E374 (e374-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 100,000 Max Cl/Cd: 53.23 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e374-il-100000-n5.txt Download as CSV file: xf-e374-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4672 0.07761 0.07285 -0.0445 1.0000 0.0202
-9.000 -0.4765 0.07120 0.06649 -0.0493 1.0000 0.0200
-8.750 -0.4905 0.06638 0.06167 -0.0515 1.0000 0.0198
-8.500 -0.5078 0.06270 0.05797 -0.0507 1.0000 0.0197
-8.250 -0.5221 0.05900 0.05420 -0.0494 1.0000 0.0196
-8.000 -0.5325 0.05571 0.05083 -0.0476 1.0000 0.0193
-7.750 -0.5442 0.05195 0.04689 -0.0451 1.0000 0.0194
-7.500 -0.5527 0.04864 0.04337 -0.0421 1.0000 0.0195
-7.250 -0.5610 0.04548 0.03992 -0.0385 1.0000 0.0198
-7.000 -0.5591 0.04196 0.03600 -0.0365 0.9965 0.0199
-6.750 -0.5365 0.03740 0.03082 -0.0381 0.9856 0.0200
-6.500 -0.5120 0.03360 0.02636 -0.0390 0.9747 0.0203
-6.250 -0.4861 0.03015 0.02244 -0.0399 0.9647 0.0209
-6.000 -0.4551 0.02766 0.01959 -0.0413 0.9568 0.0219
-5.750 -0.4252 0.02571 0.01735 -0.0421 0.9469 0.0232
-5.500 -0.3927 0.02424 0.01558 -0.0432 0.9383 0.0266
-5.250 -0.3606 0.02244 0.01357 -0.0442 0.9302 0.0301
-5.000 -0.3311 0.02107 0.01211 -0.0446 0.9200 0.0341
-4.750 -0.3007 0.01991 0.01076 -0.0452 0.9109 0.0419
-4.500 -0.2706 0.01892 0.00967 -0.0457 0.9017 0.0531
-4.250 -0.2438 0.01802 0.00878 -0.0457 0.8909 0.0697
-4.000 -0.2167 0.01717 0.00798 -0.0457 0.8810 0.0971
-3.750 -0.1890 0.01636 0.00735 -0.0458 0.8722 0.1490
-3.500 -0.1653 0.01559 0.00692 -0.0453 0.8614 0.2319
-3.250 -0.1425 0.01481 0.00655 -0.0447 0.8516 0.3451
-3.000 -0.1199 0.01403 0.00626 -0.0436 0.8431 0.4818
-2.750 -0.0973 0.01340 0.00624 -0.0419 0.8338 0.6425
-2.500 -0.0633 0.01327 0.00636 -0.0418 0.8266 0.7724
-2.250 -0.0265 0.01336 0.00636 -0.0426 0.8189 0.8360
-2.000 0.0123 0.01351 0.00635 -0.0440 0.8117 0.8750
-1.750 0.0529 0.01366 0.00632 -0.0459 0.8043 0.9029
-1.500 0.0956 0.01381 0.00627 -0.0484 0.7971 0.9236
-1.250 0.1395 0.01393 0.00620 -0.0514 0.7899 0.9405
-1.000 0.1836 0.01400 0.00612 -0.0546 0.7826 0.9550
-0.750 0.2283 0.01402 0.00597 -0.0581 0.7755 0.9672
-0.500 0.2713 0.01401 0.00584 -0.0614 0.7681 0.9783
-0.250 0.3137 0.01395 0.00568 -0.0647 0.7610 0.9883
0.000 0.3553 0.01389 0.00553 -0.0680 0.7535 0.9975
0.250 0.3832 0.01388 0.00544 -0.0683 0.7463 1.0000
0.500 0.4043 0.01393 0.00545 -0.0674 0.7384 1.0000
0.750 0.4263 0.01397 0.00544 -0.0665 0.7317 1.0000
1.000 0.4474 0.01405 0.00551 -0.0655 0.7237 1.0000
1.250 0.4696 0.01412 0.00553 -0.0645 0.7174 1.0000
1.500 0.4905 0.01424 0.00566 -0.0635 0.7095 1.0000
1.750 0.5129 0.01433 0.00574 -0.0625 0.7033 1.0000
2.000 0.5338 0.01448 0.00591 -0.0614 0.6953 1.0000
2.250 0.5564 0.01459 0.00600 -0.0605 0.6891 1.0000
2.500 0.5771 0.01476 0.00622 -0.0593 0.6810 1.0000
