E374 (e374-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 50,000 Max Cl/Cd: 34.04 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e374-il-50000-n5.txt Download as CSV file: xf-e374-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E374
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 -0.4534 0.10064 0.09370 -0.0366 1.0000 0.0393
-9.750 -0.4537 0.09629 0.08942 -0.0383 1.0000 0.0392
-9.500 -0.4565 0.09148 0.08468 -0.0408 1.0000 0.0391
-9.250 -0.4575 0.08723 0.08050 -0.0425 1.0000 0.0387
-9.000 -0.4632 0.08208 0.07541 -0.0458 1.0000 0.0386
-8.750 -0.4713 0.07760 0.07100 -0.0478 1.0000 0.0382
-8.500 -0.4833 0.07375 0.06718 -0.0483 1.0000 0.0380
-8.250 -0.4965 0.06994 0.06338 -0.0481 1.0000 0.0379
-8.000 -0.5065 0.06633 0.05974 -0.0474 1.0000 0.0376
-7.750 -0.5174 0.06263 0.05593 -0.0461 1.0000 0.0378
-7.500 -0.5248 0.05922 0.05240 -0.0443 1.0000 0.0379
-7.250 -0.5315 0.05582 0.04878 -0.0420 1.0000 0.0382
-7.000 -0.5359 0.05264 0.04534 -0.0394 1.0000 0.0385
-6.750 -0.5388 0.04965 0.04202 -0.0365 1.0000 0.0390
-6.500 -0.5397 0.04690 0.03890 -0.0333 1.0000 0.0394
-6.250 -0.5388 0.04413 0.03591 -0.0303 1.0000 0.0400
-6.000 -0.5352 0.04166 0.03313 -0.0275 1.0000 0.0406
-5.750 -0.5291 0.03942 0.03062 -0.0249 1.0000 0.0413
-5.500 -0.5138 0.03705 0.02790 -0.0237 0.9974 0.0426
-5.250 -0.4814 0.03440 0.02479 -0.0254 0.9888 0.0456
-5.000 -0.4468 0.03213 0.02184 -0.0267 0.9805 0.0521
-4.750 -0.4136 0.03005 0.01965 -0.0282 0.9724 0.0581
-4.500 -0.3801 0.02838 0.01775 -0.0294 0.9641 0.0685
-4.250 -0.3436 0.02682 0.01598 -0.0310 0.9572 0.0821
-4.000 -0.3113 0.02560 0.01463 -0.0320 0.9481 0.1054
-3.750 -0.2765 0.02423 0.01342 -0.0338 0.9409 0.1485
-3.500 -0.2470 0.02283 0.01249 -0.0350 0.9321 0.2338
-3.250 -0.2236 0.02141 0.01192 -0.0349 0.9231 0.3930
-3.000 -0.1966 0.02023 0.01197 -0.0332 0.9170 0.6581
-2.750 -0.1316 0.02053 0.01232 -0.0369 0.9162 0.8610
-2.500 -0.0482 0.02096 0.01220 -0.0459 0.9167 0.9354
-2.250 0.0354 0.02089 0.01159 -0.0566 0.9165 0.9774
-2.000 0.1045 0.02055 0.01086 -0.0655 0.9133 1.0000
-1.750 0.1354 0.02045 0.01050 -0.0670 0.9022 1.0000
-1.500 0.1631 0.02041 0.01026 -0.0677 0.8908 1.0000
-1.250 0.1905 0.02040 0.01006 -0.0683 0.8801 1.0000
-1.000 0.2197 0.02038 0.00987 -0.0691 0.8709 1.0000
-0.750 0.2438 0.02045 0.00978 -0.0690 0.8603 1.0000
-0.500 0.2658 0.02057 0.00979 -0.0684 0.8498 1.0000
-0.250 0.2901 0.02067 0.00977 -0.0681 0.8407 1.0000
0.000 0.3137 0.02080 0.00980 -0.0677 0.8316 1.0000
0.250 0.3328 0.02104 0.00996 -0.0665 0.8215 1.0000
0.500 0.3563 0.02121 0.01005 -0.0659 0.8133 1.0000
0.750 0.3774 0.02145 0.01025 -0.0650 0.8043 1.0000
1.000 0.3970 0.02175 0.01051 -0.0639 0.7951 1.0000
1.250 0.4225 0.02192 0.01065 -0.0635 0.7880 1.0000
