EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 50,000 Max Cl/Cd: 23.44 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1200-il-50000-n5.txt Download as CSV file: xf-e1200-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1200 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3308 0.13751 0.13045 -0.0530 1.0000 0.0645
-12.500 -0.3443 0.13545 0.12850 -0.0512 1.0000 0.0632
-12.000 -0.3760 0.12473 0.11790 -0.0554 0.9964 0.0591
-11.750 -0.3680 0.11985 0.11302 -0.0589 0.9916 0.0587
-11.500 -0.3640 0.11455 0.10772 -0.0627 0.9865 0.0584
-11.000 -0.3702 0.10145 0.09462 -0.0722 0.9760 0.0582
-10.750 -0.3791 0.09348 0.08663 -0.0783 0.9708 0.0577
-10.500 -0.3986 0.08570 0.07879 -0.0842 0.9638 0.0572
-10.250 -0.4235 0.07824 0.07119 -0.0902 0.9570 0.0567
-10.000 -0.4501 0.07320 0.06600 -0.0926 0.9483 0.0563
-9.750 -0.4711 0.06885 0.06143 -0.0946 0.9414 0.0560
-9.500 -0.4963 0.06625 0.05867 -0.0925 0.9319 0.0559
-9.250 -0.5060 0.06253 0.05462 -0.0929 0.9258 0.0562
-9.000 -0.5212 0.06019 0.05203 -0.0900 0.9178 0.0566
-8.750 -0.5236 0.05727 0.04874 -0.0890 0.9124 0.0571
-8.500 -0.5192 0.05427 0.04528 -0.0885 0.9083 0.0580
-8.250 -0.5233 0.05243 0.04314 -0.0853 0.9015 0.0584
-8.000 -0.5131 0.05001 0.04026 -0.0843 0.8972 0.0591
-7.750 -0.4926 0.04794 0.03800 -0.0844 0.8942 0.0602
-7.500 -0.4762 0.04648 0.03640 -0.0836 0.8908 0.0616
-7.250 -0.4686 0.04547 0.03527 -0.0812 0.8856 0.0632
-7.000 -0.4504 0.04421 0.03379 -0.0803 0.8818 0.0662
-6.750 -0.4257 0.04285 0.03207 -0.0802 0.8788 0.0694
-6.500 -0.3980 0.04166 0.03089 -0.0805 0.8766 0.0725
-6.250 -0.3867 0.04104 0.03021 -0.0780 0.8724 0.0751
-6.000 -0.3714 0.04041 0.02945 -0.0760 0.8681 0.0792
-5.750 -0.3505 0.03970 0.02872 -0.0751 0.8647 0.0851
-5.500 -0.3266 0.03902 0.02791 -0.0745 0.8618 0.0937
-5.250 -0.3026 0.03820 0.02715 -0.0744 0.8595 0.1046
-5.000 -0.3012 0.03784 0.02684 -0.0707 0.8541 0.1143
-4.750 -0.2886 0.03718 0.02627 -0.0690 0.8498 0.1339
-4.500 -0.2709 0.03630 0.02560 -0.0683 0.8464 0.1679
-4.250 -0.2510 0.03514 0.02489 -0.0685 0.8437 0.2310
-4.000 -0.2421 0.03413 0.02451 -0.0668 0.8396 0.3183
-3.750 -0.2383 0.03372 0.02505 -0.0628 0.8347 0.4419
-3.500 -0.2267 0.03457 0.02636 -0.0578 0.8308 0.5582
-3.250 -0.2047 0.03535 0.02695 -0.0559 0.8276 0.6242
-3.000 -0.1886 0.03610 0.02752 -0.0532 0.8238 0.6628
-2.750 -0.1822 0.03679 0.02811 -0.0491 0.8184 0.6882
-2.500 -0.1664 0.03742 0.02860 -0.0461 0.8142 0.7124
-2.250 -0.1454 0.03794 0.02893 -0.0440 0.8109 0.7358
-2.000 -0.1322 0.03845 0.02933 -0.0407 0.8066 0.7546
-1.750 -0.1258 0.03888 0.02969 -0.0367 0.8010 0.7722
-1.500 -0.1098 0.03926 0.02995 -0.0338 0.7967 0.7917
-1.250 -0.0879 0.03955 0.03010 -0.0317 0.7934 0.8115
-1.000 -0.0819 0.03982 0.03031 -0.0281 0.7876 0.8274
-0.750 -0.0673 0.03999 0.03037 -0.0259 0.7821 0.8412
-0.500 -0.0421 0.04007 0.03030 -0.0257 0.7781 0.8525
-0.250 -0.0205 0.04022 0.03031 -0.0251 0.7736 0.8618
0.000 -0.0088 0.04038 0.03040 -0.0233 0.7667 0.8704
0.250 0.0184 0.04049 0.03038 -0.0237 0.7622 0.8780
0.500 0.0471 0.04061 0.03038 -0.0244 0.7580 0.8849
