E374 (e374-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 200,000 Max Cl/Cd: 71.85 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e374-il-200000-n5.txt Download as CSV file: xf-e374-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4570 0.08716 0.08368 -0.0357 1.0000 0.0113
-9.500 -0.4658 0.08130 0.07788 -0.0386 1.0000 0.0110
-9.250 -0.4768 0.07510 0.07175 -0.0422 1.0000 0.0107
-9.000 -0.4962 0.06680 0.06352 -0.0490 1.0000 0.0104
-8.750 -0.5388 0.05678 0.05341 -0.0517 1.0000 0.0099
-8.500 -0.5739 0.04884 0.04520 -0.0492 1.0000 0.0095
-8.250 -0.5907 0.04442 0.04051 -0.0459 1.0000 0.0093
-8.000 -0.6003 0.04109 0.03691 -0.0423 1.0000 0.0092
-7.750 -0.5878 0.03554 0.03077 -0.0438 0.9884 0.0093
-7.500 -0.5702 0.03131 0.02598 -0.0446 0.9766 0.0094
-7.250 -0.5486 0.02813 0.02236 -0.0451 0.9647 0.0097
-7.000 -0.5226 0.02587 0.01975 -0.0459 0.9536 0.0102
-6.750 -0.4945 0.02363 0.01712 -0.0466 0.9430 0.0105
-6.500 -0.4648 0.02217 0.01537 -0.0475 0.9314 0.0116
-6.250 -0.4339 0.02084 0.01372 -0.0483 0.9197 0.0132
-6.000 -0.4034 0.01937 0.01196 -0.0489 0.9077 0.0140
-5.750 -0.3754 0.01787 0.01027 -0.0492 0.8947 0.0147
-5.500 -0.3485 0.01682 0.00911 -0.0492 0.8811 0.0160
-5.250 -0.3223 0.01602 0.00818 -0.0489 0.8677 0.0180
-5.000 -0.2973 0.01530 0.00731 -0.0484 0.8546 0.0214
-4.750 -0.2725 0.01475 0.00664 -0.0478 0.8423 0.0265
-4.500 -0.2487 0.01412 0.00592 -0.0470 0.8305 0.0337
-4.250 -0.2245 0.01367 0.00543 -0.0463 0.8190 0.0465
-4.000 -0.2004 0.01323 0.00498 -0.0457 0.8085 0.0658
-3.750 -0.1761 0.01283 0.00459 -0.0450 0.7989 0.0911
-3.500 -0.1524 0.01241 0.00427 -0.0443 0.7894 0.1306
-3.250 -0.1292 0.01197 0.00398 -0.0436 0.7804 0.1860
-3.000 -0.1067 0.01148 0.00373 -0.0428 0.7723 0.2638
-2.750 -0.0852 0.01098 0.00353 -0.0418 0.7638 0.3552
-2.500 -0.0644 0.01049 0.00335 -0.0405 0.7562 0.4536
-2.250 -0.0447 0.01000 0.00322 -0.0389 0.7486 0.5619
-2.000 -0.0247 0.00958 0.00322 -0.0369 0.7417 0.6857
-1.750 0.0004 0.00943 0.00328 -0.0358 0.7346 0.7734
-1.500 0.0291 0.00942 0.00330 -0.0355 0.7284 0.8230
-1.250 0.0597 0.00947 0.00330 -0.0356 0.7216 0.8578
-1.000 0.0929 0.00956 0.00331 -0.0364 0.7157 0.8833
-0.750 0.1275 0.00965 0.00334 -0.0376 0.7090 0.9021
-0.500 0.1634 0.00976 0.00334 -0.0390 0.7033 0.9172
-0.250 0.1987 0.00986 0.00339 -0.0405 0.6968 0.9304
0.000 0.2331 0.00998 0.00342 -0.0417 0.6908 0.9422
0.250 0.2740 0.01008 0.00346 -0.0444 0.6848 0.9493
0.500 0.3097 0.01018 0.00349 -0.0461 0.6786 0.9581
0.750 0.3482 0.01026 0.00351 -0.0483 0.6730 0.9653
1.000 0.3835 0.01032 0.00356 -0.0501 0.6664 0.9722
1.250 0.4199 0.01037 0.00355 -0.0520 0.6608 0.9776
1.500 0.4531 0.01042 0.00360 -0.0533 0.6541 0.9835
1.750 0.4890 0.01043 0.00360 -0.0553 0.6481 0.9875
2.000 0.5230 0.01046 0.00364 -0.0568 0.6414 0.9920
2.250 0.5569 0.01049 0.00366 -0.0583 0.6343 0.9960
