EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.64 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212mod-il-1000000-n5.txt Download as CSV file: xf-e1212mod-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8612 0.08559 0.08201 -0.0313 1.0000 0.0139
-15.000 -0.8875 0.07823 0.07456 -0.0354 1.0000 0.0138
-14.750 -0.9304 0.06896 0.06514 -0.0408 1.0000 0.0137
-14.500 -0.9903 0.05769 0.05368 -0.0476 1.0000 0.0136
-14.250 -1.0703 0.04335 0.03905 -0.0572 1.0000 0.0136
-14.000 -1.1114 0.03158 0.02695 -0.0685 1.0000 0.0135
-13.750 -1.1214 0.02766 0.02288 -0.0712 1.0000 0.0135
-13.500 -1.1251 0.02569 0.02080 -0.0703 1.0000 0.0135
-13.250 -1.0631 0.02369 0.01866 -0.0801 0.9270 0.0137
-13.000 -1.0552 0.02299 0.01749 -0.0783 0.8013 0.0138
-12.750 -1.0542 0.02227 0.01663 -0.0748 0.7787 0.0138
-12.500 -1.0444 0.02158 0.01582 -0.0725 0.7629 0.0139
-12.250 -1.0311 0.02091 0.01506 -0.0707 0.7510 0.0139
-12.000 -1.0158 0.02028 0.01434 -0.0691 0.7409 0.0140
-11.750 -0.9986 0.01968 0.01367 -0.0678 0.7325 0.0141
-11.500 -0.9800 0.01913 0.01305 -0.0665 0.7238 0.0142
-11.250 -0.9604 0.01862 0.01246 -0.0653 0.7162 0.0143
-11.000 -0.9397 0.01810 0.01190 -0.0643 0.7090 0.0144
-10.750 -0.9185 0.01763 0.01135 -0.0633 0.7004 0.0144
-10.500 -0.8965 0.01719 0.01085 -0.0624 0.6924 0.0145
-10.250 -0.8740 0.01675 0.01035 -0.0615 0.6814 0.0146
-10.000 -0.8517 0.01628 0.00981 -0.0606 0.6687 0.0148
-9.750 -0.8291 0.01586 0.00930 -0.0597 0.6496 0.0150
-9.500 -0.8058 0.01551 0.00884 -0.0588 0.6239 0.0152
-9.250 -0.7826 0.01521 0.00840 -0.0579 0.5896 0.0154
-9.000 -0.7588 0.01494 0.00800 -0.0571 0.5599 0.0156
-8.750 -0.7343 0.01467 0.00763 -0.0564 0.5396 0.0159
-8.500 -0.7093 0.01441 0.00728 -0.0558 0.5249 0.0162
-8.250 -0.6838 0.01415 0.00696 -0.0552 0.5144 0.0165
-7.750 -0.6318 0.01364 0.00636 -0.0541 0.5004 0.0173
-7.500 -0.6058 0.01335 0.00604 -0.0536 0.4952 0.0183
-7.250 -0.5798 0.01307 0.00572 -0.0531 0.4904 0.0197
-7.000 -0.5574 0.01233 0.00508 -0.0522 0.4856 0.0432
-6.750 -0.5313 0.01201 0.00478 -0.0517 0.4818 0.0510
-6.500 -0.5046 0.01172 0.00451 -0.0512 0.4785 0.0568
-6.250 -0.4782 0.01142 0.00423 -0.0508 0.4752 0.0647
-6.000 -0.4520 0.01108 0.00393 -0.0503 0.4714 0.0765
-5.750 -0.4259 0.01075 0.00367 -0.0498 0.4672 0.0928
-5.500 -0.3988 0.01054 0.00351 -0.0494 0.4628 0.1053
-5.250 -0.3707 0.01040 0.00339 -0.0491 0.4603 0.1133
-5.000 -0.3426 0.01026 0.00329 -0.0488 0.4571 0.1195
-4.750 -0.3141 0.01018 0.00319 -0.0486 0.4531 0.1233
