EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.42 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e326-il-1000000.txt Download as CSV file: xf-e326-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 326 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5109 0.08582 0.08427 -0.0178 1.0000 0.0090
-9.750 -0.5259 0.07838 0.07683 -0.0245 1.0000 0.0087
-9.500 -0.5461 0.07253 0.07093 -0.0275 1.0000 0.0088
-9.250 -0.5657 0.06811 0.06645 -0.0275 1.0000 0.0087
-9.000 -0.5840 0.06460 0.06287 -0.0257 1.0000 0.0087
-8.750 -0.6031 0.06160 0.05980 -0.0219 1.0000 0.0087
-8.500 -0.6146 0.05845 0.05656 -0.0186 1.0000 0.0087
-8.250 -0.6229 0.05496 0.05296 -0.0153 1.0000 0.0089
-8.000 -0.6278 0.05158 0.04945 -0.0120 1.0000 0.0090
-7.750 -0.6308 0.04814 0.04587 -0.0083 1.0000 0.0092
-7.500 -0.6134 0.04012 0.03733 -0.0070 0.9682 0.0100
-7.250 -0.5994 0.03259 0.02904 -0.0080 0.8740 0.0102
-7.000 -0.5901 0.03110 0.02726 -0.0053 0.8167 0.0104
-6.750 -0.5772 0.02979 0.02573 -0.0031 0.7829 0.0106
-6.500 -0.5631 0.02827 0.02397 -0.0010 0.7560 0.0108
-6.250 -0.5469 0.02683 0.02232 0.0009 0.7325 0.0110
-6.000 -0.5295 0.02526 0.02049 0.0028 0.7117 0.0115
-5.750 -0.5086 0.02469 0.01948 0.0052 0.6928 0.0129
-5.500 -0.4903 0.02374 0.01819 0.0073 0.6762 0.0130
-5.250 -0.4617 0.01606 0.00991 0.0086 0.6636 0.0072
-5.000 -0.4354 0.01456 0.00823 0.0091 0.6477 0.0068
-4.750 -0.4104 0.01352 0.00704 0.0098 0.6325 0.0065
-4.500 -0.3872 0.01268 0.00607 0.0109 0.6184 0.0063
-4.250 -0.3644 0.01211 0.00540 0.0120 0.6052 0.0063
-4.000 -0.3418 0.01162 0.00482 0.0131 0.5921 0.0063
-3.750 -0.3190 0.01122 0.00434 0.0142 0.5795 0.0063
-3.500 -0.2958 0.01089 0.00392 0.0152 0.5673 0.0065
-3.250 -0.2720 0.01058 0.00355 0.0161 0.5559 0.0068
-3.000 -0.2478 0.01034 0.00325 0.0169 0.5448 0.0071
-2.750 -0.2243 0.01004 0.00288 0.0179 0.5342 0.0087
-2.500 -0.1998 0.00985 0.00264 0.0186 0.5232 0.0110
-2.250 -0.1773 0.00948 0.00238 0.0197 0.5135 0.0392
-2.000 -0.1544 0.00919 0.00223 0.0207 0.5041 0.0827
-1.750 -0.1318 0.00888 0.00209 0.0216 0.4944 0.1410
-1.500 -0.1221 0.00779 0.00180 0.0247 0.4867 0.3722
-1.250 -0.1271 0.00611 0.00138 0.0310 0.4801 0.7042
-1.000 -0.1084 0.00601 0.00160 0.0333 0.4724 0.8154
-0.750 -0.0831 0.00622 0.00181 0.0343 0.4638 0.8401
-0.500 -0.0564 0.00642 0.00196 0.0348 0.4557 0.8512
-0.250 -0.0289 0.00658 0.00210 0.0352 0.4472 0.8589
0.000 -0.0017 0.00675 0.00222 0.0355 0.4400 0.8656
0.250 0.0255 0.00687 0.00230 0.0359 0.4323 0.8713
0.500 0.0533 0.00704 0.00245 0.0362 0.4254 0.8762
0.750 0.0809 0.00712 0.00247 0.0362 0.4181 0.8790
1.000 0.1087 0.00717 0.00246 0.0362 0.4117 0.8806
1.250 0.1368 0.00721 0.00245 0.0361 0.4053 0.8820
1.500 0.1644 0.00728 0.00245 0.0361 0.3984 0.8832
1.750 0.1926 0.00725 0.00240 0.0359 0.3930 0.8844
2.000 0.2206 0.00728 0.00239 0.0358 0.3870 0.8853
2.250 0.2486 0.00732 0.00240 0.0357 0.3813 0.8862
2.500 0.2768 0.00735 0.00241 0.0356 0.3758 0.8872
2.750 0.3046 0.00742 0.00244 0.0355 0.3702 0.8881
3.000 0.3326 0.00746 0.00247 0.0353 0.3652 0.8891
3.250 0.3607 0.00750 0.00250 0.0352 0.3598 0.8900
3.500 0.3883 0.00759 0.00254 0.0351 0.3544 0.8910
