EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.07 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1213-il-1000000-n5.txt Download as CSV file: xf-e1213-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0089 0.08885 0.08495 -0.0242 1.0000 0.0156
-17.000 -1.0232 0.08340 0.07942 -0.0269 1.0000 0.0156
-16.750 -1.0450 0.07697 0.07291 -0.0301 1.0000 0.0156
-16.500 -1.0736 0.06999 0.06581 -0.0337 1.0000 0.0157
-16.250 -1.1086 0.06227 0.05795 -0.0377 1.0000 0.0157
-16.000 -1.1423 0.05472 0.05026 -0.0417 1.0000 0.0156
-15.750 -1.1748 0.04711 0.04249 -0.0458 1.0000 0.0155
-15.500 -1.2015 0.03992 0.03512 -0.0503 1.0000 0.0156
-15.250 -1.2164 0.03428 0.02933 -0.0541 1.0000 0.0156
-15.000 -1.2252 0.03009 0.02501 -0.0566 1.0000 0.0157
-14.750 -1.2297 0.02724 0.02206 -0.0574 1.0000 0.0159
-14.500 -1.2309 0.02528 0.02001 -0.0568 1.0000 0.0160
-14.250 -1.2301 0.02383 0.01849 -0.0552 1.0000 0.0161
-14.000 -1.2270 0.02272 0.01733 -0.0530 1.0000 0.0163
-13.750 -1.2223 0.02185 0.01640 -0.0504 1.0000 0.0165
-13.500 -1.2165 0.02112 0.01562 -0.0475 1.0000 0.0167
-13.250 -1.2059 0.02046 0.01492 -0.0451 1.0000 0.0169
-13.000 -1.1915 0.01984 0.01426 -0.0434 1.0000 0.0171
-12.750 -1.1755 0.01926 0.01364 -0.0417 1.0000 0.0174
-12.500 -1.1583 0.01871 0.01306 -0.0402 1.0000 0.0176
-12.250 -1.1413 0.01813 0.01245 -0.0386 1.0000 0.0181
-12.000 -1.1236 0.01756 0.01187 -0.0371 1.0000 0.0186
-11.750 -1.1003 0.01702 0.01130 -0.0366 0.9950 0.0191
-11.500 -1.0447 0.01635 0.01050 -0.0426 0.8989 0.0201
-11.250 -1.0265 0.01615 0.01006 -0.0407 0.8329 0.0206
-11.000 -1.0068 0.01579 0.00957 -0.0393 0.7971 0.0217
-10.750 -0.9854 0.01544 0.00911 -0.0381 0.7694 0.0229
-10.500 -0.9636 0.01505 0.00864 -0.0371 0.7462 0.0250
-10.250 -0.9415 0.01465 0.00817 -0.0361 0.7252 0.0282
-10.000 -0.9197 0.01415 0.00765 -0.0351 0.7062 0.0350
-9.750 -0.8974 0.01366 0.00715 -0.0341 0.6893 0.0434
-9.500 -0.8745 0.01319 0.00667 -0.0333 0.6733 0.0523
-9.250 -0.8508 0.01278 0.00625 -0.0325 0.6585 0.0611
-9.000 -0.8268 0.01238 0.00585 -0.0317 0.6439 0.0706
-8.750 -0.8025 0.01197 0.00547 -0.0311 0.6299 0.0818
-8.500 -0.7775 0.01163 0.00514 -0.0304 0.6173 0.0923
-8.250 -0.7521 0.01133 0.00484 -0.0299 0.6045 0.1020
-8.000 -0.7262 0.01105 0.00457 -0.0294 0.5915 0.1118
-7.750 -0.6999 0.01080 0.00433 -0.0289 0.5807 0.1208
-7.500 -0.6732 0.01061 0.00412 -0.0285 0.5688 0.1283
-7.250 -0.6461 0.01043 0.00393 -0.0281 0.5578 0.1354
-6.750 -0.5915 0.01013 0.00360 -0.0274 0.5363 0.1488
-6.500 -0.5641 0.00999 0.00344 -0.0270 0.5256 0.1552
-6.250 -0.5363 0.00987 0.00331 -0.0267 0.5164 0.1617
-6.000 -0.5087 0.00977 0.00318 -0.0264 0.5060 0.1681
