E374 (e374-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 50,000 Max Cl/Cd: 34.15 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e374-il-50000.txt Download as CSV file: xf-e374-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4142 0.10747 0.10070 -0.0187 1.0000 0.2541
-9.000 -0.4308 0.10599 0.09938 -0.0199 1.0000 0.2647
-8.750 -0.4210 0.10232 0.09573 -0.0191 1.0000 0.2778
-8.500 -0.4110 0.09838 0.09183 -0.0183 1.0000 0.2908
-8.250 -0.4052 0.09501 0.08852 -0.0176 1.0000 0.3041
-8.000 -0.4094 0.09252 0.08612 -0.0169 1.0000 0.3202
-7.750 -0.3980 0.08878 0.08244 -0.0152 1.0000 0.3406
-7.500 -0.3929 0.08582 0.07953 -0.0138 1.0000 0.3597
-7.250 -0.4167 0.08479 0.07870 -0.0117 1.0000 0.3795
-6.000 -0.5296 0.05557 0.04901 -0.0293 1.0000 0.1330
-5.750 -0.5344 0.05151 0.04442 -0.0269 1.0000 0.1206
-5.500 -0.5297 0.04827 0.04101 -0.0245 1.0000 0.1167
-5.250 -0.5255 0.04503 0.03736 -0.0221 1.0000 0.1132
-5.000 -0.5181 0.04217 0.03405 -0.0199 1.0000 0.1124
-4.750 -0.5072 0.03968 0.03119 -0.0178 1.0000 0.1139
-4.500 -0.4934 0.03715 0.02820 -0.0159 1.0000 0.1147
-4.250 -0.4766 0.03472 0.02529 -0.0141 1.0000 0.1159
-4.000 -0.4582 0.03289 0.02283 -0.0124 1.0000 0.1214
-3.750 -0.4392 0.03109 0.02098 -0.0112 1.0000 0.1318
-3.500 -0.4180 0.02935 0.01903 -0.0099 1.0000 0.1436
-3.250 -0.3970 0.02802 0.01750 -0.0085 1.0000 0.1644
-3.000 -0.1682 0.02262 0.01536 -0.0324 1.0000 1.0000
-2.750 -0.1819 0.02247 0.01499 -0.0280 1.0000 1.0000
-2.500 -0.1888 0.02240 0.01469 -0.0241 1.0000 1.0000
-2.250 -0.1905 0.02240 0.01443 -0.0208 1.0000 1.0000
-2.000 -0.1882 0.02248 0.01423 -0.0180 1.0000 1.0000
-1.750 -0.1828 0.02262 0.01409 -0.0156 1.0000 1.0000
-1.500 -0.1753 0.02281 0.01401 -0.0135 1.0000 1.0000
-1.250 -0.1661 0.02306 0.01399 -0.0116 1.0000 1.0000
-1.000 -0.1556 0.02335 0.01404 -0.0099 1.0000 1.0000
-0.750 -0.1419 0.02371 0.01413 -0.0088 0.9994 1.0000
-0.500 -0.1041 0.02452 0.01465 -0.0123 0.9907 1.0000
-0.250 -0.0666 0.02539 0.01527 -0.0156 0.9820 1.0000
0.000 -0.0338 0.02613 0.01578 -0.0181 0.9732 1.0000
0.250 -0.0034 0.02686 0.01633 -0.0200 0.9647 1.0000
0.500 0.0333 0.02780 0.01709 -0.0230 0.9564 1.0000
0.750 0.0570 0.02843 0.01758 -0.0237 0.9475 1.0000
1.000 0.0869 0.02926 0.01829 -0.0254 0.9392 1.0000
1.250 0.1162 0.03009 0.01903 -0.0270 0.9308 1.0000
1.500 0.1394 0.03086 0.01972 -0.0275 0.9221 1.0000
1.750 0.1745 0.03187 0.02065 -0.0300 0.9138 1.0000
