EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 542 AIRFOIL (e542-il) Reynolds number: 500,000 Max Cl/Cd: 79.32 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e542-il-500000.txt Download as CSV file: xf-e542-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 542 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4119 0.12168 0.11935 -0.0477 1.0000 0.0153
-13.000 -0.4114 0.11794 0.11562 -0.0488 1.0000 0.0154
-9.500 -0.5975 0.02780 0.02243 -0.0678 0.9373 0.0093
-9.250 -0.5557 0.02477 0.01912 -0.0716 0.9303 0.0090
-9.000 -0.5152 0.02271 0.01662 -0.0748 0.9186 0.0096
-8.750 -0.4693 0.02095 0.01466 -0.0785 0.9088 0.0097
-8.500 -0.4305 0.01972 0.01327 -0.0807 0.8950 0.0097
-8.250 -0.4053 0.01919 0.01268 -0.0809 0.8780 0.0105
-8.000 -0.3813 0.01854 0.01190 -0.0805 0.8636 0.0110
-7.750 -0.3596 0.01799 0.01123 -0.0797 0.8507 0.0114
-7.500 -0.3388 0.01752 0.01063 -0.0786 0.8391 0.0118
-7.250 -0.3211 0.01681 0.00984 -0.0771 0.8284 0.0121
-7.000 -0.3062 0.01617 0.00914 -0.0751 0.8174 0.0123
-6.750 -0.2910 0.01561 0.00853 -0.0733 0.8080 0.0129
-6.500 -0.2751 0.01514 0.00800 -0.0715 0.7985 0.0138
-6.250 -0.2597 0.01463 0.00742 -0.0695 0.7901 0.0153
-6.000 -0.2433 0.01421 0.00694 -0.0677 0.7820 0.0178
-5.750 -0.2312 0.01358 0.00635 -0.0652 0.7746 0.0303
-5.500 -0.2201 0.01298 0.00590 -0.0625 0.7668 0.0604
-5.250 -0.2097 0.01243 0.00551 -0.0599 0.7600 0.1039
-5.000 -0.2055 0.01171 0.00510 -0.0561 0.7525 0.1711
-4.750 -0.2103 0.01097 0.00466 -0.0507 0.7458 0.2522
-4.500 -0.2231 0.01016 0.00428 -0.0435 0.7390 0.3520
-4.250 -0.2381 0.00895 0.00368 -0.0361 0.7327 0.4990
-4.000 -0.2383 0.00841 0.00401 -0.0304 0.7275 0.7035
-3.750 -0.2121 0.00881 0.00436 -0.0298 0.7221 0.7343
-3.500 -0.1842 0.00928 0.00475 -0.0294 0.7169 0.7483
-3.250 -0.1556 0.00983 0.00518 -0.0292 0.7123 0.7595
-3.000 -0.1237 0.01049 0.00585 -0.0293 0.7077 0.7648
-2.750 -0.0919 0.01123 0.00655 -0.0294 0.7031 0.7714
-2.500 -0.0602 0.01202 0.00728 -0.0293 0.6989 0.7789
-2.250 -0.0072 0.01396 0.00919 -0.0316 0.6951 0.7828
-2.000 0.0107 0.01408 0.00928 -0.0299 0.6904 0.7933
-1.750 0.0415 0.01421 0.00936 -0.0303 0.6861 0.7942
-1.500 0.0709 0.01427 0.00935 -0.0306 0.6824 0.7950
-1.250 0.1001 0.01432 0.00933 -0.0309 0.6786 0.7959
-1.000 0.1268 0.01430 0.00929 -0.0308 0.6744 0.7970
-0.750 0.1533 0.01427 0.00922 -0.0308 0.6704 0.7984
-0.500 0.1785 0.01419 0.00910 -0.0305 0.6667 0.8003
-0.250 0.2023 0.01409 0.00891 -0.0303 0.6631 0.8029
0.000 0.2147 0.01348 0.00828 -0.0287 0.6592 0.8089
0.250 0.2404 0.01336 0.00814 -0.0285 0.6553 0.8097
0.500 0.2673 0.01331 0.00807 -0.0285 0.6517 0.8104
0.750 0.2948 0.01328 0.00800 -0.0287 0.6482 0.8111
1.000 0.3209 0.01323 0.00793 -0.0287 0.6447 0.8119
1.250 0.3465 0.01316 0.00788 -0.0285 0.6406 0.8128
1.500 0.3725 0.01311 0.00782 -0.0284 0.6366 0.8139
1.750 0.3987 0.01303 0.00771 -0.0284 0.6328 0.8148
2.000 0.4244 0.01295 0.00761 -0.0285 0.6285 0.8158
2.250 0.4490 0.01283 0.00751 -0.0282 0.6239 0.8172
2.500 0.4747 0.01272 0.00740 -0.0283 0.6195 0.8186
2.750 0.5017 0.01263 0.00726 -0.0286 0.6155 0.8197
3.000 0.5271 0.01250 0.00715 -0.0287 0.6110 0.8209
3.250 0.5530 0.01236 0.00702 -0.0289 0.6060 0.8221
