EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Reynolds number: 500,000 Max Cl/Cd: 52.8 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea61012-il-500000-n5.txt Download as CSV file: xf-ea61012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 6(-1)-012 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
------ -------- --------- --------- -------- -------- --------
-18.750 -1.2503 0.09054 0.08709 -0.0149 1.0000 0.0215
-18.500 -1.2751 0.08213 0.07853 -0.0200 1.0000 0.0218
-18.250 -1.2929 0.07519 0.07145 -0.0241 1.0000 0.0221
-18.000 -1.3060 0.06932 0.06545 -0.0274 1.0000 0.0225
-17.750 -1.3153 0.06431 0.06032 -0.0301 1.0000 0.0229
-17.500 -1.3210 0.06010 0.05599 -0.0321 1.0000 0.0234
-17.250 -1.3246 0.05643 0.05221 -0.0337 1.0000 0.0240
-17.000 -1.3282 0.05297 0.04863 -0.0349 1.0000 0.0244
-16.750 -1.3293 0.04997 0.04551 -0.0357 1.0000 0.0250
-16.500 -1.3279 0.04740 0.04281 -0.0362 1.0000 0.0256
-16.250 -1.3269 0.04484 0.04012 -0.0366 1.0000 0.0259
-16.000 -1.3245 0.04254 0.03771 -0.0367 1.0000 0.0264
-15.750 -1.3225 0.04028 0.03538 -0.0368 1.0000 0.0270
-15.500 -1.3163 0.03853 0.03357 -0.0367 1.0000 0.0277
-15.250 -1.3097 0.03687 0.03184 -0.0364 1.0000 0.0281
-15.000 -1.3003 0.03554 0.03046 -0.0361 1.0000 0.0288
-14.750 -1.2909 0.03424 0.02909 -0.0356 1.0000 0.0294
-14.500 -1.2804 0.03306 0.02785 -0.0350 1.0000 0.0302
-14.250 -1.2698 0.03192 0.02663 -0.0344 1.0000 0.0309
-14.000 -1.2594 0.03077 0.02539 -0.0336 1.0000 0.0315
-13.750 -1.2494 0.02959 0.02412 -0.0327 1.0000 0.0320
-13.500 -1.2368 0.02870 0.02313 -0.0319 1.0000 0.0326
-13.250 -1.2245 0.02777 0.02210 -0.0309 1.0000 0.0331
-13.000 -1.2117 0.02692 0.02116 -0.0298 1.0000 0.0334
-12.750 -1.2003 0.02597 0.02012 -0.0286 1.0000 0.0338
-12.500 -1.1909 0.02490 0.01901 -0.0270 1.0000 0.0346
-12.250 -1.1786 0.02419 0.01827 -0.0254 1.0000 0.0353
-12.000 -1.1650 0.02362 0.01766 -0.0238 1.0000 0.0360
-11.750 -1.1504 0.02314 0.01714 -0.0222 1.0000 0.0366
-11.500 -1.1350 0.02267 0.01663 -0.0206 1.0000 0.0373
-11.250 -1.1174 0.02221 0.01611 -0.0194 1.0000 0.0381
-11.000 -1.0985 0.02173 0.01557 -0.0183 1.0000 0.0389
-10.750 -1.0792 0.02119 0.01498 -0.0173 1.0000 0.0396
-10.500 -1.0597 0.02061 0.01433 -0.0163 1.0000 0.0402
-10.250 -1.0392 0.02009 0.01375 -0.0154 1.0000 0.0408
-10.000 -1.0183 0.01959 0.01319 -0.0146 1.0000 0.0413
-9.750 -0.9966 0.01915 0.01269 -0.0138 1.0000 0.0417
-9.500 -0.9527 0.01853 0.01195 -0.0177 0.9152 0.0422
-9.250 -0.9312 0.01779 0.01105 -0.0170 0.8762 0.0430
-9.000 -0.9113 0.01729 0.01046 -0.0159 0.8596 0.0437
-8.750 -0.8901 0.01687 0.00996 -0.0149 0.8486 0.0444
-8.500 -0.8678 0.01648 0.00950 -0.0141 0.8403 0.0451
-8.250 -0.8452 0.01612 0.00907 -0.0133 0.8330 0.0457
-8.000 -0.8217 0.01579 0.00869 -0.0127 0.8272 0.0466