-5.750 -0.4806 0.00966 0.00308 -0.0262 0.4967 0.1740
-5.500 -0.4524 0.00962 0.00297 -0.0259 0.4873 0.1773
-5.250 -0.4244 0.00951 0.00287 -0.0256 0.4787 0.1830
-4.750 -0.3677 0.00940 0.00270 -0.0252 0.4608 0.1916
-4.500 -0.3394 0.00935 0.00261 -0.0250 0.4520 0.1951
-4.250 -0.3111 0.00928 0.00253 -0.0247 0.4440 0.1986
-4.000 -0.2827 0.00925 0.00246 -0.0245 0.4349 0.2020
-3.750 -0.2541 0.00922 0.00240 -0.0243 0.4278 0.2050
-3.500 -0.2254 0.00919 0.00233 -0.0242 0.4202 0.2072
-3.250 -0.1970 0.00917 0.00227 -0.0239 0.4116 0.2103
-3.000 -0.1685 0.00912 0.00222 -0.0238 0.4046 0.2142
-2.750 -0.1400 0.00910 0.00217 -0.0236 0.3972 0.2174
-2.500 -0.1113 0.00909 0.00213 -0.0234 0.3905 0.2202
-2.250 -0.0826 0.00908 0.00210 -0.0232 0.3828 0.2228
-2.000 -0.0541 0.00909 0.00207 -0.0230 0.3751 0.2255
-1.750 -0.0255 0.00906 0.00203 -0.0229 0.3695 0.2292
-1.500 0.0030 0.00905 0.00201 -0.0227 0.3620 0.2326
-1.250 0.0316 0.00906 0.00200 -0.0225 0.3550 0.2361
-1.000 0.0603 0.00907 0.00198 -0.0224 0.3486 0.2391
-0.750 0.0889 0.00910 0.00198 -0.0222 0.3412 0.2412
-0.500 0.1174 0.00910 0.00197 -0.0220 0.3350 0.2455
-0.250 0.1458 0.00910 0.00197 -0.0219 0.3281 0.2499
0.000 0.1742 0.00914 0.00198 -0.0217 0.3212 0.2539
0.250 0.2029 0.00916 0.00199 -0.0216 0.3157 0.2570
0.500 0.2314 0.00919 0.00200 -0.0214 0.3101 0.2603
0.750 0.2596 0.00922 0.00203 -0.0212 0.3041 0.2661
1.000 0.2882 0.00924 0.00206 -0.0211 0.2991 0.2713
1.250 0.3165 0.00929 0.00209 -0.0209 0.2927 0.2757
1.500 0.3447 0.00934 0.00213 -0.0207 0.2870 0.2809
1.750 0.3731 0.00935 0.00217 -0.0206 0.2831 0.2871
2.000 0.4015 0.00940 0.00221 -0.0204 0.2783 0.2936
2.250 0.4295 0.00945 0.00227 -0.0202 0.2728 0.3017
2.500 0.4576 0.00949 0.00233 -0.0200 0.2682 0.3106
2.750 0.4857 0.00954 0.00239 -0.0199 0.2630 0.3189
3.000 0.5136 0.00960 0.00246 -0.0196 0.2579 0.3296
3.250 0.5414 0.00966 0.00255 -0.0194 0.2534 0.3406
3.500 0.5695 0.00970 0.00262 -0.0193 0.2500 0.3536
3.750 0.5972 0.00973 0.00271 -0.0190 0.2457 0.3713
4.000 0.6245 0.00980 0.00281 -0.0188 0.2408 0.3903
4.250 0.6519 0.00985 0.00291 -0.0185 0.2365 0.4097
4.500 0.6794 0.00989 0.00301 -0.0183 0.2325 0.4313
4.750 0.7066 0.00995 0.00312 -0.0180 0.2281 0.4554
5.000 0.7333 0.01001 0.00326 -0.0177 0.2238 0.4857
5.250 0.7602 0.01003 0.00338 -0.0174 0.2207 0.5221
5.500 0.7869 0.01004 0.00351 -0.0170 0.2174 0.5615
5.750 0.8132 0.01008 0.00365 -0.0166 0.2137 0.6028
6.000 0.8389 0.01013 0.00381 -0.0161 0.2095 0.6474
6.500 0.8889 0.01013 0.00414 -0.0148 0.2028 0.7597
6.750 0.9110 0.01004 0.00431 -0.0134 0.1997 0.8448
7.000 0.9473 0.01007 0.00457 -0.0149 0.1958 0.9475
