EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 500,000 Max Cl/Cd: 84.21 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212mod-il-500000-n5.txt Download as CSV file: xf-e1212mod-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7937 0.08642 0.08215 -0.0328 1.0000 0.0178
-14.500 -0.8094 0.08057 0.07622 -0.0359 1.0000 0.0178
-14.250 -0.8393 0.07298 0.06853 -0.0402 1.0000 0.0179
-14.000 -0.8696 0.06556 0.06098 -0.0444 1.0000 0.0178
-13.750 -0.9035 0.05785 0.05313 -0.0489 1.0000 0.0176
-13.500 -0.9495 0.04850 0.04361 -0.0547 1.0000 0.0175
-13.250 -0.9902 0.03858 0.03344 -0.0621 1.0000 0.0174
-13.000 -1.0125 0.03126 0.02586 -0.0690 1.0000 0.0174
-12.750 -1.0252 0.02822 0.02268 -0.0693 1.0000 0.0174
-12.500 -1.0307 0.02660 0.02097 -0.0669 1.0000 0.0175
-12.250 -1.0324 0.02540 0.01969 -0.0639 1.0000 0.0176
-12.000 -1.0226 0.02424 0.01846 -0.0625 0.9976 0.0177
-11.750 -0.9549 0.02256 0.01654 -0.0723 0.8781 0.0181
-11.500 -0.9415 0.02195 0.01563 -0.0705 0.8175 0.0183
-11.250 -0.9277 0.02131 0.01482 -0.0687 0.7935 0.0186
-11.000 -0.9113 0.02072 0.01410 -0.0671 0.7771 0.0188
-10.750 -0.8932 0.02015 0.01341 -0.0658 0.7635 0.0190
-10.500 -0.8740 0.01959 0.01275 -0.0646 0.7529 0.0194
-10.250 -0.8537 0.01908 0.01215 -0.0635 0.7427 0.0197
-10.000 -0.8330 0.01853 0.01152 -0.0625 0.7336 0.0203
-9.750 -0.8120 0.01798 0.01090 -0.0615 0.7239 0.0211
-9.500 -0.7904 0.01746 0.01031 -0.0605 0.7143 0.0222
-9.250 -0.7705 0.01672 0.00955 -0.0594 0.7028 0.0272
-9.000 -0.7507 0.01593 0.00882 -0.0583 0.6914 0.0446
-8.750 -0.7272 0.01550 0.00835 -0.0575 0.6774 0.0505
-8.500 -0.7034 0.01509 0.00790 -0.0568 0.6609 0.0558
-8.250 -0.6793 0.01474 0.00747 -0.0560 0.6380 0.0603
-8.000 -0.6555 0.01441 0.00705 -0.0552 0.6099 0.0658
-7.750 -0.6316 0.01408 0.00663 -0.0544 0.5820 0.0733
-7.500 -0.6075 0.01374 0.00625 -0.0536 0.5607 0.0834
-7.250 -0.5825 0.01346 0.00596 -0.0530 0.5457 0.0956
-7.000 -0.5563 0.01327 0.00575 -0.0526 0.5344 0.1054
-6.750 -0.5295 0.01314 0.00558 -0.0521 0.5255 0.1121
-6.500 -0.5023 0.01300 0.00542 -0.0517 0.5184 0.1169
-6.250 -0.4749 0.01289 0.00526 -0.0513 0.5120 0.1214
-6.000 -0.4476 0.01280 0.00511 -0.0509 0.5058 0.1248
-5.750 -0.4199 0.01268 0.00498 -0.0506 0.5010 0.1285
-5.500 -0.3920 0.01259 0.00485 -0.0503 0.4960 0.1320
-5.250 -0.3642 0.01251 0.00471 -0.0499 0.4912 0.1347
-5.000 -0.3368 0.01240 0.00458 -0.0495 0.4862 0.1372
-4.750 -0.3090 0.01231 0.00446 -0.0492 0.4818 0.1401
