E374 (e374-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 100,000 Max Cl/Cd: 53.8 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e374-il-100000.txt Download as CSV file: xf-e374-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4265 0.10137 0.09654 -0.0299 1.0000 0.1034
-9.250 -0.4433 0.09818 0.09346 -0.0347 1.0000 0.1070
-9.000 -0.4751 0.09452 0.08996 -0.0423 1.0000 0.1078
-8.750 -0.4334 0.09032 0.08569 -0.0342 1.0000 0.1122
-8.500 -0.4341 0.08702 0.08242 -0.0350 1.0000 0.1171
-8.250 -0.4608 0.08329 0.07886 -0.0398 1.0000 0.1205
-8.000 -0.5026 0.08063 0.07621 -0.0428 1.0000 0.1217
-7.750 -0.4728 0.07612 0.07183 -0.0389 1.0000 0.1255
-7.500 -0.4740 0.07327 0.06900 -0.0378 1.0000 0.1296
-7.250 -0.5223 0.07166 0.06724 -0.0389 1.0000 0.1357
-7.000 -0.5063 0.06695 0.06274 -0.0365 1.0000 0.1385
-6.750 -0.5054 0.06471 0.06055 -0.0334 1.0000 0.1423
-6.500 -0.5517 0.06485 0.06040 -0.0295 1.0000 0.1503
-5.500 -0.5369 0.04079 0.03468 -0.0233 0.9947 0.0642
-5.250 -0.5049 0.03559 0.02823 -0.0239 0.9870 0.0547
-5.000 -0.4720 0.03177 0.02385 -0.0256 0.9804 0.0551
-4.750 -0.4378 0.02910 0.02102 -0.0277 0.9736 0.0595
-4.500 -0.4008 0.02668 0.01813 -0.0291 0.9672 0.0615
-4.250 -0.3621 0.02504 0.01601 -0.0306 0.9601 0.0674
-4.000 -0.3245 0.02313 0.01408 -0.0326 0.9543 0.0792
-3.750 -0.2910 0.02157 0.01262 -0.0338 0.9468 0.0983
-3.500 -0.2565 0.02010 0.01139 -0.0351 0.9404 0.1401
-3.250 -0.2313 0.01836 0.01047 -0.0351 0.9323 0.2612
-3.000 -0.2128 0.01635 0.01035 -0.0332 0.9257 0.6162
-2.750 -0.1549 0.01658 0.01109 -0.0351 0.9243 0.8833
-2.500 -0.0317 0.01747 0.01143 -0.0505 0.9316 0.9536
-2.250 0.0826 0.01726 0.01077 -0.0669 0.9365 0.9877
-2.000 0.1542 0.01673 0.00995 -0.0763 0.9337 1.0000
-1.750 0.1947 0.01646 0.00951 -0.0797 0.9252 1.0000
-1.500 0.2322 0.01623 0.00913 -0.0823 0.9162 1.0000
-1.250 0.2613 0.01615 0.00892 -0.0833 0.9053 1.0000
-1.000 0.2912 0.01607 0.00873 -0.0843 0.8957 1.0000
-0.750 0.3212 0.01599 0.00855 -0.0851 0.8866 1.0000
-0.500 0.3416 0.01611 0.00860 -0.0843 0.8753 1.0000
-0.250 0.3636 0.01622 0.00864 -0.0836 0.8654 1.0000
0.000 0.3895 0.01623 0.00857 -0.0834 0.8573 1.0000
0.250 0.4064 0.01648 0.00880 -0.0818 0.8466 1.0000
0.500 0.4262 0.01668 0.00896 -0.0806 0.8373 1.0000
0.750 0.4492 0.01679 0.00902 -0.0798 0.8293 1.0000
1.000 0.4656 0.01713 0.00936 -0.0781 0.8193 1.0000
1.250 0.4873 0.01732 0.00952 -0.0771 0.8117 1.0000
1.500 0.5058 0.01761 0.00981 -0.0756 0.8025 1.0000
