EPPLER 329 AIRFOIL (e329-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 329 AIRFOIL (e329-il) Reynolds number: 50,000 Max Cl/Cd: 27.62 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e329-il-50000-n5.txt Download as CSV file: xf-e329-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 329 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3346 0.11525 0.10846 -0.0283 1.0000 0.1101
-9.750 -0.3513 0.11315 0.10650 -0.0320 1.0000 0.1145
-9.500 -0.3711 0.11065 0.10415 -0.0362 1.0000 0.1153
-9.250 -0.3433 0.10543 0.09896 -0.0326 1.0000 0.1180
-9.000 -0.3357 0.10202 0.09561 -0.0322 1.0000 0.1206
-8.750 -0.3353 0.09875 0.09243 -0.0327 1.0000 0.1231
-8.500 -0.3403 0.09554 0.08933 -0.0338 1.0000 0.1260
-8.250 -0.4073 0.09513 0.08914 -0.0372 1.0000 0.1315
-7.250 -0.4081 0.07531 0.06930 -0.0359 1.0000 0.0561
-7.000 -0.4164 0.07278 0.06686 -0.0334 1.0000 0.0542
-6.750 -0.4307 0.07072 0.06484 -0.0300 1.0000 0.0526
-6.500 -0.4170 0.06538 0.05909 -0.0335 0.9831 0.0466
-6.250 -0.3941 0.06092 0.05444 -0.0365 0.9637 0.0450
-6.000 -0.3725 0.05673 0.04995 -0.0387 0.9434 0.0433
-5.750 -0.3485 0.05244 0.04522 -0.0405 0.9256 0.0416
-5.500 -0.3221 0.04816 0.04021 -0.0416 0.9094 0.0396
-5.250 -0.2922 0.04479 0.03630 -0.0428 0.8939 0.0391
-5.000 -0.2620 0.04167 0.03270 -0.0437 0.8784 0.0390
-4.750 -0.2309 0.03897 0.02968 -0.0448 0.8628 0.0400
-4.500 -0.1994 0.03684 0.02727 -0.0457 0.8469 0.0423
-4.250 -0.1671 0.03474 0.02473 -0.0461 0.8313 0.0442
-4.000 -0.1335 0.03273 0.02226 -0.0464 0.8158 0.0457
-3.750 -0.0982 0.03087 0.01994 -0.0466 0.8008 0.0473
-3.500 -0.0634 0.02935 0.01827 -0.0472 0.7857 0.0511
-3.250 -0.0250 0.02814 0.01679 -0.0480 0.7712 0.0567
-3.000 0.0109 0.02697 0.01549 -0.0484 0.7562 0.0636
-2.750 0.0383 0.02610 0.01445 -0.0477 0.7417 0.0738
-2.500 0.0610 0.02532 0.01359 -0.0464 0.7279 0.0891
-2.250 0.2862 0.02276 0.01316 -0.0727 0.7112 0.9974
-2.000 0.3126 0.02266 0.01271 -0.0729 0.6971 1.0000
-1.750 0.3335 0.02268 0.01243 -0.0719 0.6841 1.0000
-1.500 0.3547 0.02270 0.01217 -0.0710 0.6725 1.0000
-1.250 0.3752 0.02278 0.01204 -0.0701 0.6604 1.0000
-1.000 0.3960 0.02286 0.01192 -0.0692 0.6494 1.0000
-0.750 0.4175 0.02293 0.01176 -0.0683 0.6396 1.0000
-0.500 0.4378 0.02308 0.01177 -0.0673 0.6287 1.0000
-0.250 0.4597 0.02321 0.01172 -0.0665 0.6195 1.0000
0.000 0.4809 0.02337 0.01175 -0.0657 0.6102 1.0000
0.250 0.5020 0.02356 0.01181 -0.0648 0.6013 1.0000
0.500 0.5233 0.02373 0.01186 -0.0639 0.5930 1.0000
