EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 200,000 Max Cl/Cd: 57.63 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212mod-il-200000-n5.txt Download as CSV file: xf-e1212mod-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212MOD 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7227 0.08924 0.08436 -0.0337 1.0000 0.0451
-14.000 -0.7438 0.08252 0.07758 -0.0374 1.0000 0.0465
-13.750 -0.7696 0.07547 0.07045 -0.0413 1.0000 0.0470
-13.500 -0.8098 0.06659 0.06143 -0.0465 1.0000 0.0470
-13.250 -0.8594 0.05671 0.05137 -0.0525 1.0000 0.0460
-13.000 -0.9058 0.04707 0.04151 -0.0589 1.0000 0.0443
-12.750 -0.9441 0.03799 0.03216 -0.0663 1.0000 0.0436
-12.500 -0.9633 0.03351 0.02749 -0.0688 1.0000 0.0445
-12.250 -0.9747 0.03110 0.02496 -0.0677 1.0000 0.0462
-12.000 -0.9802 0.02952 0.02329 -0.0651 1.0000 0.0489
-11.750 -0.9787 0.02813 0.02184 -0.0630 1.0000 0.0519
-11.500 -0.9714 0.02696 0.02060 -0.0612 1.0000 0.0556
-11.250 -0.9624 0.02583 0.01942 -0.0594 1.0000 0.0596
-11.000 -0.9509 0.02484 0.01840 -0.0577 1.0000 0.0633
-10.750 -0.9376 0.02396 0.01748 -0.0561 1.0000 0.0677
-10.500 -0.9227 0.02311 0.01662 -0.0547 0.9993 0.0726
-10.250 -0.8881 0.02218 0.01566 -0.0569 0.9598 0.0789
-10.000 -0.8441 0.02137 0.01477 -0.0607 0.9095 0.0855
-9.750 -0.8043 0.02076 0.01404 -0.0634 0.8647 0.0925
-9.500 -0.7759 0.02037 0.01350 -0.0636 0.8324 0.0984
-9.250 -0.7504 0.02005 0.01301 -0.0632 0.8099 0.1036
-9.000 -0.7262 0.01978 0.01264 -0.0625 0.7926 0.1080
-8.750 -0.7019 0.01951 0.01220 -0.0618 0.7774 0.1128
-8.500 -0.6778 0.01931 0.01191 -0.0610 0.7626 0.1170
-8.250 -0.6531 0.01909 0.01154 -0.0603 0.7483 0.1218
-8.000 -0.6286 0.01890 0.01125 -0.0595 0.7344 0.1256
-7.750 -0.6038 0.01873 0.01096 -0.0588 0.7201 0.1295
-7.500 -0.5784 0.01853 0.01059 -0.0581 0.7054 0.1336
-7.250 -0.5536 0.01833 0.01034 -0.0574 0.6897 0.1369
-7.000 -0.5284 0.01819 0.01010 -0.0567 0.6727 0.1408
-6.750 -0.5029 0.01803 0.00976 -0.0560 0.6542 0.1447
-6.500 -0.4776 0.01781 0.00943 -0.0553 0.6347 0.1478
-6.250 -0.4523 0.01764 0.00918 -0.0546 0.6158 0.1510
-6.000 -0.4266 0.01751 0.00892 -0.0539 0.5991 0.1546
-5.750 -0.4006 0.01741 0.00863 -0.0533 0.5850 0.1585
-5.500 -0.3750 0.01721 0.00836 -0.0527 0.5727 0.1621
-5.250 -0.3489 0.01710 0.00820 -0.0522 0.5625 0.1663
-5.000 -0.3225 0.01702 0.00799 -0.0517 0.5530 0.1708
-4.750 -0.2957 0.01693 0.00774 -0.0512 0.5452 0.1740
