EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 200,000 Max Cl/Cd: 56.66 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1230-il-200000.txt Download as CSV file: xf-e1230-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1230 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5344 0.06748 0.06351 -0.0699 1.0000 0.0344
-11.250 -0.5489 0.06364 0.05964 -0.0703 1.0000 0.0342
-11.000 -0.5698 0.05988 0.05583 -0.0702 1.0000 0.0339
-10.750 -0.5947 0.05662 0.05249 -0.0688 1.0000 0.0337
-10.500 -0.6229 0.05417 0.04996 -0.0654 1.0000 0.0335
-10.250 -0.6532 0.05236 0.04809 -0.0598 1.0000 0.0333
-10.000 -0.6792 0.04985 0.04544 -0.0548 1.0000 0.0329
-9.750 -0.7046 0.04720 0.04261 -0.0495 1.0000 0.0325
-9.500 -0.7180 0.04308 0.03809 -0.0469 0.9974 0.0320
-9.250 -0.6991 0.03776 0.03209 -0.0496 0.9901 0.0317
-9.000 -0.6699 0.03444 0.02833 -0.0520 0.9834 0.0321
-8.750 -0.6354 0.03173 0.02523 -0.0547 0.9778 0.0327
-8.500 -0.6024 0.02960 0.02270 -0.0566 0.9695 0.0340
-8.250 -0.5685 0.02773 0.02066 -0.0584 0.9608 0.0354
-8.000 -0.5328 0.02643 0.01934 -0.0603 0.9519 0.0371
-7.750 -0.4925 0.02481 0.01751 -0.0628 0.9458 0.0389
-7.500 -0.4592 0.02324 0.01589 -0.0639 0.9350 0.0407
-7.250 -0.4247 0.02207 0.01474 -0.0652 0.9243 0.0433
-7.000 -0.3854 0.02074 0.01338 -0.0675 0.9164 0.0469
-6.750 -0.3464 0.01974 0.01234 -0.0696 0.9045 0.0525
-6.500 -0.3076 0.01870 0.01130 -0.0718 0.8903 0.0596
-6.250 -0.2686 0.01763 0.01031 -0.0741 0.8740 0.0705
-6.000 -0.2305 0.01685 0.00950 -0.0762 0.8545 0.0864
-5.750 -0.1985 0.01615 0.00878 -0.0771 0.8326 0.1026
-5.500 -0.1708 0.01569 0.00826 -0.0770 0.8106 0.1180
-5.250 -0.1467 0.01532 0.00783 -0.0763 0.7889 0.1336
-5.000 -0.1236 0.01498 0.00745 -0.0753 0.7689 0.1514
-4.750 -0.1012 0.01463 0.00708 -0.0743 0.7504 0.1734
-4.250 -0.0615 0.01365 0.00633 -0.0714 0.7162 0.2533
-4.000 -0.0467 0.01285 0.00599 -0.0692 0.7007 0.3559
-3.750 -0.0331 0.01227 0.00601 -0.0664 0.6866 0.5020
-3.500 -0.0113 0.01244 0.00627 -0.0645 0.6730 0.5780
-3.250 0.0124 0.01272 0.00647 -0.0631 0.6586 0.6136
-3.000 0.0367 0.01304 0.00666 -0.0618 0.6450 0.6380
-2.750 0.0613 0.01334 0.00675 -0.0607 0.6329 0.6575
-2.500 0.0857 0.01351 0.00681 -0.0596 0.6203 0.6733
-2.250 0.1102 0.01364 0.00683 -0.0585 0.6082 0.6873
-2.000 0.1360 0.01376 0.00685 -0.0576 0.5974 0.6993
-1.750 0.1605 0.01381 0.00687 -0.0566 0.5857 0.7108
-1.500 0.1859 0.01391 0.00683 -0.0558 0.5760 0.7227
-1.250 0.2102 0.01395 0.00680 -0.0548 0.5651 0.7347
-1.000 0.2354 0.01399 0.00678 -0.0539 0.5556 0.7463
-0.750 0.2593 0.01400 0.00677 -0.0527 0.5455 0.7598
-0.500 0.2837 0.01407 0.00677 -0.0516 0.5368 0.7737
-0.250 0.3078 0.01410 0.00675 -0.0507 0.5276 0.7857
0.000 0.3342 0.01417 0.00673 -0.0501 0.5198 0.7941
0.250 0.3591 0.01418 0.00670 -0.0496 0.5107 0.8021
0.500 0.3858 0.01423 0.00665 -0.0492 0.5030 0.8083
0.750 0.4114 0.01426 0.00667 -0.0488 0.4947 0.8151
1.000 0.4377 0.01430 0.00663 -0.0485 0.4871 0.8211
1.250 0.4648 0.01442 0.00668 -0.0484 0.4803 0.8268
1.500 0.4907 0.01447 0.00672 -0.0481 0.4729 0.8333
1.750 0.5178 0.01457 0.00673 -0.0480 0.4664 0.8391
2.000 0.5442 0.01469 0.00684 -0.0477 0.4596 0.8454
2.250 0.5703 0.01477 0.00691 -0.0475 0.4527 0.8522
2.500 0.5979 0.01494 0.00700 -0.0474 0.4470 0.8589
2.750 0.6240 0.01509 0.00719 -0.0472 0.4410 0.8664
3.000 0.6506 0.01522 0.00734 -0.0470 0.4349 0.8745
3.250 0.6784 0.01541 0.00746 -0.0470 0.4296 0.8851