2.000 0.1919 0.03260 0.02134 -0.0295 0.9048 1.0000
2.250 0.2183 0.03353 0.02224 -0.0306 0.8962 1.0000
2.500 0.2484 0.03451 0.02321 -0.0321 0.8869 1.0000
2.750 0.2655 0.03537 0.02406 -0.0316 0.8775 1.0000
3.000 0.2928 0.03639 0.02509 -0.0327 0.8678 1.0000
3.250 0.3246 0.03744 0.02617 -0.0344 0.8576 1.0000
3.500 0.3401 0.03839 0.02715 -0.0336 0.8468 1.0000
3.750 0.3623 0.03943 0.02826 -0.0338 0.8357 1.0000
4.000 0.3887 0.04050 0.02939 -0.0346 0.8238 1.0000
4.250 0.4170 0.04158 0.03055 -0.0355 0.8112 1.0000
4.500 0.4452 0.04263 0.03171 -0.0364 0.7978 1.0000
4.750 0.4710 0.04366 0.03289 -0.0367 0.7835 1.0000
5.000 0.4938 0.04469 0.03404 -0.0366 0.7681 1.0000
5.250 0.5160 0.04572 0.03519 -0.0363 0.7519 1.0000
5.500 0.5410 0.04668 0.03634 -0.0363 0.7346 1.0000
5.750 0.5761 0.04736 0.03724 -0.0370 0.7163 1.0000
6.000 0.6083 0.04797 0.03806 -0.0371 0.6970 1.0000
6.250 0.6308 0.04869 0.03898 -0.0361 0.6760 1.0000
6.500 0.6766 0.04836 0.03902 -0.0365 0.6542 1.0000
6.750 0.7225 0.04739 0.03842 -0.0362 0.6299 1.0000
7.000 0.7710 0.04560 0.03705 -0.0351 0.6034 1.0000
7.250 0.8782 0.03784 0.03013 -0.0347 0.5703 1.0000
7.500 0.9311 0.03278 0.02553 -0.0307 0.5238 1.0000
7.750 0.9621 0.02882 0.02160 -0.0248 0.4532 1.0000
8.000 0.9623 0.02818 0.02028 -0.0176 0.3595 1.0000
8.250 0.9513 0.03005 0.02122 -0.0113 0.2777 1.0000
8.500 0.9440 0.03263 0.02308 -0.0065 0.2156 1.0000
8.750 0.9518 0.03544 0.02536 -0.0036 0.1670 1.0000
9.000 0.9785 0.03842 0.02808 -0.0029 0.1333 1.0000
9.250 1.0159 0.04177 0.03148 -0.0034 0.1151 1.0000
9.500 1.0382 0.04488 0.03485 -0.0025 0.1046 1.0000
9.750 1.0682 0.04889 0.03893 -0.0028 0.0982 1.0000
10.000 1.0780 0.05265 0.04318 -0.0006 0.0962 1.0000
10.250 1.0773 0.05601 0.04707 0.0024 0.0944 1.0000
10.500 1.0723 0.05941 0.05090 0.0054 0.0926 1.0000
10.750 1.0646 0.06293 0.05478 0.0082 0.0917 1.0000
11.000 1.0512 0.06640 0.05855 0.0111 0.0911 1.0000
11.250 1.0323 0.06989 0.06228 0.0140 0.0913 1.0000
11.500 1.0105 0.07378 0.06639 0.0160 0.0921 1.0000
11.750 0.9874 0.07824 0.07104 0.0167 0.0934 1.0000
12.000 0.9634 0.08325 0.07619 0.0163 0.0945 1.0000
12.250 0.9424 0.08883 0.08187 0.0150 0.0958 1.0000
12.500 0.9243 0.09490 0.08801 0.0132 0.0968 1.0000
12.750 0.9138 0.10104 0.09419 0.0114 0.0975 1.0000
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Polar data table (+)
Polar graphs
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