-4.500 -0.2693 0.01663 0.00745 -0.0507 0.5373 0.1766
-4.250 -0.2429 0.01644 0.00720 -0.0502 0.5301 0.1790
-4.000 -0.2160 0.01628 0.00699 -0.0498 0.5237 0.1815
-3.750 -0.1888 0.01611 0.00676 -0.0493 0.5171 0.1839
-3.500 -0.1618 0.01597 0.00654 -0.0489 0.5106 0.1863
-3.250 -0.1347 0.01589 0.00633 -0.0484 0.5047 0.1889
-3.000 -0.1076 0.01568 0.00615 -0.0480 0.4986 0.1916
-2.750 -0.0807 0.01551 0.00599 -0.0476 0.4922 0.1944
-2.500 -0.0539 0.01541 0.00583 -0.0471 0.4861 0.1974
-2.250 -0.0266 0.01531 0.00569 -0.0467 0.4803 0.2007
-2.000 0.0010 0.01520 0.00556 -0.0463 0.4737 0.2045
-1.750 0.0279 0.01509 0.00544 -0.0458 0.4672 0.2087
-1.500 0.0547 0.01503 0.00535 -0.0454 0.4616 0.2137
-1.250 0.0823 0.01492 0.00527 -0.0450 0.4552 0.2194
-1.000 0.1096 0.01483 0.00520 -0.0446 0.4487 0.2256
-0.750 0.1366 0.01478 0.00515 -0.0442 0.4429 0.2334
-0.500 0.1640 0.01473 0.00512 -0.0438 0.4367 0.2425
-0.250 0.1915 0.01468 0.00512 -0.0434 0.4293 0.2541
0.000 0.2186 0.01466 0.00510 -0.0429 0.4226 0.2662
0.250 0.2462 0.01465 0.00509 -0.0426 0.4158 0.2785
0.500 0.2735 0.01464 0.00509 -0.0422 0.4084 0.2903
0.750 0.3005 0.01464 0.00506 -0.0417 0.4020 0.3002
1.000 0.3278 0.01464 0.00508 -0.0413 0.3950 0.3106
1.250 0.3548 0.01464 0.00508 -0.0408 0.3879 0.3198
1.500 0.3813 0.01466 0.00508 -0.0403 0.3818 0.3303
1.750 0.4083 0.01468 0.00513 -0.0399 0.3749 0.3404
2.000 0.4348 0.01471 0.00518 -0.0394 0.3682 0.3517
2.250 0.4610 0.01477 0.00523 -0.0388 0.3621 0.3628
2.500 0.4876 0.01482 0.00532 -0.0384 0.3557 0.3754
2.750 0.5136 0.01488 0.00541 -0.0378 0.3497 0.3890
3.000 0.5393 0.01498 0.00550 -0.0372 0.3446 0.4054
3.250 0.5656 0.01503 0.00565 -0.0367 0.3395 0.4259
3.500 0.5912 0.01509 0.00578 -0.0361 0.3345 0.4495
3.750 0.6161 0.01514 0.00591 -0.0353 0.3300 0.4791
4.000 0.6395 0.01512 0.00608 -0.0343 0.3260 0.5338
4.250 0.6608 0.01488 0.00633 -0.0328 0.3221 0.6486
4.500 0.6869 0.01465 0.00658 -0.0318 0.3180 0.8075
4.750 0.7657 0.01485 0.00690 -0.0416 0.3121 0.9923
5.250 0.8185 0.01538 0.00733 -0.0408 0.3056 1.0000
5.500 0.8420 0.01562 0.00755 -0.0399 0.3023 1.0000
5.750 0.8652 0.01588 0.00778 -0.0389 0.2989 1.0000
6.000 0.8883 0.01616 0.00801 -0.0379 0.2959 1.0000
6.250 0.9112 0.01646 0.00825 -0.0369 0.2931 1.0000
6.500 0.9343 0.01680 0.00852 -0.0359 0.2907 1.0000
6.750 0.9579 0.01708 0.00883 -0.0350 0.2884 1.0000
7.000 0.9814 0.01738 0.00915 -0.0341 0.2860 1.0000
