EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 500,000 Max Cl/Cd: 76.49 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e326-il-500000.txt Download as CSV file: xf-e326-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5068 0.08613 0.08397 -0.0208 1.0000 0.0163
-9.750 -0.5141 0.08127 0.07910 -0.0241 1.0000 0.0162
-9.000 -0.5657 0.06686 0.06448 -0.0265 1.0000 0.0163
-8.750 -0.5872 0.06302 0.06048 -0.0228 1.0000 0.0165
-8.500 -0.6001 0.05992 0.05724 -0.0191 1.0000 0.0165
-8.250 -0.6111 0.05663 0.05374 -0.0152 1.0000 0.0166
-8.000 -0.6252 0.05210 0.04902 -0.0112 1.0000 0.0167
-7.750 -0.6241 0.04922 0.04612 -0.0088 1.0000 0.0169
-7.500 -0.6214 0.04712 0.04399 -0.0063 1.0000 0.0172
-7.250 -0.6173 0.04502 0.04180 -0.0034 1.0000 0.0173
-7.000 -0.6123 0.04315 0.03986 -0.0006 1.0000 0.0177
-6.750 -0.5922 0.04043 0.03699 -0.0009 0.9879 0.0183
-6.500 -0.5570 0.03736 0.03320 -0.0017 0.9426 0.0209
-6.250 -0.5271 0.03168 0.02720 -0.0046 0.8865 0.0218
-6.000 -0.5102 0.03021 0.02546 -0.0030 0.8349 0.0223
-5.750 -0.4940 0.02884 0.02382 -0.0009 0.7998 0.0232
-5.500 -0.4750 0.02948 0.02391 0.0022 0.7713 0.0261
-5.250 -0.4523 0.01992 0.01342 0.0055 0.7548 0.0136
-5.000 -0.4246 0.01826 0.01155 0.0060 0.7325 0.0120
-4.750 -0.3944 0.01619 0.00910 0.0063 0.7130 0.0106
-4.500 -0.3684 0.01518 0.00790 0.0071 0.6948 0.0104
-4.250 -0.3444 0.01444 0.00704 0.0080 0.6775 0.0104
-4.000 -0.3221 0.01376 0.00628 0.0091 0.6609 0.0106
-3.750 -0.3003 0.01324 0.00567 0.0104 0.6454 0.0110
-3.500 -0.2784 0.01279 0.00514 0.0117 0.6308 0.0116
-3.250 -0.2557 0.01243 0.00469 0.0128 0.6169 0.0129
-3.000 -0.2343 0.01197 0.00417 0.0142 0.6035 0.0145
-2.750 -0.2118 0.01161 0.00375 0.0154 0.5906 0.0193
-2.500 -0.1924 0.01103 0.00333 0.0171 0.5790 0.0575
-2.250 -0.1764 0.01031 0.00305 0.0191 0.5683 0.1780
-2.000 -0.1817 0.00846 0.00255 0.0249 0.5594 0.5168
-1.750 -0.1837 0.00752 0.00272 0.0316 0.5508 0.7962
-1.500 -0.1619 0.00787 0.00301 0.0336 0.5399 0.8371
-1.250 -0.1350 0.00844 0.00359 0.0349 0.5295 0.8589
-1.000 -0.1077 0.00898 0.00405 0.0360 0.5198 0.8726
-0.750 -0.0828 0.00932 0.00430 0.0372 0.5097 0.8832
-0.500 -0.0461 0.00994 0.00486 0.0364 0.4996 0.8895
-0.250 -0.0212 0.01030 0.00511 0.0376 0.4910 0.8989
0.000 0.0233 0.01080 0.00555 0.0350 0.4808 0.9022
0.250 0.0549 0.01091 0.00556 0.0343 0.4725 0.9037
0.500 0.0834 0.01093 0.00551 0.0342 0.4639 0.9054
0.750 0.1085 0.01092 0.00542 0.0346 0.4568 0.9076
1.000 0.1276 0.01081 0.00527 0.0362 0.4497 0.9109
1.250 0.1435 0.01068 0.00506 0.0384 0.4433 0.9143
1.500 0.1723 0.01065 0.00499 0.0382 0.4360 0.9152
1.750 0.1998 0.01068 0.00494 0.0381 0.4295 0.9161
2.000 0.2281 0.01067 0.00492 0.0379 0.4229 0.9172
2.250 0.2552 0.01070 0.00489 0.0380 0.4164 0.9184
2.500 0.2816 0.01071 0.00487 0.0381 0.4106 0.9196
2.750 0.3081 0.01071 0.00486 0.0382 0.4045 0.9211
3.000 0.3324 0.01075 0.00483 0.0388 0.3987 0.9228
3.250 0.3562 0.01070 0.00479 0.0394 0.3932 0.9246
3.500 0.3782 0.01066 0.00474 0.0404 0.3878 0.9267