0.750 0.5438 0.02398 0.01203 -0.0630 0.5848 1.0000
1.000 0.5647 0.02419 0.01215 -0.0620 0.5770 1.0000
1.250 0.5848 0.02447 0.01236 -0.0610 0.5694 1.0000
1.500 0.6049 0.02475 0.01258 -0.0599 0.5619 1.0000
1.750 0.6253 0.02502 0.01277 -0.0589 0.5553 1.0000
2.000 0.6437 0.02541 0.01316 -0.0576 0.5476 1.0000
2.250 0.6650 0.02564 0.01329 -0.0566 0.5420 1.0000
2.500 0.6814 0.02616 0.01387 -0.0551 0.5343 1.0000
2.750 0.7008 0.02650 0.01417 -0.0539 0.5283 1.0000
3.000 0.7189 0.02692 0.01461 -0.0525 0.5222 1.0000
3.250 0.7351 0.02744 0.01517 -0.0509 0.5153 1.0000
3.500 0.7553 0.02775 0.01543 -0.0497 0.5103 1.0000
3.750 0.7687 0.02843 0.01619 -0.0479 0.5036 1.0000
4.000 0.7850 0.02892 0.01673 -0.0462 0.4976 1.0000
4.250 0.8061 0.02919 0.01693 -0.0450 0.4931 1.0000
4.500 0.8136 0.03013 0.01804 -0.0424 0.4859 1.0000
4.750 0.8298 0.03061 0.01854 -0.0407 0.4806 1.0000
5.000 0.8465 0.03107 0.01901 -0.0390 0.4756 1.0000
5.250 0.8516 0.03207 0.02016 -0.0361 0.4690 1.0000
5.500 0.8676 0.03253 0.02068 -0.0343 0.4640 1.0000
5.750 0.8793 0.03319 0.02140 -0.0320 0.4588 1.0000
6.000 0.8808 0.03426 0.02261 -0.0285 0.4522 1.0000
6.250 0.8973 0.03468 0.02305 -0.0267 0.4476 1.0000
6.500 0.9016 0.03564 0.02413 -0.0236 0.4420 1.0000
6.750 0.9006 0.03681 0.02541 -0.0199 0.4356 1.0000
7.000 0.9211 0.03709 0.02571 -0.0187 0.4312 1.0000
7.250 0.9136 0.03874 0.02748 -0.0147 0.4245 1.0000
7.500 0.9205 0.03978 0.02860 -0.0123 0.4183 1.0000
7.750 0.9511 0.03970 0.02857 -0.0122 0.4143 1.0000
8.000 0.9226 0.04280 0.03184 -0.0072 0.4054 1.0000
8.250 0.9472 0.04301 0.03211 -0.0066 0.4005 1.0000
8.500 0.9229 0.04615 0.03535 -0.0027 0.3924 1.0000
8.750 0.9298 0.04741 0.03668 -0.0010 0.3862 1.0000
9.000 0.9367 0.04879 0.03816 0.0006 0.3803 1.0000
9.250 0.9053 0.05329 0.04269 0.0027 0.3705 1.0000
9.500 0.9297 0.05344 0.04296 0.0034 0.3660 1.0000
9.750 0.8909 0.05978 0.04933 0.0036 0.3540 1.0000
10.250 0.8872 0.06588 0.05559 0.0036 0.3379 1.0000
10.750 0.8764 0.07324 0.06308 0.0028 0.3204 1.0000
11.250 0.8443 0.08359 0.07353 0.0005 0.2993 1.0000
11.500 0.8650 0.08394 0.07402 0.0012 0.2943 1.0000
12.000 0.8718 0.08931 0.07957 0.0006 0.2793 1.0000
12.250 0.8523 0.09536 0.08566 -0.0012 0.2686 1.0000
12.500 0.8799 0.09453 0.08498 -0.0001 0.2644 1.0000
13.000 0.8878 0.09987 0.09054 -0.0009 0.2497 1.0000
13.250 0.8645 0.10696 0.09765 -0.0036 0.2388 1.0000
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Polar data table (+)
Polar graphs
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