3.750 0.4164 0.00763 0.00259 0.0349 0.3497 0.8919
4.000 0.4443 0.00768 0.00263 0.0348 0.3445 0.8929
4.250 0.4717 0.00778 0.00269 0.0347 0.3390 0.8941
4.500 0.4996 0.00783 0.00275 0.0345 0.3344 0.8953
4.750 0.5274 0.00790 0.00281 0.0344 0.3292 0.8963
5.000 0.5546 0.00802 0.00290 0.0343 0.3232 0.8972
5.250 0.5827 0.00807 0.00296 0.0341 0.3185 0.8981
5.500 0.6101 0.00814 0.00303 0.0340 0.3128 0.8991
5.750 0.6371 0.00823 0.00311 0.0340 0.3071 0.9003
6.000 0.6647 0.00828 0.00319 0.0338 0.3018 0.9013
6.250 0.6915 0.00840 0.00330 0.0338 0.2958 0.9025
6.500 0.7187 0.00849 0.00342 0.0338 0.2902 0.9036
6.750 0.7457 0.00860 0.00353 0.0337 0.2840 0.9048
7.000 0.7721 0.00874 0.00368 0.0338 0.2771 0.9063
7.250 0.7990 0.00885 0.00380 0.0337 0.2703 0.9077
7.500 0.8251 0.00901 0.00396 0.0338 0.2628 0.9092
7.750 0.8517 0.00914 0.00411 0.0337 0.2557 0.9105
8.000 0.8776 0.00932 0.00428 0.0338 0.2476 0.9119
8.250 0.9035 0.00950 0.00446 0.0339 0.2388 0.9132
8.500 0.9291 0.00967 0.00464 0.0340 0.2297 0.9147
8.750 0.9536 0.00989 0.00486 0.0343 0.2192 0.9165
9.000 0.9774 0.01016 0.00510 0.0347 0.2070 0.9183
9.250 1.0010 0.01043 0.00536 0.0351 0.1947 0.9201
9.500 1.0235 0.01078 0.00568 0.0356 0.1798 0.9222
9.750 1.0452 0.01117 0.00602 0.0363 0.1639 0.9245
10.000 1.0662 0.01159 0.00640 0.0370 0.1483 0.9270
10.250 1.0864 0.01203 0.00680 0.0379 0.1339 0.9297
10.500 1.1047 0.01252 0.00725 0.0391 0.1189 0.9329
10.750 1.1225 0.01300 0.00771 0.0403 0.1067 0.9363
11.000 1.1393 0.01352 0.00821 0.0417 0.0950 0.9402
11.250 1.1553 0.01405 0.00872 0.0432 0.0846 0.9444
11.500 1.1686 0.01460 0.00927 0.0452 0.0748 0.9499
11.750 1.1791 0.01521 0.00987 0.0475 0.0652 0.9573
12.000 1.1907 0.01574 0.01044 0.0497 0.0587 0.9663
12.250 1.2075 0.01649 0.01120 0.0504 0.0511 0.9760
12.500 1.2293 0.01745 0.01216 0.0495 0.0434 0.9844
12.750 1.2530 0.01860 0.01330 0.0478 0.0362 0.9905
13.000 1.2684 0.01986 0.01457 0.0473 0.0305 1.0000
13.250 1.2687 0.02092 0.01567 0.0498 0.0279 1.0000
13.500 1.2684 0.02243 0.01720 0.0515 0.0253 1.0000
13.750 1.2694 0.02414 0.01896 0.0525 0.0227 1.0000
14.000 1.2705 0.02609 0.02098 0.0530 0.0211 1.0000
14.250 1.2680 0.02857 0.02349 0.0532 0.0190 1.0000
14.500 1.2689 0.03089 0.02589 0.0530 0.0175 1.0000
14.750 1.2677 0.03352 0.02859 0.0527 0.0166 1.0000
15.000 1.2622 0.03668 0.03183 0.0522 0.0158 1.0000
15.250 1.2560 0.03998 0.03519 0.0516 0.0146 1.0000
15.500 1.2521 0.04311 0.03841 0.0509 0.0141 1.0000
15.750 1.2449 0.04664 0.04204 0.0500 0.0139 1.0000
16.000 1.2394 0.04999 0.04547 0.0492 0.0131 1.0000
16.250 1.2300 0.05388 0.04943 0.0481 0.0124 1.0000
16.500 1.2194 0.05806 0.05369 0.0468 0.0121 1.0000
16.750 1.2085 0.06243 0.05814 0.0454 0.0117 1.0000
17.000 1.1982 0.06679 0.06258 0.0439 0.0113 1.0000
17.250 1.1926 0.07063 0.06651 0.0425 0.0109 1.0000
17.500 1.1838 0.07499 0.07096 0.0409 0.0106 1.0000
17.750 1.1756 0.07931 0.07536 0.0393 0.0104 1.0000
18.000 1.1675 0.08368 0.07980 0.0375 0.0099 1.0000
18.250 1.1584 0.08832 0.08452 0.0357 0.0097 1.0000
18.500 1.1479 0.09319 0.08946 0.0336 0.0093 1.0000
18.750 1.1362 0.09839 0.09474 0.0314 0.0090 1.0000
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