EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 1,000,000 Max Cl/Cd: 84 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e360-il-1000000-n5.txt Download as CSV file: xf-e360-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 360 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8218 0.05775 0.05553 -0.0451 1.0000 0.0040
-13.000 -0.8579 0.04888 0.04642 -0.0506 1.0000 0.0040
-12.750 -0.8752 0.04433 0.04171 -0.0517 1.0000 0.0040
-12.500 -0.8966 0.04007 0.03723 -0.0511 1.0000 0.0040
-12.250 -0.9217 0.03597 0.03287 -0.0488 1.0000 0.0040
-12.000 -0.9237 0.03418 0.03095 -0.0467 1.0000 0.0040
-11.750 -0.9263 0.03248 0.02911 -0.0439 1.0000 0.0040
-11.500 -0.9316 0.03072 0.02719 -0.0403 1.0000 0.0040
-11.250 -0.9415 0.02881 0.02508 -0.0354 1.0000 0.0040
-11.000 -0.9418 0.02717 0.02326 -0.0317 1.0000 0.0040
-10.750 -0.9351 0.02591 0.02185 -0.0288 1.0000 0.0040
-10.500 -0.9266 0.02470 0.02051 -0.0261 1.0000 0.0040
-10.250 -0.9179 0.02340 0.01904 -0.0233 1.0000 0.0041
-10.000 -0.9068 0.02231 0.01781 -0.0208 1.0000 0.0041
-9.500 -0.8593 0.02030 0.01555 -0.0207 0.9941 0.0041
-9.250 -0.8337 0.01925 0.01437 -0.0209 0.9880 0.0042
-9.000 -0.8057 0.01826 0.01327 -0.0216 0.9810 0.0042
-8.750 -0.7764 0.01716 0.01202 -0.0225 0.9688 0.0042
-8.250 -0.7036 0.01499 0.00950 -0.0273 0.9040 0.0044
-8.000 -0.6828 0.01452 0.00883 -0.0260 0.8672 0.0044
-7.750 -0.6624 0.01403 0.00818 -0.0246 0.8406 0.0045
-7.250 -0.6193 0.01316 0.00707 -0.0223 0.7992 0.0046
-7.000 -0.5966 0.01279 0.00660 -0.0214 0.7822 0.0047
-6.750 -0.5735 0.01242 0.00614 -0.0205 0.7677 0.0048
-6.250 -0.5259 0.01178 0.00534 -0.0190 0.7404 0.0049
-6.000 -0.5017 0.01148 0.00497 -0.0182 0.7277 0.0051
-5.750 -0.4773 0.01119 0.00462 -0.0176 0.7168 0.0053
-5.250 -0.4275 0.01070 0.00400 -0.0164 0.6950 0.0057
-5.000 -0.4022 0.01049 0.00373 -0.0159 0.6852 0.0060
-4.750 -0.3770 0.01026 0.00345 -0.0153 0.6758 0.0064
-4.500 -0.3515 0.01004 0.00321 -0.0148 0.6674 0.0073
-4.250 -0.3257 0.00988 0.00300 -0.0144 0.6586 0.0082
-4.000 -0.2998 0.00968 0.00278 -0.0140 0.6507 0.0102
-3.750 -0.2740 0.00951 0.00260 -0.0136 0.6430 0.0136
-3.500 -0.2479 0.00933 0.00243 -0.0132 0.6359 0.0188
-3.250 -0.2219 0.00917 0.00227 -0.0128 0.6283 0.0267
-3.000 -0.1959 0.00899 0.00213 -0.0125 0.6220 0.0386
-2.750 -0.1701 0.00879 0.00200 -0.0121 0.6151 0.0584
-2.500 -0.1450 0.00854 0.00186 -0.0116 0.6088 0.0911
-2.250 -0.1207 0.00817 0.00171 -0.0110 0.6028 0.1523
-2.000 -0.0977 0.00774 0.00156 -0.0102 0.5967 0.2387
-1.750 -0.0743 0.00732 0.00142 -0.0095 0.5912 0.3262
-1.500 -0.0509 0.00691 0.00130 -0.0088 0.5854 0.4141
-1.250 -0.0282 0.00649 0.00118 -0.0079 0.5797 0.5103
-1.000 -0.0056 0.00608 0.00110 -0.0069 0.5745 0.6093
-0.750 0.0189 0.00587 0.00107 -0.0061 0.5688 0.6719
-0.250 0.0709 0.00572 0.00110 -0.0052 0.5559 0.7451
0.000 0.0978 0.00574 0.00111 -0.0049 0.5462 0.7629
0.250 0.1251 0.00576 0.00112 -0.0047 0.5347 0.7765
0.500 0.1525 0.00580 0.00114 -0.0045 0.5217 0.7878
0.750 0.1797 0.00586 0.00115 -0.0043 0.5060 0.7973
1.000 0.2071 0.00593 0.00117 -0.0041 0.4913 0.8039
1.250 0.2348 0.00598 0.00120 -0.0041 0.4803 0.8091
1.500 0.2625 0.00606 0.00122 -0.0040 0.4673 0.8137
1.750 0.2901 0.00615 0.00125 -0.0039 0.4523 0.8177
2.000 0.3174 0.00623 0.00130 -0.0038 0.4368 0.8218
2.250 0.3443 0.00636 0.00135 -0.0037 0.4146 0.8261
2.500 0.3709 0.00654 0.00142 -0.0034 0.3883 0.8305
2.750 0.3971 0.00673 0.00152 -0.0032 0.3609 0.8343