-7.750 -0.7979 0.01545 0.00830 -0.0121 0.8218 0.0475
-7.500 -0.7743 0.01510 0.00789 -0.0114 0.8170 0.0482
-7.250 -0.7502 0.01477 0.00750 -0.0108 0.8127 0.0489
-7.000 -0.7257 0.01444 0.00713 -0.0103 0.8082 0.0496
-6.750 -0.7011 0.01414 0.00677 -0.0098 0.8039 0.0503
-6.500 -0.6762 0.01388 0.00644 -0.0093 0.8000 0.0507
-6.250 -0.6517 0.01350 0.00605 -0.0088 0.7958 0.0517
-6.000 -0.6272 0.01312 0.00566 -0.0083 0.7914 0.0529
-5.750 -0.6020 0.01283 0.00534 -0.0078 0.7875 0.0540
-5.500 -0.5765 0.01258 0.00507 -0.0074 0.7842 0.0552
-5.250 -0.5503 0.01233 0.00482 -0.0071 0.7804 0.0566
-5.000 -0.5240 0.01211 0.00458 -0.0068 0.7765 0.0580
-4.750 -0.4977 0.01190 0.00434 -0.0065 0.7728 0.0592
-4.500 -0.4714 0.01169 0.00410 -0.0062 0.7695 0.0604
-4.250 -0.4451 0.01143 0.00386 -0.0059 0.7658 0.0626
-4.000 -0.4185 0.01121 0.00366 -0.0057 0.7617 0.0650
-3.750 -0.3916 0.01103 0.00347 -0.0054 0.7577 0.0676
-3.500 -0.3649 0.01085 0.00328 -0.0052 0.7542 0.0712
-3.250 -0.3380 0.01064 0.00311 -0.0049 0.7501 0.0771
-3.000 -0.3114 0.01040 0.00294 -0.0047 0.7451 0.0882
-2.500 -0.2607 0.00964 0.00254 -0.0039 0.7356 0.1735
-2.250 -0.2353 0.00923 0.00236 -0.0036 0.7305 0.2269
-2.000 -0.2105 0.00876 0.00218 -0.0032 0.7260 0.2977
-1.750 -0.1850 0.00841 0.00204 -0.0028 0.7217 0.3604
-1.500 -0.1589 0.00807 0.00190 -0.0025 0.7161 0.4109
-1.250 -0.1361 0.00747 0.00178 -0.0017 0.7113 0.5267
-1.000 -0.1098 0.00729 0.00178 -0.0012 0.7072 0.5831
-0.750 -0.0821 0.00722 0.00177 -0.0010 0.7003 0.6089
-0.500 -0.0550 0.00714 0.00176 -0.0006 0.6922 0.6341
-0.250 -0.0274 0.00710 0.00178 -0.0004 0.6830 0.6542
0.000 0.0000 0.00709 0.00178 0.0000 0.6709 0.6709
0.250 0.0274 0.00710 0.00178 0.0003 0.6541 0.6830
0.500 0.0550 0.00714 0.00176 0.0006 0.6338 0.6920
0.750 0.0821 0.00721 0.00177 0.0010 0.6088 0.7002
1.000 0.1098 0.00729 0.00178 0.0012 0.5836 0.7072
1.250 0.1361 0.00747 0.00178 0.0017 0.5257 0.7113
1.500 0.1590 0.00807 0.00190 0.0025 0.4112 0.7161
1.750 0.1850 0.00841 0.00204 0.0028 0.3605 0.7218
2.000 0.2105 0.00876 0.00218 0.0032 0.2987 0.7260
2.250 0.2353 0.00923 0.00236 0.0036 0.2272 0.7305
2.500 0.2607 0.00963 0.00254 0.0039 0.1738 0.7355
2.750 0.2857 0.01007 0.00274 0.0043 0.1194 0.7403
3.000 0.3114 0.01040 0.00294 0.0047 0.0883 0.7451
3.250 0.3380 0.01064 0.00311 0.0049 0.0771 0.7501
3.500 0.3649 0.01085 0.00328 0.0052 0.0712 0.7542
3.750 0.3917 0.01103 0.00347 0.0054 0.0676 0.7577
4.000 0.4185 0.01121 0.00366 0.0057 0.0650 0.7617
4.250 0.4451 0.01143 0.00386 0.0059 0.0627 0.7658
4.500 0.4714 0.01169 0.00410 0.0062 0.0605 0.7695
4.750 0.4977 0.01190 0.00434 0.0065 0.0592 0.7728
5.000 0.5241 0.01211 0.00458 0.0068 0.0581 0.7765
5.250 0.5503 0.01233 0.00482 0.0071 0.0566 0.7804
5.500 0.5765 0.01258 0.00507 0.0074 0.0552 0.7842