1.750 0.5235 0.01797 0.01020 -0.0740 0.7936 1.0000
2.000 0.5466 0.01811 0.01034 -0.0729 0.7863 1.0000
2.250 0.5621 0.01857 0.01082 -0.0711 0.7764 1.0000
2.500 0.5845 0.01876 0.01103 -0.0699 0.7690 1.0000
2.750 0.6031 0.01909 0.01141 -0.0683 0.7595 1.0000
3.000 0.6206 0.01947 0.01184 -0.0665 0.7497 1.0000
3.250 0.6472 0.01944 0.01182 -0.0656 0.7424 1.0000
3.500 0.6634 0.01984 0.01229 -0.0636 0.7312 1.0000
3.750 0.6824 0.02012 0.01267 -0.0618 0.7207 1.0000
4.000 0.7072 0.02010 0.01269 -0.0606 0.7116 1.0000
4.250 0.7296 0.02015 0.01281 -0.0591 0.7008 1.0000
4.500 0.7491 0.02032 0.01307 -0.0572 0.6887 1.0000
4.750 0.7705 0.02037 0.01323 -0.0555 0.6765 1.0000
5.000 0.7933 0.02029 0.01324 -0.0538 0.6637 1.0000
5.250 0.8165 0.02013 0.01316 -0.0522 0.6501 1.0000
5.500 0.8398 0.01992 0.01305 -0.0504 0.6353 1.0000
5.750 0.8632 0.01963 0.01285 -0.0487 0.6192 1.0000
6.000 0.8878 0.01920 0.01252 -0.0469 0.6015 1.0000
6.250 0.9083 0.01887 0.01231 -0.0446 0.5802 1.0000
6.500 0.9304 0.01839 0.01189 -0.0424 0.5561 1.0000
6.750 0.9467 0.01810 0.01171 -0.0395 0.5245 1.0000
7.000 0.9598 0.01784 0.01147 -0.0359 0.4771 1.0000
7.250 0.9678 0.01803 0.01143 -0.0317 0.4070 1.0000
7.500 0.9688 0.01898 0.01184 -0.0269 0.3162 1.0000
7.750 0.9630 0.02067 0.01289 -0.0218 0.2271 1.0000
8.000 0.9540 0.02278 0.01437 -0.0165 0.1550 1.0000
8.250 0.9459 0.02495 0.01607 -0.0114 0.1126 1.0000
8.500 0.9443 0.02673 0.01767 -0.0070 0.0904 1.0000
8.750 0.9490 0.02836 0.01920 -0.0038 0.0775 1.0000
9.000 0.9639 0.03034 0.02108 -0.0019 0.0692 1.0000
9.250 0.9859 0.03221 0.02291 -0.0012 0.0618 1.0000
9.500 1.0158 0.03465 0.02554 -0.0015 0.0555 1.0000
9.750 1.0454 0.03725 0.02832 -0.0016 0.0520 1.0000
10.000 1.0768 0.04165 0.03273 -0.0029 0.0480 1.0000
10.250 1.0829 0.04339 0.03494 0.0001 0.0462 1.0000
10.500 1.0915 0.04648 0.03846 0.0024 0.0454 1.0000
10.750 1.0952 0.04980 0.04218 0.0049 0.0453 1.0000
11.000 1.0924 0.05324 0.04600 0.0079 0.0453 1.0000
11.250 1.0845 0.05657 0.04964 0.0112 0.0457 1.0000
11.500 1.0731 0.05991 0.05325 0.0143 0.0460 1.0000
11.750 1.0578 0.06324 0.05684 0.0170 0.0460 1.0000
12.000 1.0422 0.06701 0.06083 0.0187 0.0464 1.0000
12.250 1.0265 0.07123 0.06525 0.0197 0.0469 1.0000
12.500 1.0081 0.07576 0.06995 0.0200 0.0472 1.0000
12.750 0.9878 0.08038 0.07475 0.0195 0.0474 1.0000
13.000 0.9809 0.08669 0.08116 0.0188 0.0482 1.0000
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Polar data table (+)
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