LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 200,000 Max Cl/Cd: 55.15 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5c-il-200000-n5.txt Download as CSV file: xf-c5c-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL576 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7200 0.05995 0.05558 -0.0664 1.0000 0.0205
-11.000 -0.7477 0.05633 0.05186 -0.0650 1.0000 0.0204
-10.750 -0.7761 0.05378 0.04920 -0.0613 1.0000 0.0204
-10.500 -0.8051 0.05197 0.04730 -0.0554 1.0000 0.0204
-10.250 -0.8276 0.04943 0.04458 -0.0505 1.0000 0.0204
-10.000 -0.8446 0.04667 0.04157 -0.0460 1.0000 0.0204
-9.750 -0.8511 0.04335 0.03789 -0.0434 0.9988 0.0205
-9.500 -0.8408 0.04008 0.03430 -0.0435 0.9961 0.0207
-9.250 -0.8239 0.03792 0.03193 -0.0438 0.9941 0.0211
-9.000 -0.8071 0.03612 0.02994 -0.0435 0.9916 0.0215
-8.750 -0.7880 0.03424 0.02781 -0.0435 0.9891 0.0219
-8.500 -0.7671 0.03227 0.02556 -0.0437 0.9869 0.0223
-8.250 -0.7449 0.03029 0.02327 -0.0438 0.9853 0.0226
-8.000 -0.7235 0.02857 0.02126 -0.0435 0.9833 0.0229
-7.750 -0.7021 0.02706 0.01950 -0.0429 0.9807 0.0234
-7.500 -0.6778 0.02567 0.01788 -0.0429 0.9785 0.0239
-7.250 -0.6520 0.02442 0.01642 -0.0430 0.9768 0.0245
-7.000 -0.6252 0.02334 0.01514 -0.0432 0.9754 0.0252
-6.750 -0.5978 0.02223 0.01393 -0.0437 0.9741 0.0260
-6.500 -0.5740 0.02140 0.01308 -0.0434 0.9717 0.0269
-6.250 -0.5506 0.02072 0.01236 -0.0429 0.9688 0.0281
-6.000 -0.5249 0.02007 0.01163 -0.0429 0.9667 0.0295
-5.750 -0.4972 0.01948 0.01095 -0.0432 0.9648 0.0312
-5.500 -0.4688 0.01881 0.01027 -0.0438 0.9631 0.0334
-5.250 -0.4385 0.01836 0.00979 -0.0447 0.9617 0.0364
-5.000 -0.4125 0.01802 0.00936 -0.0446 0.9594 0.0393
-4.750 -0.3909 0.01744 0.00881 -0.0437 0.9557 0.0423
-4.500 -0.3630 0.01704 0.00836 -0.0440 0.9529 0.0462
-4.250 -0.3325 0.01657 0.00787 -0.0448 0.9505 0.0509
-4.000 -0.3000 0.01615 0.00744 -0.0460 0.9485 0.0577
-3.500 -0.2478 0.01529 0.00685 -0.0459 0.9421 0.1092
-3.250 -0.2214 0.01494 0.00663 -0.0459 0.9388 0.1427
-3.000 -0.1920 0.01459 0.00643 -0.0466 0.9364 0.1849
-2.750 -0.1618 0.01409 0.00623 -0.0476 0.9345 0.2498
-2.500 -0.1319 0.01337 0.00603 -0.0486 0.9329 0.3746
-2.250 -0.1111 0.01257 0.00602 -0.0476 0.9293 0.5524
-2.000 -0.0911 0.01226 0.00615 -0.0457 0.9244 0.6613
-1.750 -0.0622 0.01213 0.00615 -0.0457 0.9214 0.7117
-1.500 -0.0298 0.01204 0.00609 -0.0465 0.9191 0.7401
-1.250 0.0043 0.01195 0.00601 -0.0476 0.9174 0.7617
-1.000 0.0241 0.01196 0.00604 -0.0458 0.9108 0.7809
-0.750 0.0531 0.01190 0.00601 -0.0458 0.9072 0.8021
-0.500 0.0839 0.01182 0.00601 -0.0460 0.9048 0.8298
-0.250 0.1160 0.01174 0.00599 -0.0464 0.9029 0.8544
0.000 0.1367 0.01179 0.00609 -0.0446 0.8963 0.8756
0.250 0.1662 0.01176 0.00609 -0.0445 0.8926 0.8968
0.500 0.2008 0.01167 0.00602 -0.0455 0.8898 0.9141
0.750 0.2344 0.01157 0.00595 -0.0464 0.8847 0.9267
1.000 0.2697 0.01133 0.00571 -0.0475 0.8767 0.9356
1.250 0.3036 0.01103 0.00542 -0.0483 0.8659 0.9450
1.500 0.3442 0.01072 0.00510 -0.0505 0.8562 0.9503
1.750 0.3791 0.01055 0.00494 -0.0517 0.8442 0.9585
2.000 0.4157 0.01041 0.00481 -0.0533 0.8296 0.9647