3.500 0.7060 0.01563 0.00768 -0.0471 0.4241 0.8977
3.750 0.7352 0.01578 0.00789 -0.0475 0.4181 0.9102
4.000 0.7695 0.01600 0.00808 -0.0490 0.4128 0.9226
4.250 0.8076 0.01638 0.00839 -0.0513 0.4079 0.9370
4.500 0.8443 0.01663 0.00872 -0.0535 0.4023 0.9559
4.750 0.8864 0.01689 0.00897 -0.0568 0.3967 0.9707
5.000 0.9306 0.01727 0.00922 -0.0606 0.3918 0.9850
5.250 0.9718 0.01762 0.00964 -0.0640 0.3867 1.0000
5.500 0.9873 0.01785 0.00986 -0.0622 0.3827 1.0000
5.750 1.0083 0.01812 0.01009 -0.0612 0.3789 1.0000
6.000 1.0321 0.01844 0.01032 -0.0607 0.3753 1.0000
6.250 1.0558 0.01888 0.01073 -0.0603 0.3716 1.0000
6.500 1.0752 0.01918 0.01111 -0.0589 0.3675 1.0000
6.750 1.0972 0.01950 0.01145 -0.0581 0.3636 1.0000
7.000 1.1213 0.01984 0.01177 -0.0576 0.3602 1.0000
7.250 1.1474 0.02025 0.01210 -0.0576 0.3570 1.0000
7.500 1.1709 0.02078 0.01265 -0.0571 0.3537 1.0000
7.750 1.1898 0.02115 0.01314 -0.0558 0.3500 1.0000
8.000 1.2112 0.02152 0.01356 -0.0549 0.3463 1.0000
8.250 1.2349 0.02188 0.01392 -0.0544 0.3429 1.0000
8.500 1.2611 0.02231 0.01431 -0.0544 0.3400 1.0000
8.750 1.2869 0.02297 0.01495 -0.0545 0.3371 1.0000
9.000 1.3030 0.02344 0.01559 -0.0528 0.3339 1.0000
9.250 1.3217 0.02390 0.01615 -0.0515 0.3303 1.0000
9.500 1.3432 0.02430 0.01660 -0.0508 0.3270 1.0000
9.750 1.3678 0.02472 0.01700 -0.0506 0.3241 1.0000
10.000 1.3964 0.02531 0.01754 -0.0511 0.3213 1.0000
10.250 1.4123 0.02599 0.01836 -0.0496 0.3183 1.0000
10.500 1.4254 0.02657 0.01911 -0.0475 0.3149 1.0000
10.750 1.4426 0.02710 0.01974 -0.0462 0.3116 1.0000
11.000 1.4639 0.02753 0.02020 -0.0455 0.3085 1.0000
11.250 1.4914 0.02791 0.02052 -0.0458 0.3055 1.0000
11.500 1.5115 0.02867 0.02134 -0.0451 0.3023 1.0000
11.750 1.5165 0.02937 0.02226 -0.0420 0.2989 1.0000
12.000 1.5267 0.02998 0.02299 -0.0397 0.2955 1.0000
12.250 1.5433 0.03038 0.02343 -0.0384 0.2921 1.0000
12.500 1.5708 0.03065 0.02366 -0.0387 0.2889 1.0000
12.750 1.5882 0.03142 0.02447 -0.0377 0.2856 1.0000
13.000 1.5811 0.03236 0.02564 -0.0331 0.2825 1.0000
13.250 1.5824 0.03320 0.02662 -0.0299 0.2791 1.0000
13.500 1.5955 0.03366 0.02712 -0.0284 0.2756 1.0000
13.750 1.6257 0.03370 0.02706 -0.0289 0.2719 1.0000
14.000 1.6259 0.03485 0.02836 -0.0261 0.2686 1.0000
14.250 1.6128 0.03643 0.03017 -0.0222 0.2652 1.0000
14.500 1.6127 0.03762 0.03147 -0.0200 0.2616 1.0000
14.750 1.6292 0.03799 0.03184 -0.0192 0.2579 1.0000
15.000 1.6539 0.03826 0.03205 -0.0192 0.2539 1.0000
15.250 1.6280 0.04107 0.03515 -0.0157 0.2508 1.0000
15.500 1.6158 0.04348 0.03773 -0.0139 0.2469 1.0000
15.750 1.6244 0.04446 0.03874 -0.0132 0.2429 1.0000
16.000 1.6525 0.04419 0.03835 -0.0131 0.2386 1.0000
16.250 1.6163 0.04890 0.04338 -0.0114 0.2352 1.0000
16.500 1.5973 0.05267 0.04732 -0.0109 0.2309 1.0000
16.750 1.6083 0.05366 0.04832 -0.0107 0.2266 1.0000
17.000 1.6128 0.05542 0.05010 -0.0104 0.2223 1.0000
17.250 1.5689 0.06255 0.05751 -0.0112 0.2179 1.0000
17.500 1.5640 0.06561 0.06064 -0.0117 0.2130 1.0000
17.750 1.5865 0.06541 0.06035 -0.0113 0.2082 1.0000
18.000 1.5223 0.07619 0.07146 -0.0140 0.2033 1.0000
18.250 1.5188 0.07945 0.07476 -0.0149 0.1979 1.0000
18.500 1.5249 0.08140 0.07670 -0.0153 0.1927 1.0000
18.750 1.4553 0.09419 0.08974 -0.0195 0.1866 1.0000
19.000 1.5037 0.09012 0.08552 -0.0180 0.1812 1.0000
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Polar data table (+)
Polar graphs
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