2.750 0.6000 0.01487 0.00635 -0.0584 0.6746 1.0000
3.000 0.6206 0.01505 0.00660 -0.0572 0.6657 1.0000
3.250 0.6428 0.01518 0.00676 -0.0561 0.6578 1.0000
3.500 0.6643 0.01532 0.00695 -0.0549 0.6486 1.0000
3.750 0.6853 0.01547 0.00720 -0.0536 0.6387 1.0000
4.000 0.7072 0.01558 0.00736 -0.0523 0.6288 1.0000
4.250 0.7294 0.01568 0.00750 -0.0511 0.6185 1.0000
4.500 0.7500 0.01581 0.00773 -0.0497 0.6063 1.0000
4.750 0.7709 0.01594 0.00794 -0.0483 0.5936 1.0000
5.000 0.7917 0.01604 0.00818 -0.0468 0.5797 1.0000
5.250 0.8124 0.01614 0.00836 -0.0453 0.5645 1.0000
5.500 0.8330 0.01624 0.00853 -0.0437 0.5478 1.0000
5.750 0.8521 0.01639 0.00880 -0.0419 0.5277 1.0000
6.000 0.8712 0.01653 0.00899 -0.0401 0.5049 1.0000
6.250 0.8888 0.01672 0.00924 -0.0380 0.4754 1.0000
6.500 0.9049 0.01700 0.00953 -0.0356 0.4373 1.0000
6.750 0.9185 0.01745 0.00985 -0.0330 0.3861 1.0000
7.000 0.9259 0.01829 0.01030 -0.0295 0.3149 1.0000
7.250 0.9286 0.01956 0.01107 -0.0257 0.2412 1.0000
7.500 0.9323 0.02088 0.01200 -0.0223 0.1788 1.0000
7.750 0.9388 0.02208 0.01295 -0.0193 0.1352 1.0000
8.000 0.9460 0.02325 0.01396 -0.0165 0.1022 1.0000
8.250 0.9519 0.02449 0.01506 -0.0135 0.0759 1.0000
8.500 0.9563 0.02577 0.01623 -0.0104 0.0588 1.0000
8.750 0.9602 0.02700 0.01752 -0.0071 0.0494 1.0000
9.000 0.9622 0.02843 0.01893 -0.0039 0.0443 1.0000
9.250 0.9677 0.02974 0.02040 -0.0012 0.0406 1.0000
9.500 0.9728 0.03118 0.02194 0.0013 0.0377 1.0000
9.750 0.9758 0.03288 0.02368 0.0035 0.0348 1.0000
10.000 0.9833 0.03443 0.02535 0.0054 0.0321 1.0000
10.250 0.9919 0.03598 0.02706 0.0071 0.0297 1.0000
10.500 1.0007 0.03771 0.02890 0.0086 0.0280 1.0000
10.750 1.0095 0.03953 0.03080 0.0101 0.0265 1.0000
11.000 1.0177 0.04183 0.03312 0.0114 0.0244 1.0000
11.250 1.0276 0.04366 0.03528 0.0126 0.0227 1.0000
11.500 1.0367 0.04586 0.03773 0.0138 0.0214 1.0000
11.750 1.0442 0.04835 0.04046 0.0150 0.0205 1.0000
12.000 1.0477 0.05106 0.04339 0.0161 0.0196 1.0000
12.250 1.0487 0.05376 0.04629 0.0169 0.0189 1.0000
12.500 1.0471 0.05668 0.04938 0.0176 0.0183 1.0000
12.750 1.0421 0.06006 0.05286 0.0179 0.0173 1.0000
13.000 1.0330 0.06412 0.05715 0.0180 0.0169 1.0000
13.250 1.0222 0.06820 0.06152 0.0176 0.0166 1.0000
13.500 1.0099 0.07262 0.06621 0.0167 0.0164 1.0000
13.750 0.9942 0.07775 0.07161 0.0151 0.0162 1.0000
14.000 0.9785 0.08327 0.07734 0.0131 0.0162 1.0000
14.250 0.9611 0.08939 0.08368 0.0103 0.0162 1.0000
14.500 0.9421 0.09630 0.09078 0.0067 0.0162 1.0000
14.750 0.9246 0.10353 0.09816 0.0027 0.0165 1.0000
15.000 0.9045 0.11200 0.10678 -0.0024 0.0165 1.0000
15.250 0.8865 0.12072 0.11560 -0.0076 0.0168 1.0000
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Polar data table (+)
Polar graphs
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