2.250 0.4513 0.01025 0.00465 -0.0546 0.8100 0.9718
2.500 0.4905 0.01002 0.00435 -0.0565 0.7715 0.9760
2.750 0.5306 0.00995 0.00395 -0.0584 0.6966 0.9792
3.000 0.5636 0.01027 0.00391 -0.0592 0.6256 0.9854
3.250 0.5940 0.01077 0.00405 -0.0599 0.5465 0.9921
3.500 0.6195 0.01160 0.00432 -0.0599 0.4322 0.9995
3.750 0.6268 0.01234 0.00458 -0.0562 0.3438 1.0000
4.000 0.6363 0.01300 0.00486 -0.0529 0.2697 1.0000
4.250 0.6488 0.01359 0.00516 -0.0501 0.2095 1.0000
4.500 0.6638 0.01409 0.00545 -0.0479 0.1721 1.0000
4.750 0.6807 0.01454 0.00575 -0.0459 0.1415 1.0000
5.000 0.6986 0.01498 0.00607 -0.0441 0.1200 1.0000
5.250 0.7172 0.01543 0.00644 -0.0425 0.1066 1.0000
5.500 0.7369 0.01584 0.00684 -0.0410 0.0953 1.0000
5.750 0.7568 0.01627 0.00725 -0.0396 0.0855 1.0000
6.000 0.7766 0.01674 0.00767 -0.0382 0.0774 1.0000
6.250 0.7974 0.01714 0.00813 -0.0370 0.0718 1.0000
6.500 0.8175 0.01762 0.00858 -0.0357 0.0674 1.0000
6.750 0.8374 0.01812 0.00909 -0.0344 0.0640 1.0000
7.000 0.8578 0.01860 0.00961 -0.0331 0.0608 1.0000
7.250 0.8776 0.01913 0.01016 -0.0318 0.0581 1.0000
7.500 0.8957 0.01983 0.01082 -0.0303 0.0554 1.0000
7.750 0.9159 0.02037 0.01144 -0.0291 0.0533 1.0000
8.000 0.9356 0.02096 0.01210 -0.0278 0.0509 1.0000
8.250 0.9545 0.02158 0.01277 -0.0264 0.0487 1.0000
8.500 0.9718 0.02237 0.01356 -0.0249 0.0467 1.0000
8.750 0.9898 0.02325 0.01448 -0.0234 0.0450 1.0000
9.000 1.0093 0.02393 0.01529 -0.0222 0.0432 1.0000
9.250 1.0280 0.02467 0.01613 -0.0208 0.0413 1.0000
9.500 1.0460 0.02546 0.01699 -0.0195 0.0397 1.0000
9.750 1.0632 0.02636 0.01794 -0.0181 0.0383 1.0000
10.000 1.0808 0.02770 0.01928 -0.0169 0.0369 1.0000
10.250 1.0988 0.02860 0.02038 -0.0155 0.0357 1.0000
10.500 1.1158 0.02959 0.02156 -0.0141 0.0343 1.0000
10.750 1.1314 0.03057 0.02268 -0.0125 0.0329 1.0000
11.000 1.1456 0.03151 0.02370 -0.0108 0.0317 1.0000
11.250 1.1590 0.03252 0.02477 -0.0092 0.0308 1.0000
11.500 1.1719 0.03389 0.02619 -0.0076 0.0300 1.0000
11.750 1.1835 0.03537 0.02793 -0.0056 0.0292 1.0000
12.000 1.1928 0.03694 0.02976 -0.0036 0.0282 1.0000
12.250 1.2003 0.03842 0.03147 -0.0014 0.0272 1.0000
12.500 1.2070 0.03969 0.03290 0.0007 0.0263 1.0000
12.750 1.2139 0.04076 0.03405 0.0026 0.0255 1.0000
13.000 1.2205 0.04183 0.03515 0.0043 0.0248 1.0000
13.250 1.2240 0.04344 0.03687 0.0061 0.0241 1.0000
13.500 1.2220 0.04587 0.03965 0.0082 0.0232 1.0000
13.750 1.2197 0.04829 0.04234 0.0099 0.0224 1.0000
14.000 1.2175 0.05067 0.04492 0.0113 0.0217 1.0000
14.250 1.2149 0.05317 0.04759 0.0123 0.0212 1.0000
14.500 1.2120 0.05581 0.05036 0.0129 0.0208 1.0000
14.750 1.2079 0.05873 0.05341 0.0131 0.0204 1.0000
15.000 1.2026 0.06198 0.05678 0.0129 0.0201 1.0000
15.250 1.1957 0.06567 0.06059 0.0122 0.0199 1.0000
15.500 1.1829 0.07052 0.06561 0.0107 0.0197 1.0000
15.750 1.1605 0.07751 0.07287 0.0077 0.0196 1.0000
16.000 1.1349 0.08580 0.08142 0.0032 0.0195 1.0000
16.250 1.1068 0.09549 0.09133 -0.0026 0.0196 1.0000
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Polar data table (+)
Polar graphs
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