-4.500 -0.2808 0.01223 0.00436 -0.0489 0.4778 0.1436
-4.250 -0.2524 0.01219 0.00427 -0.0486 0.4732 0.1464
-4.000 -0.2250 0.01205 0.00414 -0.0483 0.4683 0.1501
-3.750 -0.1973 0.01200 0.00405 -0.0479 0.4631 0.1538
-3.500 -0.1689 0.01193 0.00396 -0.0477 0.4587 0.1571
-3.250 -0.1405 0.01187 0.00386 -0.0474 0.4535 0.1591
-3.000 -0.1128 0.01175 0.00373 -0.0471 0.4480 0.1618
-2.750 -0.0851 0.01165 0.00362 -0.0467 0.4430 0.1643
-2.500 -0.0571 0.01157 0.00352 -0.0464 0.4386 0.1666
-2.250 -0.0288 0.01148 0.00343 -0.0461 0.4331 0.1687
-2.000 -0.0006 0.01141 0.00333 -0.0458 0.4265 0.1708
-1.750 0.0273 0.01138 0.00325 -0.0455 0.4204 0.1727
-1.500 0.0557 0.01132 0.00317 -0.0452 0.4145 0.1747
-1.250 0.0837 0.01124 0.00309 -0.0449 0.4072 0.1779
-1.000 0.1115 0.01119 0.00302 -0.0445 0.4002 0.1816
-0.750 0.1396 0.01114 0.00297 -0.0442 0.3927 0.1856
-0.500 0.1675 0.01114 0.00292 -0.0439 0.3846 0.1895
-0.250 0.1952 0.01110 0.00288 -0.0436 0.3773 0.1953
0.000 0.2229 0.01108 0.00286 -0.0432 0.3688 0.2019
0.250 0.2505 0.01108 0.00285 -0.0429 0.3613 0.2101
0.500 0.2781 0.01107 0.00285 -0.0425 0.3537 0.2215
0.750 0.3054 0.01109 0.00289 -0.0422 0.3464 0.2365
1.000 0.3331 0.01110 0.00294 -0.0418 0.3408 0.2529
1.250 0.3608 0.01112 0.00299 -0.0415 0.3347 0.2675
1.500 0.3883 0.01120 0.00305 -0.0411 0.3288 0.2783
1.750 0.4159 0.01125 0.00311 -0.0408 0.3239 0.2882
2.000 0.4439 0.01132 0.00316 -0.0405 0.3190 0.2950
2.250 0.4712 0.01137 0.00322 -0.0401 0.3138 0.3022
2.500 0.4982 0.01147 0.00330 -0.0397 0.3089 0.3091
2.750 0.5261 0.01154 0.00337 -0.0394 0.3052 0.3148
3.000 0.5535 0.01158 0.00345 -0.0390 0.3010 0.3219
3.250 0.5806 0.01166 0.00354 -0.0386 0.2967 0.3294
3.750 0.6345 0.01184 0.00374 -0.0377 0.2892 0.3475
4.250 0.6886 0.01197 0.00396 -0.0369 0.2819 0.3719
4.500 0.7149 0.01206 0.00410 -0.0364 0.2781 0.3917
4.750 0.7406 0.01214 0.00425 -0.0359 0.2746 0.4230
5.000 0.7667 0.01216 0.00439 -0.0354 0.2721 0.4598
5.250 0.7921 0.01212 0.00454 -0.0347 0.2696 0.5128
5.500 0.8158 0.01199 0.00471 -0.0338 0.2670 0.6113
5.750 0.8370 0.01182 0.00491 -0.0323 0.2645 0.7356
6.000 0.8781 0.01158 0.00521 -0.0345 0.2615 0.9376
6.250 0.9357 0.01188 0.00546 -0.0405 0.2577 0.9948
6.500 0.9658 0.01207 0.00565 -0.0408 0.2556 1.0000
6.750 0.9899 0.01224 0.00582 -0.0399 0.2532 1.0000
7.000 1.0137 0.01242 0.00600 -0.0389 0.2503 1.0000
7.250 1.0371 0.01263 0.00619 -0.0380 0.2477 1.0000
7.500 1.0603 0.01286 0.00640 -0.0370 0.2453 1.0000
