EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 100,000 Max Cl/Cd: 41.91 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212-il-100000-n5.txt Download as CSV file: xf-e1212-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5341 0.10789 0.10205 -0.0305 1.0000 0.0774
-13.500 -0.5066 0.10606 0.10024 -0.0308 1.0000 0.0821
-13.250 -0.6178 0.08267 0.07680 -0.0438 1.0000 0.0927
-13.000 -0.5644 0.08850 0.08270 -0.0398 1.0000 0.0937
-12.750 -0.7027 0.06364 0.05769 -0.0549 1.0000 0.1007
-12.500 -0.6275 0.07213 0.06634 -0.0487 1.0000 0.1036
-12.250 -0.7747 0.04794 0.04186 -0.0653 1.0000 0.1053
-12.000 -0.8131 0.04115 0.03490 -0.0698 1.0000 0.1069
-11.750 -0.8390 0.03770 0.03129 -0.0693 1.0000 0.1091
-11.500 -0.8467 0.03590 0.02943 -0.0673 1.0000 0.1123
-11.250 -0.8427 0.03487 0.02839 -0.0656 1.0000 0.1163
-11.000 -0.8438 0.03311 0.02643 -0.0638 1.0000 0.1212
-10.750 -0.8302 0.03280 0.02621 -0.0622 1.0000 0.1251
-10.500 -0.8229 0.03170 0.02496 -0.0604 1.0000 0.1303
-10.250 -0.8098 0.03119 0.02446 -0.0587 1.0000 0.1345
-10.000 -0.7965 0.03074 0.02399 -0.0570 1.0000 0.1392
-9.750 -0.7881 0.02972 0.02280 -0.0551 1.0000 0.1442
-9.500 -0.7581 0.02972 0.02290 -0.0558 0.9929 0.1488
-9.250 -0.7243 0.02854 0.02139 -0.0585 0.9719 0.1561
-9.000 -0.6846 0.02856 0.02151 -0.0605 0.9517 0.1606
-8.750 -0.6476 0.02775 0.02047 -0.0630 0.9296 0.1671
-8.500 -0.6073 0.02726 0.01989 -0.0655 0.9084 0.1722
-8.250 -0.5673 0.02690 0.01942 -0.0678 0.8862 0.1774
-8.000 -0.5343 0.02593 0.01804 -0.0693 0.8624 0.1837
-7.500 -0.4725 0.02550 0.01746 -0.0699 0.8167 0.1917
-7.250 -0.4479 0.02489 0.01652 -0.0695 0.7958 0.1971
-7.000 -0.4220 0.02452 0.01602 -0.0690 0.7769 0.2008
-6.750 -0.3959 0.02433 0.01576 -0.0684 0.7586 0.2044
-6.500 -0.3706 0.02400 0.01526 -0.0678 0.7415 0.2088
-6.250 -0.3459 0.02350 0.01445 -0.0673 0.7257 0.2139
-6.000 -0.3196 0.02319 0.01407 -0.0668 0.7109 0.2174
-5.750 -0.2934 0.02296 0.01378 -0.0662 0.6965 0.2210
-5.500 -0.2675 0.02267 0.01336 -0.0657 0.6825 0.2254
-5.250 -0.2418 0.02233 0.01275 -0.0651 0.6698 0.2303
-5.000 -0.2158 0.02200 0.01233 -0.0646 0.6567 0.2340
-4.750 -0.1894 0.02178 0.01208 -0.0641 0.6445 0.2377
-4.500 -0.1632 0.02156 0.01174 -0.0636 0.6328 0.2420
-4.250 -0.1368 0.02130 0.01134 -0.0631 0.6208 0.2467
-4.000 -0.1104 0.02105 0.01088 -0.0626 0.6105 0.2510
-3.750 -0.0839 0.02083 0.01069 -0.0622 0.5987 0.2548
-3.250 -0.0307 0.02047 0.01016 -0.0612 0.5779 0.2640
-3.000 -0.0038 0.02032 0.00978 -0.0608 0.5688 0.2689
-2.750 0.0227 0.02011 0.00964 -0.0603 0.5580 0.2729
-2.500 0.0494 0.01998 0.00944 -0.0598 0.5493 0.2776
-2.250 0.0762 0.01986 0.00927 -0.0595 0.5393 0.2827
-2.000 0.1032 0.01976 0.00901 -0.0590 0.5305 0.2882
-1.750 0.1297 0.01962 0.00891 -0.0586 0.5214 0.2929
-1.500 0.1564 0.01953 0.00879 -0.0581 0.5126 0.2983
-1.250 0.1833 0.01946 0.00865 -0.0577 0.5045 0.3043
-1.000 0.2100 0.01939 0.00856 -0.0573 0.4956 0.3103
-0.750 0.2366 0.01933 0.00846 -0.0568 0.4885 0.3164
-0.500 0.2632 0.01930 0.00845 -0.0563 0.4797 0.3236
