EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 100,000 Max Cl/Cd: 43.3 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1230-il-100000-n5.txt Download as CSV file: xf-e1230-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4137 0.09636 0.09109 -0.0506 1.0000 0.0295
-11.750 -0.4811 0.07737 0.07200 -0.0617 1.0000 0.0286
-11.500 -0.5371 0.06608 0.06049 -0.0686 1.0000 0.0280
-11.250 -0.5756 0.05983 0.05405 -0.0705 1.0000 0.0277
-11.000 -0.6071 0.05550 0.04953 -0.0700 1.0000 0.0276
-10.750 -0.6353 0.05243 0.04631 -0.0674 1.0000 0.0276
-10.500 -0.6620 0.05026 0.04401 -0.0628 1.0000 0.0276
-10.250 -0.6812 0.04805 0.04164 -0.0584 1.0000 0.0277
-10.000 -0.6945 0.04587 0.03928 -0.0545 1.0000 0.0278
-9.750 -0.7039 0.04383 0.03704 -0.0506 1.0000 0.0281
-9.500 -0.6977 0.04127 0.03417 -0.0496 0.9967 0.0286
-9.250 -0.6719 0.03816 0.03058 -0.0518 0.9891 0.0294
-9.000 -0.6427 0.03581 0.02795 -0.0538 0.9810 0.0303
-8.750 -0.6121 0.03430 0.02636 -0.0557 0.9715 0.0315
-8.500 -0.5832 0.03272 0.02459 -0.0569 0.9604 0.0333
-8.250 -0.5550 0.03118 0.02288 -0.0579 0.9481 0.0353
-7.750 -0.4969 0.02849 0.01995 -0.0594 0.9223 0.0395
-7.500 -0.4672 0.02730 0.01877 -0.0603 0.9093 0.0417
-7.250 -0.4340 0.02615 0.01749 -0.0616 0.8969 0.0459
-7.000 -0.3977 0.02506 0.01636 -0.0636 0.8850 0.0508
-6.750 -0.3652 0.02403 0.01530 -0.0647 0.8697 0.0563
-6.500 -0.3316 0.02311 0.01432 -0.0660 0.8537 0.0643
-6.250 -0.2979 0.02226 0.01341 -0.0673 0.8369 0.0745
-6.000 -0.2651 0.02154 0.01261 -0.0684 0.8191 0.0870
-5.750 -0.2343 0.02091 0.01193 -0.0690 0.8006 0.1008
-5.500 -0.2059 0.02035 0.01134 -0.0693 0.7821 0.1158
-5.250 -0.1791 0.01985 0.01079 -0.0691 0.7641 0.1320
-5.000 -0.1536 0.01937 0.01029 -0.0687 0.7466 0.1499
-4.750 -0.1289 0.01891 0.00981 -0.0682 0.7300 0.1711
-4.500 -0.1049 0.01846 0.00936 -0.0675 0.7142 0.1981
-4.250 -0.0834 0.01797 0.00897 -0.0665 0.6985 0.2357
-4.000 -0.0632 0.01740 0.00860 -0.0652 0.6838 0.2924
-3.750 -0.0446 0.01678 0.00830 -0.0636 0.6706 0.3779
-3.500 -0.0259 0.01645 0.00840 -0.0615 0.6575 0.4822
-3.250 -0.0037 0.01654 0.00861 -0.0598 0.6441 0.5527
-3.000 0.0206 0.01674 0.00870 -0.0585 0.6321 0.5928
-2.750 0.0449 0.01694 0.00875 -0.0574 0.6198 0.6210
-2.500 0.0691 0.01713 0.00877 -0.0563 0.6079 0.6434
-2.000 0.1176 0.01737 0.00871 -0.0542 0.5856 0.6793
-1.750 0.1423 0.01746 0.00867 -0.0531 0.5758 0.6950
-1.500 0.1659 0.01753 0.00869 -0.0518 0.5650 0.7118
-1.250 0.1896 0.01760 0.00866 -0.0505 0.5558 0.7296
-1.000 0.2133 0.01763 0.00863 -0.0493 0.5458 0.7449
-0.750 0.2384 0.01765 0.00854 -0.0485 0.5372 0.7561
-0.500 0.2635 0.01767 0.00849 -0.0478 0.5276 0.7651
-0.250 0.2898 0.01771 0.00838 -0.0473 0.5198 0.7724
0.000 0.3154 0.01775 0.00837 -0.0469 0.5108 0.7795
0.250 0.3416 0.01781 0.00829 -0.0466 0.5033 0.7863
0.500 0.3681 0.01787 0.00830 -0.0463 0.4949 0.7920
0.750 0.3944 0.01794 0.00828 -0.0460 0.4871 0.7985