1.500 0.4392 0.02232 0.01104 -0.0619 0.7782 1.0000
1.750 0.4618 0.02259 0.01130 -0.0611 0.7706 1.0000
2.000 0.4820 0.02293 0.01167 -0.0600 0.7620 1.0000
2.250 0.5007 0.02333 0.01209 -0.0586 0.7532 1.0000
2.500 0.5252 0.02357 0.01236 -0.0580 0.7461 1.0000
2.750 0.5413 0.02407 0.01291 -0.0562 0.7364 1.0000
3.000 0.5652 0.02434 0.01325 -0.0555 0.7291 1.0000
3.250 0.5837 0.02478 0.01376 -0.0540 0.7197 1.0000
3.500 0.6018 0.02523 0.01429 -0.0525 0.7102 1.0000
3.750 0.6290 0.02536 0.01451 -0.0520 0.7028 1.0000
4.000 0.6445 0.02589 0.01513 -0.0500 0.6917 1.0000
4.250 0.6631 0.02630 0.01570 -0.0484 0.6811 1.0000
4.500 0.6864 0.02650 0.01602 -0.0472 0.6714 1.0000
4.750 0.7111 0.02660 0.01626 -0.0462 0.6610 1.0000
5.000 0.7296 0.02692 0.01673 -0.0443 0.6484 1.0000
5.250 0.7495 0.02714 0.01716 -0.0426 0.6354 1.0000
5.500 0.7705 0.02726 0.01745 -0.0409 0.6216 1.0000
5.750 0.7924 0.02727 0.01764 -0.0392 0.6070 1.0000
6.000 0.8158 0.02711 0.01767 -0.0375 0.5912 1.0000
6.250 0.8336 0.02716 0.01791 -0.0352 0.5725 1.0000
6.500 0.8526 0.02704 0.01799 -0.0328 0.5518 1.0000
6.750 0.8699 0.02694 0.01815 -0.0302 0.5283 1.0000
7.000 0.8860 0.02682 0.01821 -0.0274 0.5006 1.0000
7.250 0.9009 0.02671 0.01822 -0.0244 0.4661 1.0000
7.500 0.9122 0.02680 0.01832 -0.0209 0.4217 1.0000
7.750 0.9198 0.02720 0.01855 -0.0172 0.3633 1.0000
8.000 0.9222 0.02816 0.01911 -0.0132 0.3002 1.0000
8.250 0.9186 0.02970 0.02024 -0.0091 0.2457 1.0000
8.500 0.9114 0.03153 0.02172 -0.0051 0.2015 1.0000
8.750 0.9054 0.03358 0.02348 -0.0018 0.1630 1.0000
9.000 0.9006 0.03583 0.02545 0.0008 0.1333 1.0000
9.250 0.8991 0.03808 0.02756 0.0029 0.1096 1.0000
9.500 0.8987 0.04038 0.02980 0.0048 0.0940 1.0000
9.750 0.9013 0.04264 0.03202 0.0065 0.0815 1.0000
10.000 0.9093 0.04465 0.03412 0.0082 0.0721 1.0000
10.250 0.9185 0.04663 0.03618 0.0096 0.0643 1.0000
10.500 0.9277 0.04862 0.03820 0.0108 0.0578 1.0000
10.750 0.9519 0.05036 0.04021 0.0123 0.0527 1.0000
11.000 0.9762 0.05252 0.04264 0.0136 0.0487 1.0000
11.250 0.9933 0.05501 0.04513 0.0143 0.0452 1.0000
11.500 0.9980 0.05803 0.04858 0.0155 0.0427 1.0000
11.750 0.9988 0.06127 0.05219 0.0164 0.0407 1.0000
12.000 0.9970 0.06486 0.05616 0.0171 0.0394 1.0000
12.250 0.9914 0.06876 0.06036 0.0174 0.0388 1.0000
12.500 0.9814 0.07308 0.06495 0.0173 0.0383 1.0000
12.750 0.9677 0.07788 0.07001 0.0165 0.0380 1.0000
13.000 0.9508 0.08321 0.07558 0.0150 0.0379 1.0000
13.250 0.9302 0.08941 0.08200 0.0125 0.0382 1.0000
13.500 0.9071 0.09651 0.08924 0.0089 0.0387 1.0000
13.750 0.8812 0.10492 0.09780 0.0041 0.0393 1.0000
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Polar data table (+)
Polar graphs
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