-4.500 -0.2859 0.01009 0.00310 -0.0483 0.4481 0.1270
-4.250 -0.2577 0.01003 0.00301 -0.0480 0.4423 0.1307
-4.000 -0.2290 0.00997 0.00294 -0.0478 0.4386 0.1334
-3.750 -0.2003 0.00989 0.00285 -0.0476 0.4344 0.1358
-3.500 -0.1719 0.00981 0.00277 -0.0473 0.4288 0.1389
-3.250 -0.1435 0.00976 0.00270 -0.0471 0.4224 0.1416
-3.000 -0.1148 0.00971 0.00263 -0.0468 0.4174 0.1443
-2.750 -0.0859 0.00969 0.00258 -0.0466 0.4111 0.1462
-2.500 -0.0577 0.00963 0.00249 -0.0464 0.4035 0.1495
-2.250 -0.0293 0.00957 0.00244 -0.0461 0.3968 0.1525
-2.000 -0.0009 0.00954 0.00238 -0.0458 0.3883 0.1551
-1.750 0.0275 0.00954 0.00233 -0.0456 0.3803 0.1571
-1.500 0.0560 0.00953 0.00229 -0.0453 0.3718 0.1584
-1.250 0.0843 0.00956 0.00226 -0.0451 0.3627 0.1595
-1.000 0.1126 0.00954 0.00222 -0.0448 0.3549 0.1620
-0.750 0.1406 0.00956 0.00220 -0.0445 0.3462 0.1648
-0.500 0.1690 0.00955 0.00218 -0.0442 0.3405 0.1675
-0.250 0.1973 0.00955 0.00217 -0.0440 0.3341 0.1705
0.250 0.2539 0.00958 0.00217 -0.0434 0.3229 0.1778
0.500 0.2821 0.00958 0.00217 -0.0431 0.3177 0.1830
0.750 0.3101 0.00961 0.00219 -0.0429 0.3121 0.1884
1.000 0.3382 0.00961 0.00221 -0.0426 0.3074 0.1962
1.250 0.3664 0.00961 0.00222 -0.0423 0.3035 0.2057
1.500 0.3943 0.00959 0.00225 -0.0420 0.2989 0.2203
1.750 0.4220 0.00961 0.00230 -0.0417 0.2941 0.2385
2.000 0.4498 0.00962 0.00236 -0.0414 0.2900 0.2562
2.250 0.4780 0.00964 0.00242 -0.0411 0.2867 0.2701
2.500 0.5062 0.00969 0.00248 -0.0409 0.2826 0.2780
2.750 0.5340 0.00976 0.00255 -0.0406 0.2781 0.2862
3.000 0.5618 0.00985 0.00263 -0.0403 0.2735 0.2920
3.250 0.5901 0.00991 0.00269 -0.0400 0.2707 0.2959
3.500 0.6180 0.00996 0.00276 -0.0397 0.2674 0.3017
3.750 0.6457 0.01004 0.00284 -0.0394 0.2640 0.3070
4.000 0.6733 0.01013 0.00293 -0.0391 0.2605 0.3117
4.250 0.7008 0.01024 0.00302 -0.0387 0.2570 0.3165
4.500 0.7286 0.01028 0.00311 -0.0384 0.2552 0.3241
4.750 0.7562 0.01035 0.00320 -0.0381 0.2529 0.3309
5.250 0.8107 0.01050 0.00341 -0.0374 0.2478 0.3554
5.500 0.8373 0.01057 0.00355 -0.0369 0.2446 0.3780
5.750 0.8634 0.01064 0.00370 -0.0364 0.2410 0.4140
6.000 0.8901 0.01064 0.00382 -0.0360 0.2394 0.4545
6.250 0.9164 0.01066 0.00395 -0.0355 0.2370 0.4926
6.500 0.9411 0.01057 0.00411 -0.0348 0.2345 0.5900
6.750 0.9642 0.01043 0.00429 -0.0337 0.2327 0.7093
7.000 0.9883 0.01045 0.00444 -0.0328 0.2306 0.7564
7.500 1.0821 0.01047 0.00495 -0.0403 0.2250 0.9939
8.000 1.1377 0.01078 0.00527 -0.0399 0.2228 1.0000