3.750 0.3992 0.01069 0.00470 0.0415 0.3827 0.9290
4.000 0.4266 0.01065 0.00471 0.0414 0.3772 0.9299
4.250 0.4536 0.01069 0.00473 0.0414 0.3717 0.9308
4.500 0.4804 0.01077 0.00478 0.0414 0.3665 0.9318
4.750 0.5075 0.01079 0.00484 0.0414 0.3609 0.9329
5.000 0.5339 0.01086 0.00489 0.0415 0.3556 0.9341
5.250 0.5601 0.01094 0.00498 0.0416 0.3502 0.9356
5.500 0.5860 0.01098 0.00506 0.0418 0.3446 0.9373
5.750 0.6102 0.01107 0.00511 0.0422 0.3392 0.9390
6.000 0.6346 0.01110 0.00519 0.0427 0.3338 0.9408
6.250 0.6581 0.01113 0.00525 0.0432 0.3279 0.9427
6.500 0.6823 0.01125 0.00534 0.0436 0.3223 0.9443
6.750 0.7097 0.01128 0.00545 0.0435 0.3163 0.9454
7.000 0.7361 0.01140 0.00557 0.0435 0.3101 0.9467
7.250 0.7628 0.01150 0.00573 0.0434 0.3039 0.9482
7.500 0.7888 0.01161 0.00587 0.0435 0.2972 0.9500
7.750 0.8137 0.01175 0.00603 0.0438 0.2906 0.9520
8.000 0.8381 0.01184 0.00618 0.0441 0.2830 0.9541
8.250 0.8603 0.01197 0.00633 0.0449 0.2760 0.9567
8.500 0.8842 0.01208 0.00649 0.0453 0.2682 0.9588
8.750 0.9113 0.01226 0.00672 0.0450 0.2598 0.9603
9.000 0.9376 0.01250 0.00696 0.0447 0.2500 0.9621
9.250 0.9646 0.01269 0.00721 0.0444 0.2399 0.9639
9.500 0.9897 0.01294 0.00750 0.0444 0.2294 0.9663
9.750 1.0120 0.01323 0.00780 0.0449 0.2176 0.9696
10.000 1.0350 0.01356 0.00814 0.0452 0.2046 0.9726
10.250 1.0631 0.01401 0.00859 0.0443 0.1887 0.9742
10.500 1.0896 0.01458 0.00913 0.0435 0.1703 0.9761
10.750 1.1136 0.01527 0.00976 0.0430 0.1516 0.9786
11.000 1.1363 0.01594 0.01041 0.0428 0.1352 0.9819
11.250 1.1591 0.01672 0.01117 0.0423 0.1189 0.9847
11.500 1.1839 0.01773 0.01213 0.0411 0.1023 0.9867
11.750 1.2056 0.01876 0.01314 0.0403 0.0883 0.9901
12.000 1.2238 0.01980 0.01417 0.0400 0.0768 0.9947
12.250 1.2430 0.02106 0.01544 0.0389 0.0654 0.9992
12.500 1.2180 0.02149 0.01592 0.0466 0.0645 1.0000
12.750 1.2133 0.02260 0.01706 0.0498 0.0597 1.0000
13.000 1.2077 0.02443 0.01890 0.0518 0.0544 1.0000
13.250 1.2082 0.02622 0.02075 0.0527 0.0499 1.0000
13.500 1.2015 0.02889 0.02345 0.0532 0.0455 1.0000
13.750 1.2015 0.03118 0.02585 0.0533 0.0423 1.0000
14.000 1.1947 0.03430 0.02900 0.0531 0.0389 1.0000
14.250 1.1858 0.03777 0.03254 0.0526 0.0365 1.0000
14.500 1.1828 0.04071 0.03557 0.0521 0.0339 1.0000
14.750 1.1742 0.04432 0.03924 0.0513 0.0320 1.0000
15.000 1.1591 0.04873 0.04372 0.0503 0.0303 1.0000
15.250 1.1521 0.05230 0.04737 0.0494 0.0291 1.0000
15.500 1.1437 0.05610 0.05128 0.0484 0.0277 1.0000
15.750 1.1350 0.06010 0.05536 0.0471 0.0265 1.0000
16.000 1.1257 0.06431 0.05962 0.0457 0.0255 1.0000
16.250 1.1116 0.06926 0.06463 0.0440 0.0243 1.0000
16.500 1.1006 0.07390 0.06935 0.0423 0.0234 1.0000
16.750 1.0966 0.07769 0.07324 0.0409 0.0226 1.0000
17.000 1.0911 0.08175 0.07739 0.0393 0.0218 1.0000
17.250 1.0851 0.08600 0.08171 0.0375 0.0208 1.0000
17.500 1.0764 0.09070 0.08646 0.0355 0.0200 1.0000
17.750 1.0669 0.09555 0.09135 0.0334 0.0192 1.0000
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