EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 500,000 Max Cl/Cd: 81.28 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1233-il-500000-n5.txt Download as CSV file: xf-e1233-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1233 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.6270 0.10504 0.10177 -0.0566 1.0000 0.0095
-16.250 -0.6655 0.09408 0.09064 -0.0622 1.0000 0.0095
-16.000 -0.6985 0.08450 0.08089 -0.0672 1.0000 0.0095
-15.750 -0.7217 0.07688 0.07313 -0.0712 1.0000 0.0094
-15.500 -0.7465 0.06935 0.06545 -0.0752 1.0000 0.0093
-15.250 -0.7616 0.06366 0.05962 -0.0781 1.0000 0.0093
-15.000 -0.7784 0.05824 0.05406 -0.0805 1.0000 0.0094
-14.750 -0.7912 0.05392 0.04961 -0.0819 1.0000 0.0095
-14.500 -0.8033 0.05014 0.04571 -0.0827 1.0000 0.0095
-14.250 -0.7992 0.04625 0.04167 -0.0863 0.9983 0.0096
-14.000 -0.7911 0.04313 0.03843 -0.0894 0.9963 0.0096
-13.750 -0.7804 0.04035 0.03551 -0.0923 0.9943 0.0097
-13.500 -0.7699 0.03787 0.03290 -0.0944 0.9923 0.0098
-13.250 -0.7586 0.03569 0.03060 -0.0960 0.9893 0.0099
-13.000 -0.7438 0.03370 0.02849 -0.0978 0.9865 0.0100
-12.750 -0.7271 0.03174 0.02645 -0.0999 0.9841 0.0101
-12.500 -0.7129 0.03003 0.02467 -0.1009 0.9806 0.0102
-12.250 -0.7006 0.02840 0.02298 -0.1013 0.9754 0.0104
-12.000 -0.6788 0.02700 0.02150 -0.1029 0.9722 0.0104
-11.750 -0.6719 0.02588 0.02034 -0.1011 0.9633 0.0107
-11.500 -0.6640 0.02486 0.01927 -0.0994 0.9530 0.0109
-11.250 -0.6571 0.02384 0.01819 -0.0974 0.9398 0.0109
-11.000 -0.6436 0.02287 0.01716 -0.0964 0.9280 0.0112
-10.750 -0.6219 0.02185 0.01607 -0.0968 0.9175 0.0114
-10.500 -0.5938 0.02081 0.01493 -0.0982 0.9064 0.0116
-10.250 -0.5505 0.01975 0.01377 -0.1024 0.8948 0.0121
-10.000 -0.4908 0.01863 0.01253 -0.1097 0.8822 0.0126
-9.750 -0.4178 0.01746 0.01124 -0.1200 0.8637 0.0132
-9.500 -0.3685 0.01678 0.01037 -0.1252 0.8332 0.0139
-9.250 -0.3481 0.01643 0.00982 -0.1244 0.8004 0.0142
-9.000 -0.3323 0.01615 0.00937 -0.1226 0.7746 0.0148
-8.750 -0.3170 0.01588 0.00897 -0.1206 0.7527 0.0152
-8.500 -0.3023 0.01555 0.00854 -0.1185 0.7330 0.0161
-8.250 -0.2857 0.01529 0.00819 -0.1167 0.7152 0.0168
-8.000 -0.2684 0.01505 0.00783 -0.1149 0.6983 0.0177
-7.750 -0.2508 0.01480 0.00748 -0.1132 0.6824 0.0188
-7.500 -0.2318 0.01452 0.00715 -0.1117 0.6681 0.0199
-7.250 -0.2120 0.01429 0.00683 -0.1104 0.6550 0.0214
-7.000 -0.1927 0.01403 0.00651 -0.1089 0.6413 0.0234
-6.750 -0.1720 0.01381 0.00623 -0.1077 0.6286 0.0255
-6.500 -0.1507 0.01357 0.00595 -0.1066 0.6176 0.0289
