LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.85 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5d-il-1000000.txt Download as CSV file: xf-c5d-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7664 0.03495 0.03252 -0.0729 1.0000 0.0161
-12.000 -0.8909 0.04296 0.04020 -0.0681 1.0000 0.0159
-11.750 -0.9200 0.04161 0.03875 -0.0615 1.0000 0.0159
-11.500 -0.9392 0.04030 0.03732 -0.0558 0.9996 0.0158
-11.250 -0.9260 0.03775 0.03458 -0.0568 0.9976 0.0157
-11.000 -0.9101 0.03571 0.03236 -0.0574 0.9959 0.0156
-10.750 -0.8911 0.03386 0.03035 -0.0582 0.9947 0.0156
-10.500 -0.8860 0.02965 0.02581 -0.0577 0.9921 0.0154
-10.250 -0.8718 0.02670 0.02256 -0.0576 0.9897 0.0153
-10.000 -0.8515 0.02453 0.02015 -0.0579 0.9881 0.0152
-9.750 -0.8271 0.02301 0.01845 -0.0584 0.9870 0.0153
-9.500 -0.8015 0.02154 0.01680 -0.0591 0.9861 0.0153
-9.250 -0.7751 0.02000 0.01509 -0.0599 0.9854 0.0152
-9.000 -0.7509 0.01876 0.01371 -0.0599 0.9836 0.0152
-8.750 -0.7280 0.01771 0.01255 -0.0595 0.9809 0.0152
-8.500 -0.7015 0.01675 0.01149 -0.0598 0.9793 0.0152
-8.250 -0.6734 0.01587 0.01052 -0.0604 0.9781 0.0152
-8.000 -0.6441 0.01509 0.00965 -0.0612 0.9771 0.0152
-7.750 -0.6137 0.01437 0.00887 -0.0622 0.9764 0.0153
-7.500 -0.5826 0.01373 0.00817 -0.0634 0.9758 0.0153
-7.250 -0.5511 0.01316 0.00754 -0.0645 0.9752 0.0154
-7.000 -0.5199 0.01265 0.00699 -0.0656 0.9746 0.0155
-6.750 -0.4978 0.01205 0.00633 -0.0646 0.9711 0.0158
-6.500 -0.4711 0.01152 0.00575 -0.0646 0.9685 0.0163
-6.250 -0.4412 0.01110 0.00532 -0.0653 0.9667 0.0169
-6.000 -0.4103 0.01074 0.00495 -0.0661 0.9651 0.0177
-5.750 -0.3792 0.01042 0.00461 -0.0669 0.9636 0.0189
-5.500 -0.3492 0.01003 0.00423 -0.0675 0.9622 0.0218
-5.250 -0.3258 0.00979 0.00399 -0.0666 0.9582 0.0254
-5.000 -0.2991 0.00959 0.00382 -0.0664 0.9553 0.0288
-4.750 -0.2711 0.00933 0.00357 -0.0665 0.9529 0.0324
-4.500 -0.2420 0.00913 0.00338 -0.0668 0.9509 0.0354
-4.250 -0.2133 0.00889 0.00314 -0.0670 0.9487 0.0391
-4.000 -0.1886 0.00870 0.00297 -0.0664 0.9444 0.0430
-3.750 -0.1620 0.00848 0.00277 -0.0661 0.9406 0.0492
-3.500 -0.1345 0.00822 0.00257 -0.0661 0.9377 0.0619
-3.250 -0.1075 0.00788 0.00239 -0.0660 0.9350 0.0972
-3.000 -0.0807 0.00767 0.00228 -0.0659 0.9317 0.1244
-2.750 -0.0546 0.00748 0.00215 -0.0655 0.9271 0.1432
-2.500 -0.0276 0.00722 0.00201 -0.0654 0.9230 0.1749
-2.250 -0.0007 0.00687 0.00186 -0.0653 0.9195 0.2332
-2.000 0.0237 0.00637 0.00173 -0.0649 0.9153 0.3368
-1.750 0.0454 0.00559 0.00158 -0.0640 0.9104 0.5218
-1.500 0.0712 0.00526 0.00151 -0.0636 0.9061 0.6070
-1.250 0.0980 0.00507 0.00147 -0.0633 0.9012 0.6559
-1.000 0.1246 0.00496 0.00144 -0.0629 0.8945 0.6892
-0.750 0.1524 0.00487 0.00137 -0.0627 0.8870 0.7131
-0.500 0.1790 0.00480 0.00132 -0.0622 0.8759 0.7353
-0.250 0.2056 0.00473 0.00129 -0.0618 0.8640 0.7550
0.000 0.2327 0.00470 0.00127 -0.0614 0.8526 0.7719
0.250 0.2594 0.00469 0.00124 -0.0610 0.8354 0.7857
0.500 0.2859 0.00470 0.00122 -0.0605 0.8168 0.7985
0.750 0.3124 0.00472 0.00122 -0.0600 0.7983 0.8102
1.000 0.3386 0.00476 0.00123 -0.0595 0.7770 0.8216
1.250 0.3639 0.00486 0.00124 -0.0589 0.7491 0.8338
1.500 0.3881 0.00499 0.00129 -0.0579 0.7142 0.8460
1.750 0.4112 0.00518 0.00137 -0.0568 0.6752 0.8599
2.000 0.4336 0.00543 0.00146 -0.0555 0.6293 0.8728
2.250 0.4556 0.00572 0.00157 -0.0542 0.5766 0.8851
2.500 0.4778 0.00603 0.00170 -0.0530 0.5214 0.8973
2.750 0.4961 0.00658 0.00190 -0.0511 0.4266 0.9110
3.000 0.5152 0.00710 0.00212 -0.0494 0.3447 0.9265
