LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Reynolds number: 100,000 Max Cl/Cd: 44.32 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5d-il-100000-n5.txt Download as CSV file: xf-c5d-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL758.6 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5386 0.09443 0.08876 -0.0433 1.0000 0.0346
-10.250 -0.5491 0.08876 0.08314 -0.0456 1.0000 0.0342
-10.000 -0.5659 0.08159 0.07603 -0.0492 1.0000 0.0337
-9.750 -0.5975 0.07262 0.06706 -0.0545 1.0000 0.0331
-9.500 -0.6333 0.06731 0.06170 -0.0543 1.0000 0.0327
-9.250 -0.6662 0.06372 0.05804 -0.0507 1.0000 0.0324
-9.000 -0.6912 0.05971 0.05388 -0.0475 1.0000 0.0322
-8.750 -0.7105 0.05577 0.04971 -0.0442 1.0000 0.0320
-8.500 -0.7238 0.05191 0.04558 -0.0409 1.0000 0.0319
-8.250 -0.7310 0.04827 0.04160 -0.0378 1.0000 0.0319
-8.000 -0.7327 0.04492 0.03789 -0.0350 1.0000 0.0320
-7.750 -0.7296 0.04187 0.03446 -0.0325 1.0000 0.0322
-7.500 -0.7225 0.03912 0.03133 -0.0303 1.0000 0.0325
-7.250 -0.7118 0.03676 0.02861 -0.0283 1.0000 0.0331
-7.000 -0.6985 0.03464 0.02611 -0.0265 1.0000 0.0341
-6.750 -0.6831 0.03267 0.02368 -0.0248 1.0000 0.0353
-6.500 -0.6656 0.03090 0.02155 -0.0234 1.0000 0.0363
-6.250 -0.6470 0.02946 0.02003 -0.0223 1.0000 0.0373
-6.000 -0.6273 0.02821 0.01865 -0.0213 1.0000 0.0384
-5.750 -0.6065 0.02703 0.01731 -0.0203 1.0000 0.0397
-5.500 -0.5850 0.02592 0.01602 -0.0193 1.0000 0.0414
-5.250 -0.5620 0.02503 0.01490 -0.0185 0.9998 0.0440
-5.000 -0.5322 0.02399 0.01393 -0.0196 0.9974 0.0473
-4.750 -0.5011 0.02319 0.01303 -0.0207 0.9950 0.0512
-4.500 -0.4711 0.02237 0.01220 -0.0216 0.9923 0.0561
-4.250 -0.4409 0.02171 0.01150 -0.0224 0.9894 0.0615
-4.000 -0.4097 0.02108 0.01087 -0.0236 0.9866 0.0689
-3.750 -0.3782 0.02052 0.01031 -0.0247 0.9840 0.0784
-3.500 -0.3491 0.01999 0.00987 -0.0254 0.9803 0.0933
-3.250 -0.3176 0.01950 0.00947 -0.0265 0.9771 0.1204
-3.000 -0.2848 0.01899 0.00916 -0.0280 0.9745 0.1640
-2.750 -0.2569 0.01841 0.00888 -0.0287 0.9703 0.2251
-2.500 -0.2280 0.01751 0.00863 -0.0297 0.9667 0.3562
-2.250 -0.2020 0.01657 0.00887 -0.0293 0.9639 0.6155
-2.000 -0.1766 0.01650 0.00913 -0.0280 0.9595 0.7273
-1.750 -0.1515 0.01654 0.00923 -0.0268 0.9540 0.7810
-1.500 -0.1207 0.01662 0.00931 -0.0268 0.9500 0.8179
-1.250 -0.0945 0.01670 0.00937 -0.0260 0.9446 0.8494
-1.000 -0.0664 0.01678 0.00944 -0.0255 0.9392 0.8790
-0.750 -0.0308 0.01693 0.00957 -0.0264 0.9358 0.9114
-0.500 0.0152 0.01714 0.00974 -0.0296 0.9340 0.9432
-0.250 0.0595 0.01729 0.00984 -0.0330 0.9301 0.9634
0.000 0.1029 0.01736 0.00986 -0.0365 0.9255 0.9754
0.250 0.1479 0.01739 0.00984 -0.0404 0.9220 0.9837
0.500 0.1962 0.01740 0.00982 -0.0450 0.9193 0.9899
0.750 0.2358 0.01742 0.00984 -0.0480 0.9129 0.9992
