.0845 0.02508 0.02065 0.0258 0.0049 1.0000
11.500 1.0924 0.02616 0.02184 0.0282 0.0048 1.0000
11.750 1.0956 0.02725 0.02305 0.0311 0.0047 1.0000
12.000 1.0912 0.02915 0.02510 0.0340 0.0047 1.0000
12.250 1.0941 0.03062 0.02669 0.0357 0.0046 1.0000
12.500 1.0951 0.03242 0.02861 0.0369 0.0044 1.0000
12.750 1.0924 0.03479 0.03113 0.0377 0.0043 1.0000
13.000 1.0922 0.03713 0.03358 0.0378 0.0042 1.0000
13.250 1.0779 0.04144 0.03810 0.0371 0.0043 1.0000
13.500 1.0698 0.04542 0.04223 0.0355 0.0043 1.0000
13.750 1.0585 0.05025 0.04722 0.0331 0.0042 1.0000
14.000 1.0470 0.05552 0.05263 0.0301 0.0042 1.0000
14.250 1.0366 0.06097 0.05821 0.0267 0.0041 1.0000
14.500 1.0114 0.06925 0.06668 0.0217 0.0042 1.0000
14.750 0.9922 0.07693 0.07450 0.0170 0.0041 1.0000
15.000 0.9686 0.08572 0.08342 0.0118 0.0042 1.0000
15.250 0.9422 0.09554 0.09338 0.0062 0.0043 1.0000
15.500 0.9154 0.10585 0.10380 0.0006 0.0045 1.0000
15.750 0.8864 0.11735 0.11542 -0.0055 0.0043 1.0000
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Polar data table (+)
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