3.250 0.5348 0.00759 0.00234 -0.0477 0.2754 0.9432
3.500 0.5557 0.00807 0.00257 -0.0463 0.2069 0.9587
3.750 0.5814 0.00846 0.00278 -0.0460 0.1690 0.9710
4.000 0.6111 0.00885 0.00299 -0.0467 0.1284 0.9799
4.250 0.6425 0.00923 0.00322 -0.0477 0.0991 0.9871
4.500 0.6751 0.00958 0.00346 -0.0490 0.0769 0.9926
4.750 0.7089 0.00994 0.00370 -0.0505 0.0605 0.9958
5.000 0.7434 0.01023 0.00394 -0.0522 0.0558 0.9988
5.250 0.7682 0.01050 0.00419 -0.0517 0.0524 1.0000
5.500 0.7881 0.01071 0.00441 -0.0501 0.0509 1.0000
5.750 0.8097 0.01092 0.00463 -0.0489 0.0498 1.0000
6.000 0.8320 0.01116 0.00488 -0.0478 0.0487 1.0000
6.250 0.8548 0.01142 0.00516 -0.0469 0.0476 1.0000
6.500 0.8776 0.01172 0.00546 -0.0460 0.0461 1.0000
6.750 0.9000 0.01208 0.00582 -0.0450 0.0443 1.0000
7.000 0.9203 0.01263 0.00642 -0.0436 0.0423 1.0000
7.250 0.9440 0.01290 0.00671 -0.0429 0.0417 1.0000
7.500 0.9680 0.01315 0.00698 -0.0423 0.0410 1.0000
7.750 0.9920 0.01340 0.00725 -0.0417 0.0399 1.0000
8.000 1.0157 0.01367 0.00753 -0.0410 0.0386 1.0000
8.250 1.0388 0.01398 0.00785 -0.0403 0.0374 1.0000
8.500 1.0611 0.01436 0.00823 -0.0394 0.0362 1.0000
8.750 1.0778 0.01521 0.00914 -0.0376 0.0342 1.0000
9.000 1.1032 0.01530 0.00924 -0.0373 0.0337 1.0000
9.250 1.1277 0.01546 0.00942 -0.0368 0.0327 1.0000
9.500 1.1514 0.01567 0.00966 -0.0362 0.0315 1.0000
9.750 1.1748 0.01590 0.00989 -0.0355 0.0302 1.0000
10.000 1.1959 0.01629 0.01026 -0.0345 0.0287 1.0000
10.250 1.2160 0.01668 0.01069 -0.0333 0.0275 1.0000
10.500 1.2383 0.01689 0.01092 -0.0325 0.0262 1.0000
10.750 1.2601 0.01713 0.01116 -0.0316 0.0248 1.0000
11.000 1.2787 0.01761 0.01162 -0.0301 0.0229 1.0000
11.250 1.2994 0.01792 0.01197 -0.0291 0.0217 1.0000
11.500 1.3189 0.01832 0.01238 -0.0279 0.0202 1.0000
11.750 1.3351 0.01897 0.01303 -0.0262 0.0186 1.0000
12.000 1.3532 0.01947 0.01359 -0.0248 0.0178 1.0000
12.250 1.3702 0.02004 0.01420 -0.0233 0.0168 1.0000
12.500 1.3852 0.02076 0.01494 -0.0215 0.0158 1.0000
12.750 1.3976 0.02165 0.01589 -0.0194 0.0150 1.0000
13.000 1.4128 0.02233 0.01665 -0.0178 0.0145 1.0000
13.250 1.4270 0.02307 0.01747 -0.0161 0.0139 1.0000
13.500 1.4403 0.02388 0.01833 -0.0143 0.0133 1.0000
13.750 1.4512 0.02487 0.01937 -0.0124 0.0128 1.0000
14.000 1.4563 0.02629 0.02087 -0.0098 0.0122 1.0000
14.250 1.4660 0.02738 0.02206 -0.0079 0.0119 1.0000
14.500 1.4763 0.02844 0.02321 -0.0061 0.0117 1.0000
14.750 1.4853 0.02962 0.02449 -0.0044 0.0114 1.0000
15.000 1.4929 0.03092 0.02589 -0.0026 0.0112 1.0000
15.250 1.4994 0.03234 0.02740 -0.0009 0.0109 1.0000
15.500 1.5049 0.03389 0.02904 0.0007 0.0107 1.0000
15.750 1.5089 0.03561 0.03085 0.0023 0.0105 1.0000
16.000 1.5107 0.03758 0.03292 0.0038 0.0103 1.0000
16.250 1.5098 0.03989 0.03533 0.0051 0.0101 1.0000
16.500 1.5049 0.04270 0.03826 0.0063 0.0099 1.0000
16.750 1.4956 0.04615 0.04185 0.0071 0.0097 1.0000
17.000 1.4816 0.05043 0.04628 0.0073 0.0096 1.0000
17.250 1.4693 0.05485 0.05085 0.0068 0.0095 1.0000
17.500 1.4632 0.05877 0.05491 0.0060 0.0094 1.0000
17.750 1.4540 0.06339 0.05966 0.0046 0.0094 1.0000
18.000 1.4407 0.06884 0.06527 0.0026 0.0093 1.0000
18.250 1.4239 0.07519 0.07177 -0.0002 0.0093 1.0000
18.500 1.4020 0.08278 0.07952 -0.0039 0.0093 1.0000
18.750 1.3745 0.09176 0.08868 -0.0086 0.0093 1.0000
19.000 1.3396 0.10247 0.09957 -0.0143 0.0093 1.0000
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Polar data table (+)
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