-0.250 0.2899 0.01926 0.00837 -0.0559 0.4721 0.3307
0.000 0.3162 0.01923 0.00836 -0.0554 0.4648 0.3383
0.250 0.3427 0.01925 0.00837 -0.0549 0.4568 0.3478
0.500 0.3690 0.01923 0.00835 -0.0544 0.4503 0.3571
0.750 0.3953 0.01926 0.00842 -0.0540 0.4428 0.3684
1.000 0.4213 0.01926 0.00848 -0.0534 0.4355 0.3801
1.500 0.4737 0.01936 0.00865 -0.0525 0.4222 0.4123
1.750 0.4997 0.01939 0.00875 -0.0520 0.4156 0.4330
2.000 0.5257 0.01943 0.00880 -0.0514 0.4101 0.4580
2.250 0.5507 0.01949 0.00906 -0.0508 0.4030 0.4888
2.500 0.5758 0.01951 0.00922 -0.0501 0.3969 0.5286
2.750 0.6008 0.01952 0.00932 -0.0493 0.3919 0.5795
3.000 0.6238 0.01954 0.00965 -0.0482 0.3853 0.6423
3.250 0.6459 0.01950 0.00988 -0.0466 0.3795 0.7228
3.500 0.6726 0.01943 0.01003 -0.0456 0.3745 0.8348
3.750 0.7253 0.01961 0.01034 -0.0503 0.3669 1.0000
4.000 0.7490 0.01991 0.01056 -0.0495 0.3613 1.0000
4.250 0.7734 0.02020 0.01071 -0.0489 0.3567 1.0000
4.500 0.7972 0.02056 0.01102 -0.0482 0.3518 1.0000
4.750 0.8205 0.02093 0.01138 -0.0474 0.3463 1.0000
5.000 0.8443 0.02126 0.01164 -0.0468 0.3414 1.0000
5.250 0.8690 0.02159 0.01183 -0.0462 0.3373 1.0000
5.500 0.8914 0.02204 0.01232 -0.0453 0.3322 1.0000
5.750 0.9142 0.02246 0.01274 -0.0446 0.3274 1.0000
6.000 0.9378 0.02284 0.01307 -0.0439 0.3232 1.0000
6.250 0.9624 0.02321 0.01332 -0.0433 0.3196 1.0000
6.500 0.9831 0.02374 0.01394 -0.0424 0.3147 1.0000
6.750 1.0048 0.02422 0.01445 -0.0415 0.3100 1.0000
7.000 1.0273 0.02465 0.01485 -0.0407 0.3061 1.0000
7.250 1.0511 0.02508 0.01518 -0.0401 0.3029 1.0000
7.500 1.0713 0.02569 0.01586 -0.0391 0.2990 1.0000
7.750 1.0905 0.02630 0.01654 -0.0381 0.2947 1.0000
8.000 1.1110 0.02683 0.01708 -0.0371 0.2908 1.0000
8.250 1.1329 0.02729 0.01751 -0.0363 0.2874 1.0000
8.500 1.1549 0.02783 0.01799 -0.0356 0.2844 1.0000
8.750 1.1697 0.02865 0.01896 -0.0341 0.2806 1.0000
9.000 1.1861 0.02939 0.01978 -0.0328 0.2770 1.0000
9.250 1.2039 0.03003 0.02045 -0.0316 0.2738 1.0000
9.500 1.2240 0.03057 0.02096 -0.0307 0.2709 1.0000
9.750 1.2453 0.03115 0.02149 -0.0300 0.2682 1.0000
10.000 1.2510 0.03225 0.02278 -0.0277 0.2647 1.0000
10.250 1.2580 0.03324 0.02388 -0.0254 0.2616 1.0000
10.500 1.2680 0.03416 0.02486 -0.0236 0.2588 1.0000
10.750 1.2816 0.03495 0.02568 -0.0221 0.2562 1.0000
11.000 1.3003 0.03558 0.02627 -0.0213 0.2538 1.0000
11.250 1.3099 0.03665 0.02739 -0.0197 0.2514 1.0000
11.500 1.2997 0.03868 0.02963 -0.0171 0.2484 1.0000
11.750 1.2940 0.04072 0.03183 -0.0154 0.2455 1.0000
12.000 1.2942 0.04258 0.03379 -0.0142 0.2428 1.0000
12.250 1.3028 0.04396 0.03521 -0.0135 0.2404 1.0000
12.500 1.3208 0.04473 0.03596 -0.0129 0.2383 1.0000
12.750 1.3289 0.04627 0.03754 -0.0123 0.2361 1.0000
13.000 1.2465 0.05595 0.04768 -0.0130 0.2319 1.0000
13.250 1.0572 0.08355 0.07575 -0.0236 0.2197 1.0000
13.500 1.1063 0.07951 0.07166 -0.0211 0.2204 1.0000
13.750 1.1641 0.07455 0.06664 -0.0181 0.2209 1.0000
15.250 0.8845 0.14581 0.13854 -0.0505 0.1720 1.0000
15.500 0.8956 0.14774 0.14050 -0.0511 0.1697 1.0000
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