EPPLER 502 AIRFOIL (e502-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 502 AIRFOIL (e502-il) Reynolds number: 50,000 Max Cl/Cd: 20.98 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e502-il-50000-n5.txt Download as CSV file: xf-e502-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 502 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4458 0.11050 0.10376 -0.0501 1.0000 0.0404
-12.000 -0.4514 0.10459 0.09793 -0.0531 1.0000 0.0399
-11.750 -0.4618 0.09731 0.09070 -0.0573 1.0000 0.0393
-11.500 -0.4775 0.09025 0.08368 -0.0616 1.0000 0.0385
-11.250 -0.4990 0.08383 0.07731 -0.0650 1.0000 0.0379
-11.000 -0.5218 0.07853 0.07197 -0.0669 1.0000 0.0373
-10.750 -0.5461 0.07406 0.06745 -0.0673 1.0000 0.0368
-10.500 -0.5704 0.07051 0.06383 -0.0661 1.0000 0.0366
-10.250 -0.5959 0.06806 0.06135 -0.0631 1.0000 0.0363
-10.000 -0.6281 0.06713 0.06043 -0.0574 1.0000 0.0360
-9.750 -0.6517 0.06553 0.05870 -0.0535 0.9917 0.0358
-9.500 -0.6570 0.06190 0.05472 -0.0531 0.9768 0.0359
-9.250 -0.6555 0.05827 0.05072 -0.0528 0.9656 0.0364
-9.000 -0.6498 0.05497 0.04704 -0.0524 0.9564 0.0375
-8.750 -0.6417 0.05212 0.04379 -0.0516 0.9478 0.0389
-8.500 -0.6277 0.04900 0.04007 -0.0513 0.9414 0.0416
-8.250 -0.6142 0.04623 0.03666 -0.0499 0.9340 0.0437
-8.000 -0.5873 0.04300 0.03310 -0.0507 0.9296 0.0461
-7.750 -0.5564 0.04078 0.03065 -0.0521 0.9261 0.0519
-7.500 -0.5201 0.03840 0.02784 -0.0533 0.9221 0.0579
-7.250 -0.4773 0.03657 0.02581 -0.0557 0.9191 0.0685
-7.000 -0.4104 0.03453 0.02364 -0.0612 0.9198 0.0850
-6.750 -0.3726 0.03326 0.02231 -0.0627 0.9166 0.0991
-6.500 -0.3462 0.03206 0.02117 -0.0631 0.9126 0.1208
-6.250 -0.3350 0.03112 0.02037 -0.0612 0.9060 0.1439
-6.000 -0.3272 0.02982 0.01949 -0.0590 0.9001 0.1952
-5.750 -0.2783 0.03047 0.02256 -0.0565 0.9001 0.5656
-5.500 -0.2775 0.03114 0.02304 -0.0516 0.8927 0.6394
-5.250 -0.2869 0.03137 0.02309 -0.0458 0.8853 0.6827
-5.000 -0.2762 0.03282 0.02431 -0.0410 0.8798 0.7234
-4.750 -0.1987 0.03562 0.02660 -0.0444 0.8802 0.7733
-4.500 -0.1617 0.03624 0.02687 -0.0450 0.8766 0.7950
-4.250 -0.1273 0.03640 0.02673 -0.0461 0.8731 0.8105
-4.000 -0.0839 0.03632 0.02634 -0.0489 0.8707 0.8221
-3.750 -0.0515 0.03626 0.02602 -0.0502 0.8672 0.8328
-3.500 -0.0325 0.03632 0.02591 -0.0493 0.8621 0.8433
-3.250 -0.0057 0.03621 0.02562 -0.0498 0.8583 0.8522
-3.000 0.0274 0.03597 0.02517 -0.0515 0.8554 0.8588
-2.750 0.0403 0.03611 0.02519 -0.0498 0.8501 0.8664
-2.500 0.0630 0.03606 0.02501 -0.0499 0.8458 0.8721
-2.250 0.0916 0.03591 0.02472 -0.0509 0.8425 0.8772
-2.000 0.1001 0.03609 0.02482 -0.0485 0.8376 0.8837
-1.750 0.1234 0.03613 0.02476 -0.0487 0.8331 0.8878
-1.500 0.1461 0.03612 0.02466 -0.0488 0.8294 0.8923
-1.250 0.1601 0.03621 0.02467 -0.0472 0.8257 0.8973
-1.000 0.1751 0.03648 0.02491 -0.0461 0.8200 0.9012
-0.750 0.1962 0.03657 0.02494 -0.0459 0.8159 0.9049
-0.500 0.2185 0.03659 0.02490 -0.0457 0.8127 0.9087
-0.250 0.2187 0.03710 0.02541 -0.0420 0.8062 0.9133
0.000 0.2409 0.03724 0.02553 -0.0421 0.8019 0.9163
0.250 0.2676 0.03727 0.02552 -0.0427 0.7986 0.9191
0.500 0.2618 0.03789 0.02616 -0.0380 0.7916 0.9241