3.500 0.5803 0.01228 0.00692 -0.0294 0.6013 0.8235
3.750 0.6079 0.01224 0.00687 -0.0299 0.5966 0.8244
4.000 0.6323 0.01209 0.00677 -0.0295 0.5911 0.8250
4.250 0.6578 0.01200 0.00670 -0.0294 0.5858 0.8256
4.500 0.6839 0.01197 0.00667 -0.0294 0.5805 0.8262
4.750 0.7081 0.01189 0.00665 -0.0290 0.5741 0.8268
5.000 0.7337 0.01186 0.00663 -0.0289 0.5681 0.8274
5.250 0.7581 0.01183 0.00665 -0.0285 0.5615 0.8281
5.500 0.7822 0.01180 0.00667 -0.0280 0.5543 0.8290
5.750 0.8063 0.01180 0.00670 -0.0276 0.5469 0.8299
6.000 0.8299 0.01177 0.00671 -0.0271 0.5382 0.8306
6.250 0.8532 0.01175 0.00674 -0.0266 0.5287 0.8314
6.500 0.8756 0.01177 0.00675 -0.0259 0.5179 0.8322
6.750 0.8974 0.01177 0.00680 -0.0251 0.5054 0.8331
7.000 0.9183 0.01181 0.00685 -0.0241 0.4909 0.8340
7.250 0.9369 0.01189 0.00693 -0.0227 0.4728 0.8350
7.500 0.9542 0.01203 0.00703 -0.0211 0.4516 0.8360
7.750 0.9658 0.01224 0.00717 -0.0184 0.4263 0.8370
8.000 0.9730 0.01256 0.00738 -0.0149 0.3964 0.8383
8.250 0.9797 0.01304 0.00774 -0.0115 0.3661 0.8396
8.500 0.9839 0.01363 0.00818 -0.0078 0.3341 0.8406
8.750 0.9870 0.01427 0.00870 -0.0040 0.3034 0.8417
9.000 0.9909 0.01496 0.00929 -0.0006 0.2754 0.8428
9.250 0.9953 0.01570 0.00995 0.0026 0.2512 0.8439
9.500 1.0005 0.01648 0.01065 0.0054 0.2281 0.8451
10.000 1.0105 0.01824 0.01227 0.0107 0.1869 0.8474
10.250 1.0159 0.01921 0.01318 0.0130 0.1684 0.8487
10.500 1.0203 0.02029 0.01420 0.0152 0.1505 0.8499
10.750 1.0252 0.02142 0.01527 0.0173 0.1344 0.8513
11.000 1.0307 0.02258 0.01639 0.0191 0.1192 0.8527
11.250 1.0361 0.02380 0.01757 0.0208 0.1052 0.8540
11.500 1.0415 0.02509 0.01881 0.0223 0.0923 0.8550
11.750 1.0457 0.02647 0.02013 0.0239 0.0786 0.8560
12.000 1.0502 0.02782 0.02148 0.0254 0.0686 0.8572
12.250 1.0543 0.02928 0.02292 0.0268 0.0589 0.8583
12.500 1.0583 0.03080 0.02442 0.0281 0.0503 0.8595
12.750 1.0623 0.03238 0.02600 0.0293 0.0442 0.8607
13.000 1.0672 0.03396 0.02759 0.0303 0.0382 0.8619
13.250 1.0728 0.03554 0.02919 0.0311 0.0328 0.8632
13.500 1.0780 0.03721 0.03089 0.0318 0.0292 0.8645
13.750 1.0829 0.03897 0.03265 0.0324 0.0256 0.8658
14.000 1.0893 0.04067 0.03442 0.0329 0.0233 0.8671
14.250 1.0941 0.04255 0.03633 0.0333 0.0209 0.8684
14.500 1.0998 0.04441 0.03825 0.0336 0.0191 0.8697
14.750 1.1028 0.04658 0.04047 0.0339 0.0176 0.8710
15.000 1.1089 0.04842 0.04240 0.0340 0.0158 0.8726
15.250 1.1092 0.05092 0.04496 0.0342 0.0147 0.8740
15.500 1.1157 0.05285 0.04697 0.0342 0.0128 0.8755
15.750 1.1161 0.05550 0.04969 0.0341 0.0118 0.8769
16.000 1.1190 0.05796 0.05225 0.0339 0.0102 0.8784
16.250 1.1163 0.06114 0.05550 0.0335 0.0095 0.8798
16.500 1.1196 0.06370 0.05817 0.0330 0.0081 0.8814
16.750 1.1174 0.06702 0.06155 0.0323 0.0072 0.8829
17.000 1.1162 0.07036 0.06500 0.0315 0.0061 0.8844
17.250 1.1117 0.07423 0.06895 0.0304 0.0057 0.8857
17.500 1.1078 0.07808 0.07294 0.0292 0.0053 0.8872
17.750 1.1025 0.08221 0.07717 0.0278 0.0043 0.8888
18.000 1.0994 0.08616 0.08125 0.0264 0.0044 0.8905
18.250 1.0944 0.09050 0.08571 0.0246 0.0043 0.8921
18.500 1.0857 0.09552 0.09087 0.0225 0.0043 0.8937
18.750 1.0732 0.10136 0.09685 0.0199 0.0038 0.8952
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