7.250 0.9920 0.01031 0.00480 -0.0184 0.1920 0.9787
7.500 1.0286 0.01049 0.00499 -0.0202 0.1894 0.9885
7.750 1.0616 0.01070 0.00518 -0.0212 0.1864 0.9957
8.000 1.0959 0.01094 0.00540 -0.0226 0.1828 0.9999
8.250 1.1192 0.01119 0.00562 -0.0217 0.1795 1.0000
8.500 1.1427 0.01138 0.00582 -0.0208 0.1775 1.0000
8.750 1.1663 0.01157 0.00602 -0.0200 0.1757 1.0000
9.000 1.1896 0.01177 0.00624 -0.0191 0.1737 1.0000
9.250 1.2125 0.01200 0.00646 -0.0181 0.1714 1.0000
9.500 1.2349 0.01226 0.00671 -0.0171 0.1688 1.0000
9.750 1.2568 0.01254 0.00699 -0.0161 0.1661 1.0000
10.000 1.2792 0.01278 0.00725 -0.0152 0.1643 1.0000
10.250 1.3020 0.01301 0.00749 -0.0143 0.1628 1.0000
10.500 1.3244 0.01325 0.00775 -0.0133 0.1610 1.0000
10.750 1.3461 0.01352 0.00803 -0.0123 0.1587 1.0000
11.000 1.3669 0.01383 0.00834 -0.0112 0.1564 1.0000
11.250 1.3868 0.01418 0.00869 -0.0100 0.1539 1.0000
11.500 1.4062 0.01452 0.00905 -0.0087 0.1517 1.0000
11.750 1.4268 0.01479 0.00935 -0.0076 0.1504 1.0000
12.000 1.4462 0.01509 0.00968 -0.0063 0.1486 1.0000
12.250 1.4629 0.01543 0.01004 -0.0046 0.1465 1.0000
12.500 1.4761 0.01581 0.01044 -0.0024 0.1443 1.0000
12.750 1.4880 0.01627 0.01091 -0.0001 0.1421 1.0000
13.000 1.4989 0.01682 0.01147 0.0021 0.1395 1.0000
13.250 1.5137 0.01726 0.01196 0.0037 0.1381 1.0000
13.500 1.5270 0.01781 0.01254 0.0054 0.1357 1.0000
13.750 1.5390 0.01847 0.01323 0.0069 0.1339 1.0000
14.000 1.5473 0.01940 0.01417 0.0085 0.1302 1.0000
14.250 1.5558 0.02044 0.01524 0.0098 0.1278 1.0000
14.500 1.5678 0.02137 0.01621 0.0107 0.1261 1.0000
14.750 1.5775 0.02252 0.01741 0.0115 0.1231 1.0000
15.000 1.5852 0.02393 0.01884 0.0121 0.1203 1.0000
15.250 1.5915 0.02554 0.02049 0.0125 0.1182 1.0000
15.500 1.5979 0.02723 0.02223 0.0128 0.1156 1.0000
15.750 1.6041 0.02902 0.02407 0.0130 0.1129 1.0000
16.000 1.6068 0.03118 0.02627 0.0130 0.1099 1.0000
16.250 1.6070 0.03364 0.02877 0.0128 0.1076 1.0000
16.500 1.6060 0.03626 0.03145 0.0126 0.1044 1.0000
16.750 1.6013 0.03930 0.03454 0.0122 0.1006 1.0000
17.000 1.5900 0.04305 0.03832 0.0116 0.0970 1.0000
17.250 1.5861 0.04608 0.04143 0.0112 0.0953 1.0000
17.500 1.5771 0.04974 0.04515 0.0104 0.0925 1.0000
17.750 1.5629 0.05410 0.04957 0.0094 0.0896 1.0000
18.000 1.5481 0.05863 0.05416 0.0082 0.0871 1.0000
18.250 1.5307 0.06353 0.05913 0.0069 0.0833 1.0000
18.500 1.5148 0.06839 0.06406 0.0054 0.0811 1.0000
18.750 1.4941 0.07390 0.06963 0.0037 0.0781 1.0000
19.000 1.4802 0.07866 0.07447 0.0022 0.0764 1.0000
19.250 1.4572 0.08468 0.08055 0.0001 0.0733 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 1213 AIRFOIL (e1213-il)