0.750 0.2795 0.03808 0.02635 -0.0371 0.7869 0.9271
1.000 0.3113 0.03810 0.02636 -0.0386 0.7839 0.9291
1.250 0.3103 0.03875 0.02705 -0.0350 0.7759 0.9333
1.500 0.3315 0.03892 0.02724 -0.0347 0.7716 0.9360
1.750 0.3304 0.03944 0.02779 -0.0307 0.7647 0.9402
2.000 0.3524 0.03972 0.02810 -0.0307 0.7590 0.9427
2.250 0.3856 0.03974 0.02817 -0.0323 0.7555 0.9444
2.500 0.3821 0.04044 0.02895 -0.0284 0.7463 0.9486
2.750 0.4105 0.04053 0.02910 -0.0290 0.7420 0.9510
3.000 0.4066 0.04119 0.02981 -0.0249 0.7328 0.9556
3.250 0.4395 0.04127 0.02998 -0.0264 0.7280 0.9572
3.500 0.4442 0.04186 0.03065 -0.0239 0.7187 0.9610
3.750 0.4766 0.04191 0.03082 -0.0251 0.7136 0.9631
4.000 0.4759 0.04254 0.03152 -0.0216 0.7034 0.9682
4.250 0.5152 0.04244 0.03158 -0.0237 0.6986 0.9697
4.500 0.5225 0.04304 0.03228 -0.0218 0.6876 0.9737
5.000 0.5688 0.04335 0.03290 -0.0214 0.6713 0.9802
5.250 0.5826 0.04381 0.03351 -0.0204 0.6600 0.9845
5.750 0.6402 0.04363 0.03374 -0.0213 0.6422 0.9910
6.000 0.6557 0.04389 0.03418 -0.0203 0.6296 0.9957
6.250 0.6733 0.04406 0.03453 -0.0195 0.6170 1.0000
6.500 0.6702 0.04420 0.03476 -0.0150 0.6046 1.0000
6.750 0.6694 0.04420 0.03486 -0.0107 0.5924 1.0000
7.000 0.6717 0.04398 0.03480 -0.0067 0.5805 1.0000
7.250 0.6915 0.04299 0.03398 -0.0043 0.5709 1.0000
7.500 0.6854 0.04288 0.03395 0.0008 0.5572 1.0000
7.750 0.6829 0.04262 0.03377 0.0054 0.5433 1.0000
8.000 0.6865 0.04221 0.03345 0.0094 0.5292 1.0000
8.250 0.6922 0.04190 0.03324 0.0128 0.5133 1.0000
8.500 0.6970 0.04195 0.03340 0.0158 0.4947 1.0000
8.750 0.7149 0.04121 0.03288 0.0180 0.4764 1.0000
9.000 0.7373 0.04021 0.03204 0.0200 0.4559 1.0000
9.250 0.7618 0.03907 0.03104 0.0220 0.4296 1.0000
9.500 0.7810 0.03854 0.03054 0.0241 0.3961 1.0000
9.750 0.7998 0.03813 0.03000 0.0263 0.3556 1.0000
10.000 0.8086 0.03874 0.03038 0.0286 0.3144 1.0000
10.250 0.8112 0.04007 0.03150 0.0307 0.2765 1.0000
10.500 0.8118 0.04172 0.03298 0.0326 0.2421 1.0000
10.750 0.8115 0.04362 0.03470 0.0342 0.2112 1.0000
11.000 0.8112 0.04567 0.03660 0.0357 0.1837 1.0000
11.250 0.8104 0.04787 0.03859 0.0369 0.1604 1.0000
11.500 0.8119 0.05009 0.04075 0.0380 0.1385 1.0000
11.750 0.8128 0.05241 0.04295 0.0389 0.1210 1.0000
12.000 0.8159 0.05466 0.04512 0.0397 0.1067 1.0000
12.250 0.8197 0.05697 0.04740 0.0404 0.0936 1.0000
12.500 0.8251 0.05926 0.04975 0.0410 0.0822 1.0000
12.750 0.8322 0.06153 0.05213 0.0417 0.0728 1.0000
13.000 0.8388 0.06384 0.05443 0.0422 0.0656 1.0000
13.250 0.8476 0.06618 0.05698 0.0427 0.0589 1.0000
13.500 0.8547 0.06870 0.05960 0.0431 0.0536 1.0000
13.750 0.8603 0.07167 0.06289 0.0433 0.0489 1.0000
14.000 0.8652 0.07448 0.06577 0.0434 0.0456 1.0000
14.250 0.8675 0.07788 0.06933 0.0433 0.0430 1.0000
14.500 0.8610 0.08225 0.07404 0.0426 0.0413 1.0000
14.750 0.8524 0.08711 0.07920 0.0414 0.0401 1.0000
15.000 0.8401 0.09250 0.08484 0.0397 0.0391 1.0000
15.250 0.8252 0.09859 0.09116 0.0372 0.0384 1.0000
15.500 0.8080 0.10552 0.09831 0.0340 0.0384 1.0000
15.750 0.7860 0.11395 0.10694 0.0296 0.0387 1.0000
16.000 0.7616 0.12392 0.11708 0.0241 0.0402 1.0000
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