1.000 0.4214 0.01804 0.00828 -0.0459 0.4801 0.8043
1.250 0.4478 0.01814 0.00835 -0.0457 0.4725 0.8103
1.500 0.4743 0.01826 0.00837 -0.0455 0.4663 0.8172
1.750 0.5009 0.01839 0.00847 -0.0453 0.4594 0.8234
2.000 0.5271 0.01852 0.00858 -0.0451 0.4524 0.8307
2.250 0.5542 0.01867 0.00863 -0.0450 0.4467 0.8384
2.500 0.5807 0.01884 0.00883 -0.0448 0.4401 0.8469
2.750 0.6082 0.01902 0.00901 -0.0448 0.4340 0.8555
3.000 0.6372 0.01922 0.00915 -0.0452 0.4289 0.8656
3.500 0.6952 0.01968 0.00965 -0.0460 0.4168 0.8969
3.750 0.7286 0.01993 0.00984 -0.0473 0.4115 0.9128
4.250 0.8008 0.02056 0.01051 -0.0514 0.4005 0.9542
4.500 0.8387 0.02087 0.01077 -0.0539 0.3952 0.9788
5.000 0.8918 0.02154 0.01137 -0.0546 0.3860 1.0000
5.250 0.9115 0.02188 0.01170 -0.0534 0.3814 1.0000
5.500 0.9332 0.02222 0.01200 -0.0526 0.3775 1.0000
5.750 0.9566 0.02257 0.01226 -0.0521 0.3742 1.0000
6.000 0.9777 0.02300 0.01270 -0.0512 0.3702 1.0000
6.250 0.9976 0.02344 0.01319 -0.0502 0.3657 1.0000
6.500 1.0190 0.02384 0.01361 -0.0493 0.3616 1.0000
6.750 1.0420 0.02422 0.01395 -0.0488 0.3581 1.0000
7.000 1.0670 0.02464 0.01427 -0.0486 0.3552 1.0000
7.250 1.0847 0.02521 0.01500 -0.0472 0.3514 1.0000
7.500 1.1037 0.02575 0.01561 -0.0461 0.3475 1.0000
7.750 1.1244 0.02622 0.01611 -0.0453 0.3438 1.0000
8.000 1.1470 0.02665 0.01653 -0.0447 0.3405 1.0000
8.250 1.1720 0.02709 0.01691 -0.0445 0.3378 1.0000
8.500 1.1862 0.02782 0.01781 -0.0428 0.3342 1.0000
8.750 1.2024 0.02851 0.01862 -0.0414 0.3307 1.0000
9.000 1.2204 0.02912 0.01930 -0.0403 0.3274 1.0000
9.250 1.2409 0.02963 0.01983 -0.0395 0.3243 1.0000
9.500 1.2646 0.03009 0.02026 -0.0392 0.3215 1.0000
9.750 1.2788 0.03087 0.02116 -0.0376 0.3185 1.0000
10.000 1.2873 0.03182 0.02229 -0.0353 0.3152 1.0000
10.250 1.2978 0.03267 0.02326 -0.0333 0.3120 1.0000
10.500 1.3120 0.03339 0.02406 -0.0318 0.3090 1.0000
10.750 1.3311 0.03395 0.02463 -0.0309 0.3062 1.0000
11.000 1.3567 0.03439 0.02504 -0.0309 0.3037 1.0000
11.250 1.3521 0.03585 0.02674 -0.0274 0.3006 1.0000
11.500 1.3484 0.03741 0.02851 -0.0243 0.2973 1.0000
11.750 1.3508 0.03878 0.03001 -0.0221 0.2941 1.0000
12.000 1.3620 0.03975 0.03105 -0.0209 0.2912 1.0000
12.250 1.3836 0.04022 0.03152 -0.0205 0.2886 1.0000
12.500 1.3949 0.04130 0.03268 -0.0193 0.2859 1.0000
12.750 1.3588 0.04528 0.03698 -0.0157 0.2820 1.0000
13.000 1.3324 0.04931 0.04122 -0.0138 0.2779 1.0000
13.250 1.3359 0.05116 0.04315 -0.0131 0.2746 1.0000
13.500 1.3655 0.05078 0.04276 -0.0128 0.2721 1.0000
13.750 1.0907 0.08699 0.07945 -0.0197 0.2525 1.0000
14.000 1.1383 0.08299 0.07548 -0.0178 0.2533 1.0000
14.250 1.1921 0.07833 0.07085 -0.0158 0.2539 1.0000
14.500 1.2618 0.07194 0.06447 -0.0135 0.2545 1.0000
16.000 0.9878 0.13479 0.12779 -0.0345 0.1963 1.0000
16.250 0.9654 0.14267 0.13573 -0.0380 0.1873 1.0000
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