3.000 0.4225 0.00698 0.00164 -0.0028 0.3252 0.8386
3.250 0.4472 0.00731 0.00180 -0.0023 0.2847 0.8431
3.500 0.4726 0.00758 0.00194 -0.0020 0.2538 0.8475
3.750 0.4981 0.00782 0.00209 -0.0016 0.2291 0.8516
4.000 0.5235 0.00805 0.00225 -0.0013 0.2069 0.8560
4.250 0.5489 0.00830 0.00240 -0.0009 0.1851 0.8608
4.750 0.5999 0.00872 0.00273 -0.0002 0.1546 0.8698
5.000 0.6257 0.00891 0.00289 0.0001 0.1440 0.8748
5.250 0.6512 0.00912 0.00306 0.0004 0.1333 0.8799
5.500 0.6763 0.00932 0.00324 0.0008 0.1243 0.8848
5.750 0.7020 0.00947 0.00340 0.0012 0.1186 0.8904
6.000 0.7271 0.00969 0.00359 0.0016 0.1115 0.8962
6.250 0.7523 0.00985 0.00378 0.0020 0.1065 0.9021
6.500 0.7770 0.01005 0.00398 0.0024 0.1010 0.9087
6.750 0.8016 0.01025 0.00419 0.0029 0.0959 0.9155
7.000 0.8264 0.01042 0.00440 0.0034 0.0928 0.9234
7.250 0.8508 0.01063 0.00462 0.0040 0.0889 0.9314
7.500 0.8748 0.01087 0.00486 0.0045 0.0841 0.9410
7.750 0.9009 0.01106 0.00510 0.0047 0.0815 0.9504
8.000 0.9279 0.01131 0.00536 0.0046 0.0781 0.9600
8.250 0.9568 0.01161 0.00566 0.0039 0.0740 0.9684
8.500 0.9870 0.01189 0.00596 0.0031 0.0709 0.9753
8.750 1.0176 0.01218 0.00626 0.0021 0.0679 0.9817
9.000 1.0477 0.01253 0.00660 0.0011 0.0640 0.9869
9.250 1.0783 0.01286 0.00695 0.0000 0.0610 0.9913
9.500 1.1080 0.01319 0.00730 -0.0009 0.0583 0.9963
9.750 1.1339 0.01357 0.00767 -0.0011 0.0548 1.0000
10.000 1.1511 0.01390 0.00801 0.0007 0.0522 1.0000
10.250 1.1695 0.01420 0.00834 0.0021 0.0505 1.0000
10.500 1.1874 0.01455 0.00870 0.0037 0.0479 1.0000
10.750 1.2040 0.01498 0.00911 0.0053 0.0446 1.0000
11.000 1.2217 0.01535 0.00951 0.0068 0.0427 1.0000
11.250 1.2384 0.01574 0.00993 0.0084 0.0406 1.0000
11.500 1.2518 0.01618 0.01038 0.0106 0.0386 1.0000
11.750 1.2639 0.01666 0.01088 0.0129 0.0366 1.0000
12.000 1.2779 0.01709 0.01135 0.0149 0.0356 1.0000
12.250 1.2913 0.01759 0.01189 0.0168 0.0342 1.0000
12.500 1.3031 0.01819 0.01251 0.0188 0.0322 1.0000
12.750 1.3144 0.01886 0.01321 0.0207 0.0306 1.0000
13.000 1.3267 0.01951 0.01391 0.0224 0.0296 1.0000
13.250 1.3386 0.02021 0.01466 0.0239 0.0284 1.0000
13.500 1.3491 0.02105 0.01553 0.0254 0.0269 1.0000
13.750 1.3569 0.02211 0.01660 0.0270 0.0238 1.0000
14.000 1.3677 0.02304 0.01760 0.0282 0.0239 1.0000
14.250 1.3773 0.02410 0.01873 0.0293 0.0228 1.0000
14.500 1.3826 0.02554 0.02016 0.0306 0.0199 1.0000
14.750 1.3919 0.02675 0.02145 0.0314 0.0197 1.0000
15.000 1.3999 0.02811 0.02287 0.0321 0.0190 1.0000
15.250 1.4072 0.02957 0.02441 0.0328 0.0185 1.0000
15.500 1.4093 0.03155 0.02640 0.0334 0.0159 1.0000
15.750 1.4148 0.03329 0.02821 0.0338 0.0153 1.0000
16.000 1.4192 0.03519 0.03018 0.0341 0.0146 1.0000
16.250 1.4214 0.03735 0.03240 0.0343 0.0138 1.0000
16.500 1.4216 0.03977 0.03489 0.0343 0.0129 1.0000
16.750 1.4232 0.04212 0.03732 0.0342 0.0123 1.0000
17.000 1.4235 0.04464 0.03993 0.0340 0.0119 1.0000
17.250 1.4223 0.04743 0.04280 0.0336 0.0115 1.0000
17.500 1.4206 0.05039 0.04585 0.0330 0.0113 1.0000
17.750 1.4166 0.05369 0.04924 0.0322 0.0109 1.0000
18.000 1.4097 0.05748 0.05312 0.0311 0.0103 1.0000
18.250 1.4029 0.06142 0.05714 0.0298 0.0097 1.0000
18.500 1.3971 0.06533 0.06116 0.0284 0.0097 1.0000
18.750 1.3880 0.06984 0.06578 0.0266 0.0095 1.0000
19.000 1.3767 0.07483 0.07088 0.0245 0.0092 1.0000
19.250 1.3618 0.08053 0.07670 0.0219 0.0089 1.0000
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