-6.000 -0.1074 0.01310 0.00544 -0.1046 0.5960 0.0405
-5.750 -0.0853 0.01292 0.00522 -0.1036 0.5852 0.0479
-5.500 -0.0623 0.01273 0.00502 -0.1028 0.5746 0.0562
-5.250 -0.0391 0.01256 0.00484 -0.1020 0.5652 0.0643
-5.000 -0.0152 0.01240 0.00466 -0.1013 0.5557 0.0727
-4.750 0.0086 0.01226 0.00450 -0.1007 0.5466 0.0809
-4.500 0.0331 0.01212 0.00434 -0.1001 0.5372 0.0902
-4.000 0.0819 0.01181 0.00405 -0.0990 0.5202 0.1168
-3.500 0.1311 0.01143 0.00378 -0.0981 0.5045 0.1631
-3.250 0.1556 0.01125 0.00365 -0.0976 0.4963 0.1925
-3.000 0.1807 0.01102 0.00352 -0.0973 0.4891 0.2322
-2.750 0.2059 0.01074 0.00339 -0.0971 0.4820 0.2842
-2.500 0.2305 0.01044 0.00326 -0.0968 0.4754 0.3491
-2.250 0.2564 0.01005 0.00313 -0.0969 0.4692 0.4307
-2.000 0.2821 0.00978 0.00309 -0.0967 0.4623 0.5116
-1.750 0.3079 0.00973 0.00311 -0.0963 0.4557 0.5569
-1.500 0.3348 0.00972 0.00314 -0.0961 0.4495 0.5861
-1.250 0.3612 0.00977 0.00319 -0.0958 0.4436 0.6068
-1.000 0.3874 0.00985 0.00324 -0.0954 0.4383 0.6233
-0.750 0.4144 0.00991 0.00330 -0.0952 0.4331 0.6371
-0.500 0.4407 0.01001 0.00337 -0.0948 0.4273 0.6495
0.000 0.4927 0.01026 0.00355 -0.0940 0.4168 0.6785
0.250 0.5182 0.01037 0.00367 -0.0934 0.4119 0.6881
0.500 0.5437 0.01050 0.00374 -0.0929 0.4071 0.6954
0.750 0.5689 0.01061 0.00380 -0.0924 0.4028 0.6996
1.000 0.5949 0.01068 0.00386 -0.0920 0.3987 0.7026
1.250 0.6204 0.01077 0.00393 -0.0916 0.3942 0.7056
1.500 0.6453 0.01089 0.00400 -0.0910 0.3894 0.7089
1.750 0.6699 0.01103 0.00408 -0.0904 0.3851 0.7122
2.000 0.6960 0.01112 0.00415 -0.0901 0.3815 0.7153
2.250 0.7214 0.01122 0.00422 -0.0897 0.3776 0.7180
2.500 0.7458 0.01134 0.00433 -0.0891 0.3738 0.7206
2.750 0.7695 0.01149 0.00445 -0.0884 0.3699 0.7234
3.000 0.7943 0.01162 0.00457 -0.0879 0.3663 0.7260
3.250 0.8196 0.01174 0.00468 -0.0874 0.3627 0.7289
3.500 0.8442 0.01188 0.00481 -0.0869 0.3590 0.7320
3.750 0.8684 0.01205 0.00494 -0.0864 0.3555 0.7348
4.000 0.8918 0.01223 0.00509 -0.0857 0.3522 0.7372
4.250 0.9159 0.01236 0.00524 -0.0851 0.3494 0.7395
4.500 0.9402 0.01249 0.00540 -0.0845 0.3461 0.7420
4.750 0.9638 0.01265 0.00556 -0.0838 0.3426 0.7449
5.000 0.9867 0.01284 0.00574 -0.0831 0.3392 0.7478
5.250 1.0092 0.01304 0.00592 -0.0823 0.3362 0.7506
5.500 1.0322 0.01324 0.00612 -0.0816 0.3335 0.7531
6.000 1.0792 0.01357 0.00649 -0.0804 0.3280 0.7580
6.250 1.1012 0.01376 0.00671 -0.0795 0.3247 0.7608
6.500 1.1223 0.01399 0.00694 -0.0785 0.3215 0.7637
6.750 1.1430 0.01424 0.00719 -0.0775 0.3187 0.7665