7.250 1.0046 0.01769 0.00948 -0.0332 0.2837 1.0000
7.500 1.0278 0.01801 0.00980 -0.0323 0.2814 1.0000
7.750 1.0506 0.01835 0.01013 -0.0314 0.2793 1.0000
8.000 1.0733 0.01869 0.01045 -0.0305 0.2771 1.0000
8.250 1.0957 0.01907 0.01077 -0.0295 0.2747 1.0000
8.500 1.1178 0.01944 0.01116 -0.0285 0.2722 1.0000
8.750 1.1394 0.01978 0.01157 -0.0275 0.2696 1.0000
9.000 1.1607 0.02014 0.01197 -0.0264 0.2670 1.0000
9.250 1.1817 0.02051 0.01238 -0.0253 0.2646 1.0000
9.500 1.2021 0.02088 0.01276 -0.0242 0.2622 1.0000
9.750 1.2223 0.02128 0.01314 -0.0230 0.2598 1.0000
10.000 1.2427 0.02172 0.01353 -0.0219 0.2575 1.0000
10.250 1.2614 0.02216 0.01405 -0.0205 0.2556 1.0000
10.500 1.2792 0.02261 0.01459 -0.0191 0.2535 1.0000
10.750 1.2960 0.02308 0.01513 -0.0176 0.2513 1.0000
11.000 1.3106 0.02355 0.01566 -0.0157 0.2491 1.0000
11.250 1.3238 0.02403 0.01618 -0.0137 0.2468 1.0000
11.500 1.3372 0.02454 0.01671 -0.0118 0.2446 1.0000
11.750 1.3512 0.02508 0.01722 -0.0100 0.2422 1.0000
12.000 1.3632 0.02572 0.01792 -0.0083 0.2399 1.0000
12.250 1.3729 0.02648 0.01880 -0.0064 0.2377 1.0000
12.500 1.3827 0.02731 0.01973 -0.0048 0.2355 1.0000
12.750 1.3920 0.02821 0.02071 -0.0034 0.2331 1.0000
13.000 1.4012 0.02916 0.02174 -0.0021 0.2309 1.0000
13.250 1.4111 0.03014 0.02275 -0.0009 0.2287 1.0000
13.500 1.4219 0.03111 0.02371 0.0001 0.2264 1.0000
13.750 1.4287 0.03242 0.02511 0.0011 0.2241 1.0000
14.000 1.4311 0.03410 0.02694 0.0019 0.2213 1.0000
14.250 1.4336 0.03585 0.02882 0.0026 0.2183 1.0000
14.500 1.4365 0.03764 0.03068 0.0031 0.2153 1.0000
14.750 1.4413 0.03930 0.03238 0.0036 0.2125 1.0000
15.000 1.4450 0.04115 0.03426 0.0040 0.2096 1.0000
15.250 1.4389 0.04409 0.03738 0.0038 0.2063 1.0000
15.500 1.4321 0.04722 0.04065 0.0035 0.2022 1.0000
15.750 1.4294 0.04997 0.04347 0.0032 0.1987 1.0000
16.000 1.4252 0.05299 0.04653 0.0027 0.1950 1.0000
16.250 1.4072 0.05791 0.05166 0.0013 0.1902 1.0000
16.500 1.3948 0.06226 0.05608 0.0000 0.1850 1.0000
16.750 1.3775 0.06738 0.06132 -0.0017 0.1799 1.0000
17.000 1.3499 0.07409 0.06816 -0.0042 0.1733 1.0000
17.250 1.3248 0.08067 0.07484 -0.0067 0.1668 1.0000
17.500 1.2967 0.08792 0.08216 -0.0095 0.1597 1.0000
17.750 1.2722 0.09486 0.08917 -0.0123 0.1535 1.0000
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Polar data table (+)
Polar graphs
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