EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 500,000 Max Cl/Cd: 79.39 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1213-il-500000.txt Download as CSV file: xf-e1213-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1213 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9453 0.08688 0.08239 -0.0252 1.0000 0.0284
-16.250 -0.9515 0.08259 0.07807 -0.0272 1.0000 0.0288
-16.000 -0.9590 0.07818 0.07361 -0.0293 1.0000 0.0290
-15.750 -0.9693 0.07355 0.06892 -0.0316 1.0000 0.0291
-15.500 -0.9854 0.06832 0.06362 -0.0341 1.0000 0.0295
-15.250 -1.0028 0.06299 0.05821 -0.0367 1.0000 0.0296
-15.000 -1.0244 0.05713 0.05225 -0.0396 1.0000 0.0297
-14.750 -1.0471 0.05106 0.04606 -0.0427 1.0000 0.0298
-14.500 -1.0689 0.04494 0.03982 -0.0459 1.0000 0.0298
-14.250 -1.0886 0.03884 0.03357 -0.0496 1.0000 0.0299
-14.000 -1.1009 0.03386 0.02843 -0.0528 1.0000 0.0304
-13.750 -1.1114 0.02997 0.02441 -0.0546 1.0000 0.0306
-13.500 -1.1147 0.02762 0.02194 -0.0545 1.0000 0.0311
-13.250 -1.1237 0.02549 0.01972 -0.0528 1.0000 0.0316
-13.000 -1.1263 0.02410 0.01827 -0.0501 1.0000 0.0323
-12.750 -1.1265 0.02301 0.01713 -0.0469 1.0000 0.0332
-12.500 -1.1195 0.02209 0.01615 -0.0444 1.0000 0.0345
-12.250 -1.1101 0.02111 0.01513 -0.0422 1.0000 0.0362
-12.000 -1.0986 0.02017 0.01417 -0.0402 1.0000 0.0387
-11.750 -1.0864 0.01921 0.01321 -0.0382 1.0000 0.0429
-11.500 -1.0750 0.01813 0.01217 -0.0361 1.0000 0.0518
-11.250 -1.0628 0.01705 0.01119 -0.0341 1.0000 0.0658
-11.000 -1.0480 0.01616 0.01039 -0.0323 1.0000 0.0813
-10.750 -1.0299 0.01552 0.00982 -0.0308 1.0000 0.0939
-10.500 -1.0107 0.01499 0.00932 -0.0293 1.0000 0.1046
-10.250 -0.9906 0.01454 0.00892 -0.0280 1.0000 0.1138
-10.000 -0.9703 0.01413 0.00855 -0.0266 1.0000 0.1223
-9.750 -0.9494 0.01378 0.00823 -0.0253 1.0000 0.1296
-9.500 -0.9161 0.01349 0.00793 -0.0263 0.9950 0.1378
-9.250 -0.8735 0.01311 0.00760 -0.0294 0.9789 0.1466
-9.000 -0.8267 0.01279 0.00726 -0.0330 0.9431 0.1542
-8.750 -0.7809 0.01259 0.00696 -0.0363 0.8938 0.1618
-8.500 -0.7557 0.01251 0.00674 -0.0353 0.8481 0.1675
-8.250 -0.7311 0.01248 0.00658 -0.0344 0.8155 0.1733
-8.000 -0.7053 0.01247 0.00640 -0.0336 0.7887 0.1784
-7.750 -0.6803 0.01236 0.00624 -0.0328 0.7656 0.1838
-7.500 -0.6539 0.01234 0.00610 -0.0322 0.7449 0.1887
-7.250 -0.6270 0.01232 0.00595 -0.0316 0.7255 0.1929
-7.000 -0.6011 0.01217 0.00577 -0.0310 0.7079 0.1979
-6.750 -0.5739 0.01215 0.00568 -0.0306 0.6911 0.2027
-6.500 -0.5462 0.01218 0.00559 -0.0302 0.6754 0.2070
-6.250 -0.5198 0.01202 0.00539 -0.0296 0.6609 0.2118
-6.000 -0.4926 0.01198 0.00530 -0.0292 0.6465 0.2162