5.750 0.6020 0.01283 0.00534 0.0078 0.0540 0.7875
6.000 0.6272 0.01312 0.00566 0.0083 0.0528 0.7914
6.250 0.6517 0.01350 0.00604 0.0088 0.0516 0.7958
6.500 0.6762 0.01388 0.00644 0.0093 0.0508 0.8000
6.750 0.7010 0.01414 0.00678 0.0098 0.0503 0.8039
7.000 0.7258 0.01444 0.00712 0.0103 0.0496 0.8083
7.250 0.7502 0.01476 0.00749 0.0108 0.0490 0.8127
7.500 0.7743 0.01510 0.00789 0.0114 0.0482 0.8170
7.750 0.7980 0.01545 0.00830 0.0120 0.0475 0.8218
8.000 0.8217 0.01579 0.00868 0.0127 0.0466 0.8273
8.250 0.8452 0.01612 0.00907 0.0133 0.0457 0.8331
8.500 0.8679 0.01648 0.00949 0.0141 0.0450 0.8403
8.750 0.8902 0.01686 0.00995 0.0149 0.0443 0.8486
9.000 0.9114 0.01729 0.01045 0.0158 0.0437 0.8596
9.250 0.9312 0.01780 0.01106 0.0170 0.0430 0.8762
9.500 0.9528 0.01854 0.01195 0.0177 0.0421 0.9154
9.750 0.9967 0.01914 0.01268 0.0138 0.0417 1.0000
10.000 1.0185 0.01958 0.01318 0.0145 0.0413 1.0000
10.250 1.0395 0.02006 0.01372 0.0154 0.0408 1.0000
10.500 1.0598 0.02061 0.01433 0.0163 0.0402 1.0000
10.750 1.0795 0.02118 0.01497 0.0173 0.0396 1.0000
11.000 1.0987 0.02173 0.01558 0.0183 0.0389 1.0000
11.250 1.1177 0.02219 0.01609 0.0193 0.0381 1.0000
11.500 1.1355 0.02263 0.01658 0.0205 0.0372 1.0000
11.750 1.1512 0.02305 0.01704 0.0221 0.0365 1.0000
12.000 1.1655 0.02358 0.01762 0.0238 0.0359 1.0000
12.250 1.1790 0.02418 0.01825 0.0254 0.0353 1.0000
12.500 1.1912 0.02494 0.01905 0.0269 0.0347 1.0000
12.750 1.2009 0.02596 0.02012 0.0285 0.0339 1.0000
13.000 1.2119 0.02695 0.02119 0.0298 0.0334 1.0000
13.250 1.2253 0.02774 0.02207 0.0308 0.0330 1.0000
13.500 1.2378 0.02864 0.02307 0.0317 0.0326 1.0000
13.750 1.2496 0.02963 0.02415 0.0326 0.0320 1.0000
14.000 1.2601 0.03076 0.02538 0.0335 0.0315 1.0000
14.250 1.2720 0.03175 0.02644 0.0342 0.0306 1.0000
14.500 1.2817 0.03299 0.02777 0.0349 0.0301 1.0000
14.750 1.2918 0.03421 0.02906 0.0355 0.0294 1.0000
15.000 1.3012 0.03552 0.03044 0.0360 0.0288 1.0000
15.250 1.3096 0.03695 0.03193 0.0363 0.0282 1.0000
15.500 1.3177 0.03845 0.03349 0.0366 0.0276 1.0000
15.750 1.3235 0.04025 0.03534 0.0367 0.0269 1.0000
16.000 1.3252 0.04254 0.03771 0.0366 0.0263 1.0000
16.250 1.3283 0.04477 0.04006 0.0365 0.0259 1.0000
16.500 1.3316 0.04708 0.04248 0.0362 0.0253 1.0000
16.750 1.3308 0.04990 0.04543 0.0356 0.0249 1.0000
17.000 1.3287 0.05301 0.04867 0.0347 0.0245 1.0000
17.250 1.3283 0.05607 0.05184 0.0336 0.0238 1.0000
17.500 1.3228 0.05998 0.05588 0.0320 0.0234 1.0000
17.750 1.3165 0.06427 0.06027 0.0299 0.0229 1.0000
18.000 1.3082 0.06915 0.06527 0.0273 0.0224 1.0000
18.250 1.2948 0.07507 0.07133 0.0239 0.0221 1.0000
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Polar data table (+)
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