EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 500,000 Max Cl/Cd: 81.81 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212mod-il-500000.txt Download as CSV file: xf-e1212mod-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8374 0.08677 0.08264 -0.0338 1.0000 0.0260
-15.000 -0.8492 0.08157 0.07739 -0.0366 1.0000 0.0259
-14.750 -0.8702 0.07521 0.07095 -0.0401 1.0000 0.0259
-14.500 -0.8949 0.06859 0.06422 -0.0438 1.0000 0.0257
-14.250 -0.9367 0.05988 0.05536 -0.0490 1.0000 0.0257
-14.000 -0.9801 0.05101 0.04634 -0.0544 1.0000 0.0255
-13.750 -1.0235 0.04133 0.03644 -0.0611 1.0000 0.0252
-13.500 -1.0523 0.03253 0.02737 -0.0693 1.0000 0.0252
-13.250 -1.0666 0.02872 0.02339 -0.0711 1.0000 0.0253
-13.000 -1.0725 0.02683 0.02140 -0.0695 1.0000 0.0254
-12.750 -1.0764 0.02551 0.01999 -0.0665 1.0000 0.0256
-12.500 -1.0738 0.02437 0.01878 -0.0639 1.0000 0.0258
-12.250 -1.0664 0.02327 0.01762 -0.0618 1.0000 0.0262
-12.000 -1.0561 0.02229 0.01659 -0.0598 1.0000 0.0267
-11.750 -1.0435 0.02141 0.01566 -0.0580 1.0000 0.0273
-11.500 -1.0293 0.02061 0.01481 -0.0562 1.0000 0.0282
-11.250 -1.0148 0.01980 0.01399 -0.0545 1.0000 0.0296
-11.000 -0.9994 0.01904 0.01322 -0.0528 1.0000 0.0318
-10.750 -0.9842 0.01826 0.01247 -0.0510 1.0000 0.0364
-10.500 -0.9460 0.01723 0.01149 -0.0538 0.9789 0.0474
-10.250 -0.8967 0.01633 0.01059 -0.0586 0.9439 0.0567
-10.000 -0.8485 0.01555 0.00973 -0.0630 0.8881 0.0659
-9.750 -0.8251 0.01516 0.00917 -0.0622 0.8445 0.0727
-9.500 -0.8033 0.01478 0.00871 -0.0611 0.8204 0.0800
-9.000 -0.7565 0.01416 0.00800 -0.0592 0.7872 0.0958
-8.750 -0.7314 0.01394 0.00775 -0.0585 0.7740 0.1039
-8.500 -0.7059 0.01380 0.00756 -0.0579 0.7607 0.1114
-8.250 -0.6797 0.01366 0.00738 -0.0573 0.7471 0.1165
-8.000 -0.6532 0.01358 0.00722 -0.0567 0.7333 0.1215
-7.750 -0.6270 0.01348 0.00704 -0.0561 0.7178 0.1256
-7.500 -0.6001 0.01340 0.00692 -0.0556 0.7007 0.1298
-7.250 -0.5727 0.01339 0.00679 -0.0551 0.6815 0.1336
-7.000 -0.5467 0.01324 0.00658 -0.0545 0.6592 0.1371
-6.750 -0.5203 0.01319 0.00643 -0.0539 0.6341 0.1403
-6.500 -0.4934 0.01318 0.00628 -0.0533 0.6102 0.1433
-6.250 -0.4662 0.01321 0.00615 -0.0529 0.5911 0.1457
-6.000 -0.4400 0.01302 0.00590 -0.0523 0.5765 0.1487
-5.750 -0.4132 0.01293 0.00576 -0.0518 0.5652 0.1516
-5.500 -0.3857 0.01290 0.00567 -0.0515 0.5557 0.1545
-5.250 -0.3581 0.01290 0.00556 -0.0511 0.5476 0.1572
-5.000 -0.3300 0.01286 0.00545 -0.0508 0.5407 0.1591
-4.750 -0.3033 0.01264 0.00519 -0.0503 0.5338 0.1618