-5.750 -0.4649 0.01195 0.00520 -0.0289 0.6326 0.2202
-5.500 -0.4370 0.01195 0.00508 -0.0285 0.6199 0.2233
-5.250 -0.4102 0.01175 0.00484 -0.0280 0.6072 0.2273
-5.000 -0.3827 0.01163 0.00471 -0.0277 0.5949 0.2311
-4.750 -0.3551 0.01159 0.00459 -0.0273 0.5834 0.2345
-4.500 -0.3270 0.01154 0.00448 -0.0270 0.5718 0.2380
-4.250 -0.2989 0.01154 0.00438 -0.0267 0.5608 0.2408
-4.000 -0.2718 0.01133 0.00416 -0.0263 0.5498 0.2450
-3.750 -0.2441 0.01124 0.00406 -0.0260 0.5398 0.2488
-3.500 -0.2162 0.01120 0.00396 -0.0257 0.5292 0.2525
-3.250 -0.1879 0.01117 0.00388 -0.0255 0.5193 0.2560
-3.000 -0.1597 0.01118 0.00379 -0.0252 0.5094 0.2586
-2.750 -0.1323 0.01099 0.00363 -0.0248 0.5004 0.2635
-2.500 -0.1046 0.01094 0.00355 -0.0245 0.4907 0.2676
-2.250 -0.0764 0.01090 0.00349 -0.0243 0.4817 0.2714
-2.000 -0.0482 0.01090 0.00342 -0.0240 0.4727 0.2751
-1.750 -0.0203 0.01085 0.00334 -0.0238 0.4644 0.2793
-1.500 0.0074 0.01076 0.00326 -0.0234 0.4555 0.2843
-1.250 0.0352 0.01075 0.00322 -0.0232 0.4472 0.2889
-1.000 0.0636 0.01073 0.00318 -0.0230 0.4389 0.2934
-0.500 0.1192 0.01065 0.00310 -0.0224 0.4229 0.3046
-0.250 0.1470 0.01067 0.00308 -0.0221 0.4150 0.3104
0.000 0.1751 0.01067 0.00306 -0.0219 0.4076 0.3164
0.250 0.2027 0.01062 0.00305 -0.0216 0.3998 0.3244
0.500 0.2304 0.01067 0.00306 -0.0213 0.3923 0.3325
0.750 0.2583 0.01061 0.00306 -0.0210 0.3852 0.3418
1.000 0.2858 0.01065 0.00307 -0.0207 0.3778 0.3523
1.250 0.3134 0.01062 0.00311 -0.0205 0.3712 0.3653
1.500 0.3409 0.01060 0.00314 -0.0202 0.3645 0.3811
1.750 0.3678 0.01064 0.00319 -0.0198 0.3577 0.4003
2.000 0.3953 0.01059 0.00324 -0.0195 0.3515 0.4240
2.250 0.4223 0.01057 0.00330 -0.0192 0.3448 0.4525
2.500 0.4485 0.01058 0.00339 -0.0187 0.3386 0.4866
2.750 0.4753 0.01050 0.00347 -0.0183 0.3332 0.5281
3.000 0.5012 0.01044 0.00357 -0.0177 0.3273 0.5782
3.250 0.5258 0.01043 0.00370 -0.0169 0.3213 0.6358
3.500 0.5508 0.01028 0.00381 -0.0161 0.3161 0.7003
3.750 0.5741 0.01016 0.00394 -0.0149 0.3104 0.7742
4.000 0.5971 0.01012 0.00412 -0.0134 0.3047 0.8609
4.250 0.6511 0.01019 0.00436 -0.0183 0.2984 0.9430
4.500 0.6992 0.01040 0.00453 -0.0222 0.2918 0.9733
4.750 0.7403 0.01066 0.00472 -0.0248 0.2857 0.9886
5.000 0.7851 0.01079 0.00485 -0.0281 0.2796 0.9972
5.250 0.8182 0.01100 0.00499 -0.0292 0.2740 1.0000
5.500 0.8404 0.01124 0.00518 -0.0280 0.2694 1.0000
5.750 0.8641 0.01137 0.00533 -0.0271 0.2653 1.0000
6.000 0.8872 0.01156 0.00549 -0.0261 0.2608 1.0000
6.250 0.9094 0.01182 0.00570 -0.0250 0.2563 1.0000
6.500 0.9323 0.01206 0.00592 -0.0239 0.2523 1.0000
6.750 0.9560 0.01223 0.00611 -0.0231 0.2483 1.0000