2.500 0.5912 0.01051 0.00370 -0.0600 0.6261 0.9998
2.750 0.6139 0.01056 0.00374 -0.0591 0.6182 1.0000
3.000 0.6356 0.01060 0.00383 -0.0580 0.6084 1.0000
3.250 0.6575 0.01066 0.00391 -0.0569 0.5989 1.0000
3.500 0.6794 0.01074 0.00400 -0.0558 0.5895 1.0000
3.750 0.7011 0.01081 0.00412 -0.0547 0.5786 1.0000
4.000 0.7228 0.01090 0.00424 -0.0536 0.5670 1.0000
4.250 0.7444 0.01099 0.00436 -0.0524 0.5542 1.0000
4.500 0.7658 0.01110 0.00450 -0.0511 0.5403 1.0000
4.750 0.7870 0.01123 0.00468 -0.0499 0.5251 1.0000
5.000 0.8078 0.01138 0.00484 -0.0485 0.5077 1.0000
5.250 0.8280 0.01156 0.00502 -0.0470 0.4849 1.0000
5.500 0.8471 0.01179 0.00522 -0.0454 0.4563 1.0000
5.750 0.8642 0.01213 0.00544 -0.0434 0.4161 1.0000
6.000 0.8772 0.01271 0.00576 -0.0407 0.3567 1.0000
6.250 0.8857 0.01361 0.00626 -0.0375 0.2840 1.0000
6.500 0.8949 0.01455 0.00691 -0.0345 0.2220 1.0000
6.750 0.9050 0.01545 0.00754 -0.0318 0.1712 1.0000
7.000 0.9164 0.01627 0.00817 -0.0292 0.1320 1.0000
7.250 0.9281 0.01709 0.00883 -0.0267 0.0984 1.0000
7.500 0.9403 0.01788 0.00950 -0.0244 0.0733 1.0000
7.750 0.9518 0.01871 0.01024 -0.0219 0.0532 1.0000
8.000 0.9630 0.01954 0.01105 -0.0194 0.0399 1.0000
8.250 0.9734 0.02041 0.01192 -0.0167 0.0329 1.0000
8.500 0.9843 0.02119 0.01282 -0.0142 0.0287 1.0000
8.750 0.9907 0.02211 0.01377 -0.0110 0.0256 1.0000
9.000 0.9979 0.02302 0.01477 -0.0080 0.0235 1.0000
9.250 1.0058 0.02397 0.01584 -0.0053 0.0223 1.0000
9.500 1.0137 0.02498 0.01696 -0.0029 0.0207 1.0000
9.750 1.0211 0.02611 0.01817 -0.0007 0.0192 1.0000
10.000 1.0243 0.02761 0.01971 0.0017 0.0175 1.0000
10.250 1.0295 0.02910 0.02130 0.0038 0.0166 1.0000
10.500 1.0373 0.03049 0.02284 0.0055 0.0158 1.0000
10.750 1.0448 0.03198 0.02448 0.0071 0.0148 1.0000
11.000 1.0527 0.03342 0.02602 0.0084 0.0135 1.0000
11.250 1.0593 0.03500 0.02768 0.0096 0.0125 1.0000
11.500 1.0618 0.03711 0.02987 0.0110 0.0117 1.0000
11.750 1.0665 0.03926 0.03214 0.0123 0.0112 1.0000
12.000 1.0730 0.04120 0.03429 0.0134 0.0105 1.0000
12.250 1.0781 0.04339 0.03666 0.0145 0.0102 1.0000
12.500 1.0816 0.04581 0.03928 0.0155 0.0098 1.0000
12.750 1.0826 0.04850 0.04217 0.0163 0.0093 1.0000
13.000 1.0825 0.05130 0.04518 0.0168 0.0090 1.0000
13.250 1.0803 0.05438 0.04845 0.0171 0.0087 1.0000
13.500 1.0779 0.05733 0.05156 0.0170 0.0084 1.0000
13.750 1.0731 0.06072 0.05510 0.0167 0.0081 1.0000
14.000 1.0676 0.06429 0.05882 0.0160 0.0080 1.0000
14.250 1.0616 0.06798 0.06265 0.0150 0.0077 1.0000
14.500 1.0512 0.07261 0.06744 0.0137 0.0075 1.0000
15.000 1.0254 0.08355 0.07877 0.0096 0.0074 1.0000
15.250 1.0098 0.08996 0.08536 0.0065 0.0073 1.0000
15.750 0.9793 0.10405 0.09982 -0.0011 0.0073 1.0000
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Polar data table (+)
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