8.250 1.1620 0.01094 0.00544 -0.0391 0.2209 1.0000
8.500 1.1861 0.01112 0.00561 -0.0382 0.2184 1.0000
8.750 1.2095 0.01133 0.00580 -0.0373 0.2154 1.0000
9.000 1.2327 0.01156 0.00602 -0.0363 0.2128 1.0000
9.250 1.2557 0.01179 0.00624 -0.0353 0.2106 1.0000
9.500 1.2798 0.01196 0.00643 -0.0344 0.2095 1.0000
9.750 1.3037 0.01214 0.00662 -0.0336 0.2081 1.0000
10.000 1.3272 0.01233 0.00683 -0.0327 0.2060 1.0000
10.250 1.3500 0.01255 0.00705 -0.0317 0.2033 1.0000
10.500 1.3720 0.01280 0.00730 -0.0306 0.2004 1.0000
10.750 1.3935 0.01307 0.00757 -0.0294 0.1981 1.0000
11.000 1.4146 0.01334 0.00785 -0.0283 0.1959 1.0000
11.250 1.4366 0.01356 0.00809 -0.0272 0.1943 1.0000
11.500 1.4577 0.01380 0.00835 -0.0260 0.1912 1.0000
11.750 1.4770 0.01410 0.00865 -0.0246 0.1875 1.0000
12.000 1.4922 0.01448 0.00901 -0.0225 0.1832 1.0000
12.250 1.5075 0.01479 0.00934 -0.0204 0.1790 1.0000
12.500 1.5192 0.01526 0.00978 -0.0179 0.1718 1.0000
12.750 1.5293 0.01583 0.01033 -0.0153 0.1625 1.0000
13.000 1.5322 0.01679 0.01121 -0.0123 0.1481 1.0000
13.250 1.5313 0.01811 0.01245 -0.0093 0.1351 1.0000
13.500 1.5329 0.01954 0.01386 -0.0073 0.1260 1.0000
13.750 1.5392 0.02092 0.01526 -0.0061 0.1209 1.0000
14.000 1.5452 0.02251 0.01687 -0.0054 0.1166 1.0000
14.250 1.5510 0.02424 0.01862 -0.0048 0.1125 1.0000
14.500 1.5580 0.02595 0.02037 -0.0044 0.1098 1.0000
14.750 1.5629 0.02788 0.02234 -0.0041 0.1074 1.0000
15.000 1.5663 0.02999 0.02450 -0.0039 0.1054 1.0000
15.250 1.5695 0.03217 0.02673 -0.0038 0.1033 1.0000
15.500 1.5728 0.03440 0.02903 -0.0038 0.1019 1.0000
15.750 1.5716 0.03714 0.03182 -0.0039 0.0996 1.0000
16.000 1.5684 0.04018 0.03492 -0.0042 0.0979 1.0000
16.250 1.5610 0.04371 0.03851 -0.0047 0.0960 1.0000
16.500 1.5558 0.04701 0.04190 -0.0051 0.0949 1.0000
16.750 1.5525 0.05016 0.04512 -0.0055 0.0941 1.0000
17.000 1.5469 0.05359 0.04863 -0.0061 0.0929 1.0000
17.250 1.5411 0.05706 0.05217 -0.0066 0.0919 1.0000
17.500 1.5328 0.06087 0.05605 -0.0073 0.0908 1.0000
17.750 1.5213 0.06509 0.06035 -0.0082 0.0896 1.0000
18.000 1.5091 0.06948 0.06481 -0.0092 0.0884 1.0000
18.250 1.4990 0.07367 0.06907 -0.0101 0.0876 1.0000
18.500 1.4860 0.07828 0.07375 -0.0112 0.0862 1.0000
18.750 1.4771 0.08245 0.07801 -0.0122 0.0856 1.0000
19.000 1.4687 0.08656 0.08219 -0.0133 0.0846 1.0000
19.250 1.4602 0.09070 0.08641 -0.0143 0.0837 1.0000
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Polar data table (+)
Polar graphs
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