E374 (e374-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 500,000 Max Cl/Cd: 103.2 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e374-il-500000.txt Download as CSV file: xf-e374-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4462 0.08618 0.08399 -0.0360 1.0000 0.0190
-9.250 -0.4495 0.08179 0.07963 -0.0382 1.0000 0.0191
-9.000 -0.4558 0.07690 0.07477 -0.0410 1.0000 0.0195
-8.750 -0.4670 0.07123 0.06916 -0.0452 1.0000 0.0193
-8.500 -0.4900 0.06523 0.06317 -0.0493 1.0000 0.0192
-8.250 -0.5094 0.06109 0.05899 -0.0483 1.0000 0.0193
-8.000 -0.5238 0.05697 0.05480 -0.0470 1.0000 0.0193
-7.750 -0.5375 0.05346 0.05121 -0.0442 1.0000 0.0197
-7.500 -0.5202 0.04630 0.04373 -0.0490 0.9927 0.0207
-7.250 -0.4916 0.04281 0.03973 -0.0515 0.9849 0.0225
-7.000 -0.5114 0.02297 0.01818 -0.0488 0.9675 0.0116
-6.750 -0.4825 0.02046 0.01529 -0.0495 0.9576 0.0115
-6.500 -0.4544 0.01804 0.01262 -0.0502 0.9455 0.0123
-6.250 -0.4233 0.01645 0.01080 -0.0511 0.9321 0.0126
-6.000 -0.3937 0.01540 0.00959 -0.0515 0.9159 0.0133
-5.750 -0.3681 0.01443 0.00843 -0.0510 0.8976 0.0138
-5.500 -0.3430 0.01401 0.00787 -0.0504 0.8794 0.0152
-5.250 -0.3183 0.01362 0.00732 -0.0496 0.8629 0.0159
-5.000 -0.2995 0.01220 0.00572 -0.0478 0.8477 0.0173
-4.750 -0.2766 0.01166 0.00510 -0.0468 0.8342 0.0195
-4.500 -0.2525 0.01128 0.00459 -0.0460 0.8219 0.0222
-4.250 -0.2297 0.01068 0.00390 -0.0449 0.8108 0.0291
-4.000 -0.2055 0.01031 0.00348 -0.0441 0.8003 0.0413
-3.750 -0.1817 0.00987 0.00311 -0.0434 0.7902 0.0680
-3.500 -0.1580 0.00946 0.00286 -0.0427 0.7812 0.1135
-3.250 -0.1343 0.00908 0.00265 -0.0421 0.7725 0.1710
-3.000 -0.1108 0.00867 0.00246 -0.0414 0.7640 0.2438
-2.750 -0.0878 0.00826 0.00229 -0.0407 0.7567 0.3298
-2.500 -0.0659 0.00777 0.00216 -0.0397 0.7487 0.4348
-2.250 -0.0475 0.00716 0.00204 -0.0380 0.7419 0.5821
-2.000 -0.0288 0.00669 0.00202 -0.0359 0.7345 0.7125
-1.750 -0.0056 0.00655 0.00202 -0.0346 0.7283 0.7813
-1.500 0.0194 0.00648 0.00204 -0.0338 0.7214 0.8257
-1.250 0.0455 0.00648 0.00203 -0.0331 0.7153 0.8573
-1.000 0.0723 0.00649 0.00206 -0.0326 0.7091 0.8849
-0.750 0.1016 0.00654 0.00210 -0.0327 0.7029 0.9047
-0.500 0.1322 0.00663 0.00214 -0.0330 0.6973 0.9204
-0.250 0.1645 0.00673 0.00220 -0.0338 0.6910 0.9334
0.000 0.1964 0.00686 0.00225 -0.0345 0.6855 0.9440
0.250 0.2327 0.00698 0.00235 -0.0361 0.6794 0.9513
0.500 0.2682 0.00710 0.00242 -0.0377 0.6737 0.9582
0.750 0.3102 0.00723 0.00249 -0.0407 0.6679 0.9619
1.000 0.3464 0.00733 0.00257 -0.0425 0.6617 0.9680
1.250 0.3848 0.00745 0.00261 -0.0448 0.6561 0.9721
1.500 0.4261 0.00750 0.00267 -0.0478 0.6491 0.9758
1.750 0.4630 0.00760 0.00271 -0.0498 0.6424 0.9811
2.000 0.5007 0.00762 0.00276 -0.0520 0.6342 0.9849
2.250 0.5393 0.00766 0.00275 -0.0545 0.6265 0.9880
2.500 0.5758 0.00766 0.00276 -0.0565 0.6176 0.9917
2.750 0.6110 0.00768 0.00279 -0.0583 0.6094 0.9949