7.000 1.1651 0.01446 0.00743 -0.0767 0.3164 0.7692
7.250 1.1877 0.01467 0.00767 -0.0760 0.3141 0.7721
7.500 1.2093 0.01489 0.00793 -0.0752 0.3112 0.7749
7.750 1.2297 0.01513 0.00821 -0.0742 0.3085 0.7778
8.000 1.2491 0.01541 0.00851 -0.0730 0.3054 0.7808
8.250 1.2679 0.01573 0.00884 -0.0718 0.3027 0.7838
8.500 1.2874 0.01603 0.00917 -0.0707 0.3005 0.7871
8.750 1.3083 0.01630 0.00949 -0.0699 0.2984 0.7905
9.000 1.3283 0.01659 0.00983 -0.0689 0.2958 0.7938
9.250 1.3468 0.01690 0.01020 -0.0678 0.2932 0.7971
9.500 1.3643 0.01727 0.01061 -0.0665 0.2904 0.8006
9.750 1.3807 0.01770 0.01105 -0.0651 0.2877 0.8044
10.000 1.3966 0.01816 0.01154 -0.0637 0.2853 0.8087
10.250 1.4155 0.01851 0.01197 -0.0627 0.2834 0.8128
10.500 1.4330 0.01890 0.01244 -0.0616 0.2810 0.8174
10.750 1.4496 0.01934 0.01295 -0.0604 0.2783 0.8223
11.000 1.4648 0.01986 0.01352 -0.0590 0.2756 0.8274
11.250 1.4788 0.02043 0.01414 -0.0576 0.2730 0.8330
11.500 1.4910 0.02109 0.01485 -0.0560 0.2704 0.8400
11.750 1.5062 0.02165 0.01549 -0.0548 0.2679 0.8476
12.000 1.5205 0.02221 0.01616 -0.0535 0.2650 0.8565
12.250 1.5329 0.02289 0.01692 -0.0520 0.2617 0.8671
12.750 1.5501 0.02458 0.01878 -0.0484 0.2550 0.9110
13.250 1.5804 0.02618 0.02058 -0.0474 0.2488 1.0000
13.500 1.5909 0.02726 0.02170 -0.0464 0.2452 1.0000
13.750 1.5988 0.02855 0.02301 -0.0453 0.2419 1.0000
14.000 1.6066 0.02989 0.02439 -0.0443 0.2388 1.0000
14.250 1.6179 0.03103 0.02561 -0.0436 0.2351 1.0000
14.500 1.6245 0.03254 0.02717 -0.0427 0.2303 1.0000
14.750 1.6264 0.03446 0.02911 -0.0417 0.2258 1.0000
15.000 1.6324 0.03616 0.03087 -0.0410 0.2207 1.0000
15.250 1.6316 0.03847 0.03320 -0.0402 0.2135 1.0000
15.500 1.6311 0.04083 0.03560 -0.0395 0.2082 1.0000
15.750 1.6322 0.04314 0.03797 -0.0390 0.2024 1.0000
16.000 1.6246 0.04636 0.04120 -0.0385 0.1964 1.0000
16.250 1.6246 0.04893 0.04384 -0.0383 0.1903 1.0000
16.500 1.6172 0.05233 0.04728 -0.0381 0.1845 1.0000
16.750 1.6118 0.05563 0.05064 -0.0381 0.1789 1.0000
17.000 1.6019 0.05953 0.05458 -0.0383 0.1721 1.0000
17.250 1.5929 0.06341 0.05852 -0.0386 0.1671 1.0000
17.500 1.5835 0.06746 0.06262 -0.0391 0.1608 1.0000
17.750 1.5685 0.07229 0.06749 -0.0398 0.1547 1.0000
18.000 1.5572 0.07677 0.07204 -0.0406 0.1484 1.0000
18.250 1.5411 0.08199 0.07730 -0.0418 0.1428 1.0000
18.500 1.5267 0.08709 0.08245 -0.0430 0.1359 1.0000
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Polar data table (+)
Polar graphs
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