1.000 0.2671 0.01733 0.00975 -0.0491 0.9063 1.0000
1.250 0.2913 0.01724 0.00965 -0.0487 0.8971 1.0000
1.500 0.3275 0.01707 0.00950 -0.0505 0.8904 1.0000
1.750 0.3523 0.01692 0.00937 -0.0499 0.8794 1.0000
2.250 0.4223 0.01629 0.00882 -0.0521 0.8597 1.0000
2.500 0.4544 0.01583 0.00840 -0.0522 0.8439 1.0000
2.750 0.4814 0.01543 0.00803 -0.0513 0.8243 1.0000
3.000 0.5055 0.01513 0.00776 -0.0499 0.8015 1.0000
3.250 0.5335 0.01481 0.00745 -0.0492 0.7743 1.0000
3.500 0.5650 0.01447 0.00710 -0.0491 0.7382 1.0000
3.750 0.6019 0.01421 0.00668 -0.0498 0.6840 1.0000
4.000 0.6329 0.01428 0.00643 -0.0496 0.6066 1.0000
4.250 0.6523 0.01479 0.00644 -0.0475 0.5050 1.0000
4.500 0.6632 0.01569 0.00667 -0.0442 0.3880 1.0000
4.750 0.6747 0.01667 0.00709 -0.0414 0.2911 1.0000
5.000 0.6897 0.01754 0.00758 -0.0393 0.2208 1.0000
5.250 0.7059 0.01838 0.00813 -0.0374 0.1764 1.0000
5.500 0.7240 0.01909 0.00871 -0.0358 0.1451 1.0000
5.750 0.7419 0.01984 0.00929 -0.0342 0.1242 1.0000
6.000 0.7601 0.02058 0.00994 -0.0326 0.1099 1.0000
6.250 0.7787 0.02130 0.01065 -0.0311 0.1002 1.0000
6.500 0.7974 0.02205 0.01142 -0.0296 0.0937 1.0000
6.750 0.8163 0.02280 0.01219 -0.0281 0.0885 1.0000
7.000 0.8345 0.02370 0.01303 -0.0267 0.0842 1.0000
7.250 0.8552 0.02445 0.01390 -0.0255 0.0799 1.0000
7.500 0.8757 0.02530 0.01479 -0.0244 0.0765 1.0000
7.750 0.8963 0.02626 0.01574 -0.0234 0.0738 1.0000
8.000 0.9184 0.02736 0.01686 -0.0227 0.0712 1.0000
8.250 0.9410 0.02830 0.01798 -0.0219 0.0680 1.0000
8.500 0.9632 0.02934 0.01911 -0.0212 0.0653 1.0000
8.750 0.9845 0.03039 0.02019 -0.0204 0.0629 1.0000
9.000 1.0064 0.03170 0.02154 -0.0199 0.0604 1.0000
9.250 1.0276 0.03299 0.02311 -0.0189 0.0578 1.0000
9.500 1.0469 0.03422 0.02452 -0.0179 0.0552 1.0000
9.750 1.0650 0.03537 0.02571 -0.0168 0.0529 1.0000
10.000 1.0841 0.03707 0.02746 -0.0160 0.0509 1.0000
10.250 1.0983 0.03885 0.02965 -0.0142 0.0487 1.0000
10.500 1.1108 0.04055 0.03166 -0.0124 0.0464 1.0000
10.750 1.1224 0.04222 0.03352 -0.0105 0.0447 1.0000
11.000 1.1337 0.04379 0.03518 -0.0088 0.0432 1.0000
11.250 1.1424 0.04600 0.03751 -0.0070 0.0418 1.0000
11.500 1.1366 0.04844 0.04044 -0.0030 0.0405 1.0000
11.750 1.1296 0.05108 0.04346 0.0006 0.0392 1.0000
12.000 1.1212 0.05386 0.04656 0.0038 0.0382 1.0000
12.250 1.1114 0.05676 0.04973 0.0067 0.0375 1.0000
12.500 1.1012 0.05969 0.05291 0.0089 0.0368 1.0000
12.750 1.0894 0.06284 0.05627 0.0107 0.0362 1.0000
13.000 1.0768 0.06625 0.05986 0.0117 0.0357 1.0000
13.250 1.0637 0.06997 0.06374 0.0121 0.0352 1.0000
13.500 1.0459 0.07462 0.06857 0.0116 0.0350 1.0000
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Polar data table (+)
Polar graphs
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