0.750 0.0576 0.04089 0.03060 -0.0227 0.7500 0.8927
1.000 0.0875 0.04101 0.03062 -0.0237 0.7453 0.8993
1.250 0.1105 0.04127 0.03081 -0.0238 0.7392 0.9060
1.500 0.1304 0.04152 0.03101 -0.0235 0.7318 0.9136
1.750 0.1675 0.04166 0.03107 -0.0255 0.7275 0.9193
2.000 0.1816 0.04208 0.03147 -0.0247 0.7185 0.9279
2.250 0.2175 0.04228 0.03161 -0.0266 0.7128 0.9339
2.500 0.2424 0.04264 0.03195 -0.0273 0.7051 0.9420
2.750 0.2758 0.04294 0.03224 -0.0292 0.6977 0.9488
3.000 0.3201 0.04293 0.03219 -0.0321 0.6936 0.9556
3.250 0.3410 0.04358 0.03287 -0.0330 0.6819 0.9653
3.750 0.4069 0.04392 0.03323 -0.0367 0.6649 0.9928
4.000 0.4218 0.04424 0.03354 -0.0360 0.6545 1.0000
4.250 0.4539 0.04408 0.03336 -0.0369 0.6477 1.0000
4.500 0.4688 0.04455 0.03383 -0.0364 0.6356 1.0000
4.750 0.5093 0.04408 0.03335 -0.0380 0.6304 1.0000
5.000 0.5246 0.04463 0.03392 -0.0376 0.6172 1.0000
5.250 0.5438 0.04509 0.03440 -0.0375 0.6048 1.0000
5.500 0.5797 0.04469 0.03401 -0.0385 0.5977 1.0000
5.750 0.6018 0.04498 0.03433 -0.0386 0.5855 1.0000
6.000 0.6214 0.04545 0.03483 -0.0384 0.5724 1.0000
6.250 0.6446 0.04570 0.03511 -0.0385 0.5604 1.0000
6.500 0.6814 0.04494 0.03439 -0.0391 0.5531 1.0000
6.750 0.7007 0.04538 0.03488 -0.0388 0.5394 1.0000
7.000 0.7221 0.04565 0.03519 -0.0385 0.5265 1.0000
7.500 0.7819 0.04471 0.03435 -0.0385 0.5063 1.0000
7.750 0.8036 0.04493 0.03461 -0.0381 0.4925 1.0000
8.000 0.8279 0.04495 0.03468 -0.0378 0.4794 1.0000
8.250 0.8570 0.04453 0.03429 -0.0375 0.4674 1.0000
8.500 0.8945 0.04339 0.03316 -0.0376 0.4571 1.0000
8.750 0.9188 0.04346 0.03325 -0.0372 0.4423 1.0000
9.000 0.9434 0.04356 0.03335 -0.0368 0.4275 1.0000
9.250 0.9679 0.04372 0.03349 -0.0364 0.4128 1.0000
9.500 0.9915 0.04400 0.03375 -0.0359 0.3981 1.0000
9.750 1.0140 0.04442 0.03414 -0.0355 0.3838 1.0000
10.000 1.0362 0.04492 0.03460 -0.0350 0.3702 1.0000
10.250 1.0588 0.04540 0.03505 -0.0346 0.3570 1.0000
10.500 1.0799 0.04607 0.03570 -0.0342 0.3446 1.0000
10.750 1.0921 0.04749 0.03717 -0.0335 0.3321 1.0000
11.000 1.1079 0.04864 0.03834 -0.0329 0.3206 1.0000
11.250 1.1315 0.04920 0.03886 -0.0326 0.3103 1.0000
11.500 1.1404 0.05095 0.04072 -0.0319 0.2996 1.0000
11.750 1.1546 0.05231 0.04213 -0.0314 0.2898 1.0000
12.000 1.1748 0.05316 0.04298 -0.0310 0.2805 1.0000
12.250 1.1796 0.05537 0.04536 -0.0303 0.2716 1.0000
12.500 1.2049 0.05582 0.04574 -0.0301 0.2631 1.0000
12.750 1.2013 0.05876 0.04893 -0.0293 0.2549 1.0000
13.000 1.2273 0.05917 0.04927 -0.0291 0.2471 1.0000
13.250 1.2184 0.06268 0.05306 -0.0283 0.2398 1.0000
13.500 1.2423 0.06318 0.05354 -0.0280 0.2323 1.0000
13.750 1.2302 0.06717 0.05781 -0.0274 0.2260 1.0000
14.000 1.2381 0.06923 0.05996 -0.0271 0.2194 1.0000
14.250 1.2420 0.07176 0.06261 -0.0268 0.2133 1.0000
14.500 1.2258 0.07654 0.06764 -0.0268 0.2075 1.0000
14.750 1.2568 0.07605 0.06708 -0.0264 0.2011 1.0000
15.000 1.2175 0.08388 0.07526 -0.0273 0.1967 1.0000
15.250 1.1836 0.09180 0.08342 -0.0290 0.1917 1.0000
15.500 1.2398 0.08739 0.07889 -0.0271 0.1856 1.0000
15.750 1.0431 0.12396 0.11593 -0.0421 0.1781 1.0000
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