3.000 0.6474 0.00767 0.00276 -0.0604 0.6005 0.9976
3.250 0.6819 0.00764 0.00276 -0.0620 0.5903 1.0000
3.500 0.7038 0.00767 0.00280 -0.0610 0.5808 1.0000
3.750 0.7257 0.00771 0.00283 -0.0599 0.5716 1.0000
4.000 0.7477 0.00773 0.00289 -0.0589 0.5606 1.0000
4.250 0.7696 0.00778 0.00295 -0.0578 0.5484 1.0000
4.500 0.7909 0.00785 0.00302 -0.0566 0.5328 1.0000
4.750 0.8119 0.00795 0.00310 -0.0553 0.5151 1.0000
5.000 0.8328 0.00807 0.00321 -0.0540 0.4932 1.0000
5.250 0.8520 0.00829 0.00334 -0.0524 0.4614 1.0000
5.500 0.8706 0.00858 0.00353 -0.0507 0.4244 1.0000
5.750 0.8861 0.00908 0.00380 -0.0485 0.3688 1.0000
6.000 0.8980 0.00984 0.00421 -0.0458 0.2978 1.0000
6.250 0.9106 0.01059 0.00468 -0.0433 0.2386 1.0000
6.500 0.9237 0.01130 0.00515 -0.0408 0.1892 1.0000
6.750 0.9371 0.01200 0.00564 -0.0384 0.1455 1.0000
7.000 0.9496 0.01274 0.00618 -0.0359 0.1042 1.0000
7.250 0.9598 0.01361 0.00680 -0.0330 0.0626 1.0000
7.500 0.9692 0.01454 0.00755 -0.0298 0.0342 1.0000
7.750 0.9812 0.01529 0.00829 -0.0271 0.0269 1.0000
8.000 0.9965 0.01582 0.00888 -0.0249 0.0240 1.0000
8.250 1.0086 0.01652 0.00961 -0.0223 0.0213 1.0000
8.500 1.0153 0.01751 0.01069 -0.0188 0.0194 1.0000
8.750 1.0282 0.01810 0.01137 -0.0164 0.0184 1.0000
9.000 1.0383 0.01870 0.01203 -0.0135 0.0170 1.0000
9.250 1.0464 0.01942 0.01280 -0.0104 0.0158 1.0000
9.500 1.0494 0.02052 0.01395 -0.0068 0.0145 1.0000
9.750 1.0437 0.02241 0.01596 -0.0024 0.0136 1.0000
10.000 1.0548 0.02329 0.01693 -0.0004 0.0133 1.0000
10.250 1.0655 0.02425 0.01798 0.0015 0.0125 1.0000
10.500 1.0734 0.02556 0.01939 0.0036 0.0120 1.0000
10.750 1.0824 0.02682 0.02073 0.0054 0.0115 1.0000
11.000 1.0915 0.02805 0.02202 0.0070 0.0107 1.0000
11.250 1.0989 0.02951 0.02356 0.0086 0.0102 1.0000
11.500 1.1043 0.03150 0.02563 0.0103 0.0097 1.0000
11.750 1.1085 0.03382 0.02815 0.0121 0.0090 1.0000
12.000 1.1159 0.03551 0.02999 0.0134 0.0088 1.0000
12.250 1.1216 0.03741 0.03205 0.0147 0.0086 1.0000
12.500 1.1248 0.03975 0.03457 0.0160 0.0084 1.0000
12.750 1.1266 0.04205 0.03704 0.0171 0.0081 1.0000
13.000 1.1265 0.04461 0.03978 0.0180 0.0079 1.0000
13.250 1.1239 0.04743 0.04278 0.0187 0.0077 1.0000
13.500 1.1160 0.05118 0.04677 0.0193 0.0078 1.0000
13.750 1.1071 0.05496 0.05074 0.0195 0.0077 1.0000
14.000 1.0973 0.05893 0.05490 0.0192 0.0076 1.0000
14.250 1.0849 0.06338 0.05955 0.0184 0.0076 1.0000
14.500 1.0677 0.06884 0.06522 0.0170 0.0076 1.0000
14.750 1.0482 0.07498 0.07158 0.0149 0.0077 1.0000
15.000 1.0320 0.08101 0.07777 0.0122 0.0076 1.0000
15.250 1.0084 0.08891 0.08588 0.0084 0.0078 1.0000
15.500 0.9850 0.09741 0.09456 0.0038 0.0081 1.0000
15.750 0.9682 0.10530 0.10259 -0.0009 0.0078 1.0000
16.000 0.9406 0.11629 0.11375 -0.0074 0.0082 1.0000
16.250 0.9160 0.12765 0.12524 -0.0142 0.0084 1.0000
16.500 0.8847 0.14208 0.13978 -0.0223 0.0087 1.0000
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