-4.500 -0.2765 0.01253 0.00505 -0.0498 0.5271 0.1651
-4.250 -0.2483 0.01246 0.00499 -0.0496 0.5221 0.1686
-4.000 -0.2201 0.01245 0.00492 -0.0493 0.5161 0.1721
-3.750 -0.1922 0.01246 0.00484 -0.0489 0.5099 0.1746
-3.500 -0.1656 0.01222 0.00462 -0.0485 0.5040 0.1790
-3.250 -0.1376 0.01209 0.00451 -0.0482 0.4989 0.1823
-3.000 -0.1097 0.01201 0.00440 -0.0478 0.4933 0.1853
-2.750 -0.0819 0.01196 0.00428 -0.0475 0.4879 0.1876
-2.500 -0.0539 0.01194 0.00419 -0.0471 0.4823 0.1893
-2.250 -0.0263 0.01170 0.00399 -0.0467 0.4776 0.1927
-2.000 0.0013 0.01155 0.00386 -0.0464 0.4720 0.1962
-1.750 0.0289 0.01148 0.00375 -0.0460 0.4663 0.1994
-1.500 0.0567 0.01145 0.00369 -0.0456 0.4607 0.2028
-1.250 0.0852 0.01136 0.00359 -0.0453 0.4556 0.2060
-1.000 0.1127 0.01119 0.00348 -0.0450 0.4498 0.2121
-0.750 0.1403 0.01113 0.00340 -0.0446 0.4438 0.2186
-0.500 0.1682 0.01105 0.00335 -0.0442 0.4379 0.2272
-0.250 0.1963 0.01094 0.00331 -0.0439 0.4313 0.2393
0.000 0.2240 0.01089 0.00328 -0.0436 0.4242 0.2558
0.250 0.2521 0.01086 0.00330 -0.0433 0.4172 0.2739
0.500 0.2802 0.01082 0.00330 -0.0430 0.4092 0.2889
0.750 0.3078 0.01085 0.00328 -0.0426 0.4013 0.3008
1.000 0.3361 0.01084 0.00329 -0.0423 0.3938 0.3116
1.250 0.3635 0.01086 0.00329 -0.0419 0.3858 0.3213
1.500 0.3911 0.01089 0.00332 -0.0416 0.3785 0.3311
1.750 0.4187 0.01092 0.00334 -0.0412 0.3710 0.3400
2.000 0.4454 0.01100 0.00340 -0.0407 0.3636 0.3495
2.250 0.4733 0.01103 0.00345 -0.0404 0.3574 0.3582
2.500 0.5002 0.01108 0.00352 -0.0399 0.3509 0.3692
2.750 0.5269 0.01121 0.00361 -0.0395 0.3445 0.3803
3.000 0.5543 0.01122 0.00370 -0.0391 0.3393 0.3951
3.250 0.5811 0.01127 0.00380 -0.0386 0.3338 0.4134
3.500 0.6069 0.01138 0.00392 -0.0381 0.3281 0.4376
3.750 0.6334 0.01138 0.00404 -0.0376 0.3237 0.4694
4.000 0.6588 0.01129 0.00416 -0.0369 0.3191 0.5258
4.250 0.6812 0.01110 0.00431 -0.0357 0.3146 0.6338
4.500 0.7016 0.01099 0.00451 -0.0339 0.3100 0.7576
4.750 0.7676 0.01082 0.00483 -0.0410 0.3051 0.9705
5.000 0.8230 0.01102 0.00501 -0.0464 0.3004 0.9990
5.250 0.8491 0.01123 0.00516 -0.0459 0.2970 1.0000
5.500 0.8719 0.01148 0.00535 -0.0447 0.2936 1.0000
5.750 0.8948 0.01176 0.00559 -0.0436 0.2903 1.0000
6.000 0.9192 0.01191 0.00575 -0.0427 0.2882 1.0000
6.250 0.9433 0.01208 0.00592 -0.0418 0.2856 1.0000
6.500 0.9673 0.01227 0.00610 -0.0408 0.2829 1.0000
6.750 0.9909 0.01247 0.00627 -0.0399 0.2800 1.0000
7.000 1.0138 0.01274 0.00649 -0.0388 0.2769 1.0000
7.250 1.0362 0.01311 0.00680 -0.0377 0.2736 1.0000
7.500 1.0605 0.01327 0.00700 -0.0368 0.2720 1.0000