7.000 0.9790 0.01245 0.00631 -0.0221 0.2440 1.0000
7.250 1.0007 0.01276 0.00656 -0.0209 0.2397 1.0000
7.500 1.0233 0.01302 0.00683 -0.0199 0.2362 1.0000
7.750 1.0467 0.01322 0.00706 -0.0190 0.2329 1.0000
8.000 1.0694 0.01347 0.00731 -0.0180 0.2294 1.0000
8.250 1.0910 0.01378 0.00759 -0.0169 0.2259 1.0000
8.500 1.1115 0.01420 0.00796 -0.0157 0.2221 1.0000
8.750 1.1348 0.01440 0.00822 -0.0148 0.2194 1.0000
9.000 1.1574 0.01465 0.00850 -0.0139 0.2163 1.0000
9.250 1.1791 0.01496 0.00881 -0.0128 0.2133 1.0000
9.500 1.1995 0.01533 0.00916 -0.0116 0.2104 1.0000
9.750 1.2183 0.01585 0.00964 -0.0103 0.2071 1.0000
10.000 1.2403 0.01610 0.00996 -0.0093 0.2052 1.0000
10.250 1.2613 0.01640 0.01031 -0.0082 0.2027 1.0000
10.500 1.2814 0.01673 0.01066 -0.0071 0.2001 1.0000
10.750 1.3001 0.01712 0.01106 -0.0057 0.1978 1.0000
11.000 1.3169 0.01759 0.01152 -0.0042 0.1952 1.0000
11.250 1.3311 0.01820 0.01210 -0.0023 0.1924 1.0000
11.500 1.3464 0.01853 0.01252 -0.0004 0.1908 1.0000
11.750 1.3608 0.01893 0.01298 0.0015 0.1888 1.0000
12.000 1.3747 0.01939 0.01349 0.0034 0.1867 1.0000
12.250 1.3879 0.01991 0.01405 0.0051 0.1846 1.0000
12.500 1.3998 0.02055 0.01470 0.0068 0.1825 1.0000
12.750 1.4102 0.02136 0.01550 0.0085 0.1801 1.0000
13.000 1.4218 0.02220 0.01637 0.0099 0.1780 1.0000
13.250 1.4339 0.02295 0.01721 0.0111 0.1763 1.0000
13.500 1.4454 0.02382 0.01816 0.0121 0.1743 1.0000
13.750 1.4562 0.02479 0.01918 0.0130 0.1722 1.0000
14.000 1.4662 0.02587 0.02031 0.0138 0.1701 1.0000
14.250 1.4750 0.02711 0.02156 0.0146 0.1681 1.0000
14.500 1.4828 0.02847 0.02290 0.0154 0.1654 1.0000
14.750 1.4912 0.02984 0.02438 0.0158 0.1637 1.0000
15.000 1.4993 0.03131 0.02595 0.0161 0.1620 1.0000
15.250 1.5064 0.03292 0.02764 0.0163 0.1598 1.0000
15.500 1.5124 0.03464 0.02943 0.0164 0.1577 1.0000
15.750 1.5172 0.03652 0.03133 0.0165 0.1556 1.0000
16.000 1.5204 0.03849 0.03330 0.0166 0.1531 1.0000
16.250 1.5239 0.04053 0.03541 0.0166 0.1511 1.0000
16.500 1.5259 0.04286 0.03786 0.0162 0.1492 1.0000
16.750 1.5262 0.04540 0.04050 0.0157 0.1467 1.0000
17.000 1.5268 0.04795 0.04311 0.0152 0.1446 1.0000
17.250 1.5253 0.05074 0.04593 0.0146 0.1423 1.0000
17.500 1.5253 0.05327 0.04844 0.0143 0.1397 1.0000
17.750 1.5216 0.05661 0.05193 0.0132 0.1378 1.0000
18.000 1.5185 0.05989 0.05532 0.0122 0.1356 1.0000
18.250 1.5143 0.06336 0.05887 0.0110 0.1331 1.0000
18.500 1.5088 0.06697 0.06251 0.0098 0.1307 1.0000
18.750 1.5045 0.07034 0.06586 0.0088 0.1279 1.0000
19.000 1.4947 0.07483 0.07051 0.0069 0.1255 1.0000
19.250 1.4864 0.07907 0.07485 0.0053 0.1228 1.0000
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