7.750 1.0832 0.01311 0.00663 -0.0359 0.2433 1.0000
8.000 1.1056 0.01338 0.00688 -0.0348 0.2412 1.0000
8.250 1.1294 0.01358 0.00710 -0.0339 0.2397 1.0000
8.500 1.1530 0.01378 0.00733 -0.0330 0.2381 1.0000
8.750 1.1762 0.01400 0.00756 -0.0321 0.2360 1.0000
9.000 1.1989 0.01424 0.00781 -0.0311 0.2339 1.0000
9.250 1.2211 0.01450 0.00808 -0.0300 0.2318 1.0000
9.500 1.2427 0.01478 0.00836 -0.0289 0.2298 1.0000
9.750 1.2634 0.01509 0.00866 -0.0276 0.2279 1.0000
10.000 1.2831 0.01543 0.00900 -0.0263 0.2258 1.0000
10.250 1.3043 0.01569 0.00930 -0.0251 0.2244 1.0000
10.500 1.3253 0.01595 0.00960 -0.0239 0.2227 1.0000
10.750 1.3451 0.01623 0.00992 -0.0226 0.2206 1.0000
11.000 1.3622 0.01654 0.01026 -0.0208 0.2182 1.0000
11.250 1.3774 0.01688 0.01062 -0.0187 0.2161 1.0000
11.500 1.3903 0.01732 0.01105 -0.0164 0.2129 1.0000
11.750 1.4028 0.01782 0.01156 -0.0143 0.2103 1.0000
12.000 1.4200 0.01818 0.01198 -0.0128 0.2078 1.0000
12.250 1.4355 0.01864 0.01249 -0.0113 0.2056 1.0000
12.500 1.4498 0.01918 0.01307 -0.0097 0.2032 1.0000
12.750 1.4629 0.01983 0.01375 -0.0082 0.2007 1.0000
13.000 1.4739 0.02064 0.01458 -0.0067 0.1981 1.0000
13.250 1.4852 0.02151 0.01549 -0.0054 0.1955 1.0000
13.500 1.4996 0.02228 0.01633 -0.0045 0.1926 1.0000
13.750 1.5113 0.02328 0.01737 -0.0036 0.1882 1.0000
14.000 1.5190 0.02462 0.01874 -0.0027 0.1838 1.0000
14.250 1.5290 0.02587 0.02003 -0.0020 0.1791 1.0000
14.500 1.5357 0.02743 0.02162 -0.0014 0.1725 1.0000
14.750 1.5396 0.02929 0.02351 -0.0009 0.1658 1.0000
15.000 1.5371 0.03180 0.02601 -0.0005 0.1559 1.0000
15.250 1.5292 0.03496 0.02918 -0.0004 0.1465 1.0000
15.500 1.5163 0.03878 0.03301 -0.0006 0.1378 1.0000
15.750 1.5041 0.04269 0.03696 -0.0011 0.1321 1.0000
16.000 1.4902 0.04686 0.04118 -0.0017 0.1274 1.0000
16.250 1.4761 0.05115 0.04553 -0.0024 0.1240 1.0000
16.500 1.4647 0.05523 0.04968 -0.0031 0.1208 1.0000
16.750 1.4511 0.05963 0.05414 -0.0040 0.1181 1.0000
17.000 1.4337 0.06454 0.05910 -0.0051 0.1153 1.0000
17.250 1.4237 0.06866 0.06330 -0.0060 0.1135 1.0000
17.500 1.4153 0.07267 0.06739 -0.0070 0.1117 1.0000
17.750 1.4053 0.07696 0.07175 -0.0081 0.1100 1.0000
18.000 1.3937 0.08151 0.07637 -0.0093 0.1081 1.0000
18.250 1.3821 0.08611 0.08102 -0.0106 0.1063 1.0000
18.500 1.3696 0.09091 0.08587 -0.0120 0.1046 1.0000
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Polar data table (+)
Polar graphs
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