7.750 1.0846 0.01348 0.00723 -0.0360 0.2703 1.0000
8.000 1.1084 0.01369 0.00745 -0.0351 0.2683 1.0000
8.250 1.1321 0.01390 0.00767 -0.0342 0.2660 1.0000
8.500 1.1554 0.01413 0.00790 -0.0332 0.2638 1.0000
8.750 1.1781 0.01440 0.00814 -0.0322 0.2614 1.0000
9.000 1.2004 0.01475 0.00847 -0.0312 0.2591 1.0000
9.250 1.2228 0.01516 0.00886 -0.0302 0.2569 1.0000
9.500 1.2459 0.01537 0.00913 -0.0293 0.2557 1.0000
9.750 1.2685 0.01560 0.00941 -0.0283 0.2542 1.0000
10.000 1.2908 0.01585 0.00969 -0.0273 0.2524 1.0000
10.250 1.3125 0.01610 0.00997 -0.0262 0.2504 1.0000
10.500 1.3336 0.01636 0.01025 -0.0250 0.2483 1.0000
10.750 1.3540 0.01666 0.01056 -0.0238 0.2462 1.0000
11.000 1.3730 0.01702 0.01090 -0.0223 0.2437 1.0000
11.250 1.3919 0.01750 0.01136 -0.0210 0.2408 1.0000
11.500 1.4078 0.01770 0.01164 -0.0190 0.2389 1.0000
11.750 1.4233 0.01799 0.01199 -0.0170 0.2370 1.0000
12.000 1.4384 0.01831 0.01236 -0.0150 0.2349 1.0000
12.250 1.4536 0.01868 0.01278 -0.0132 0.2329 1.0000
12.500 1.4680 0.01911 0.01323 -0.0114 0.2309 1.0000
12.750 1.4816 0.01963 0.01375 -0.0096 0.2287 1.0000
13.000 1.4949 0.02028 0.01439 -0.0080 0.2261 1.0000
13.250 1.5084 0.02085 0.01504 -0.0065 0.2242 1.0000
13.500 1.5214 0.02145 0.01574 -0.0051 0.2220 1.0000
13.750 1.5339 0.02215 0.01651 -0.0039 0.2193 1.0000
14.000 1.5457 0.02297 0.01738 -0.0028 0.2164 1.0000
14.250 1.5554 0.02399 0.01842 -0.0017 0.2135 1.0000
14.500 1.5641 0.02518 0.01960 -0.0007 0.2103 1.0000
14.750 1.5759 0.02623 0.02077 -0.0001 0.2078 1.0000
15.000 1.5865 0.02741 0.02205 0.0005 0.2043 1.0000
15.250 1.5943 0.02885 0.02353 0.0010 0.2006 1.0000
15.500 1.5965 0.03078 0.02545 0.0015 0.1964 1.0000
15.750 1.6055 0.03230 0.02710 0.0017 0.1919 1.0000
16.000 1.6078 0.03445 0.02930 0.0018 0.1862 1.0000
16.250 1.6065 0.03699 0.03188 0.0018 0.1805 1.0000
16.500 1.6024 0.03997 0.03491 0.0015 0.1725 1.0000
16.750 1.5934 0.04352 0.03850 0.0011 0.1643 1.0000
17.000 1.5751 0.04821 0.04320 0.0002 0.1555 1.0000
17.250 1.5546 0.05325 0.04826 -0.0009 0.1480 1.0000
17.500 1.5349 0.05827 0.05331 -0.0020 0.1424 1.0000
17.750 1.5138 0.06351 0.05858 -0.0032 0.1379 1.0000
18.000 1.4944 0.06868 0.06379 -0.0044 0.1341 1.0000
18.250 1.4806 0.07324 0.06840 -0.0055 0.1309 1.0000
18.500 1.4652 0.07810 0.07329 -0.0068 0.1279 1.0000
18.750 1.4519 0.08271 0.07791 -0.0080 0.1253 1.0000
19.000 1.4441 0.08675 0.08203 -0.0091 0.1230 1.0000
19.250 1.4390 0.09045 0.08579 -0.0101 0.1210 1.0000
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