LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.48 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141c-il-1000000.txt Download as CSV file: xf-c141c-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL426.57 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9660 0.06868 0.06637 -0.0532 1.0000 0.0126
-15.000 -1.0133 0.05445 0.05184 -0.0646 1.0000 0.0124
-14.750 -1.0358 0.04724 0.04442 -0.0697 1.0000 0.0124
-14.500 -1.0503 0.04237 0.03937 -0.0721 1.0000 0.0124
-14.250 -1.0602 0.03874 0.03558 -0.0729 1.0000 0.0125
-14.000 -1.0671 0.03591 0.03260 -0.0725 1.0000 0.0126
-13.750 -1.0718 0.03366 0.03020 -0.0711 1.0000 0.0127
-13.500 -1.0755 0.03183 0.02823 -0.0687 1.0000 0.0128
-13.250 -1.0811 0.03043 0.02671 -0.0651 1.0000 0.0129
-13.000 -1.0952 0.02951 0.02569 -0.0588 1.0000 0.0130
-12.750 -1.1048 0.02863 0.02471 -0.0531 1.0000 0.0131
-12.500 -1.1083 0.02775 0.02373 -0.0483 1.0000 0.0132
-12.250 -1.1064 0.02693 0.02280 -0.0445 0.9999 0.0134
-12.000 -1.0829 0.02582 0.02156 -0.0450 0.9986 0.0136
-11.750 -1.0583 0.02483 0.02043 -0.0456 0.9973 0.0137
-11.500 -1.0354 0.02346 0.01890 -0.0460 0.9959 0.0139
-11.250 -1.0171 0.02114 0.01634 -0.0460 0.9946 0.0143
-11.000 -0.9931 0.02006 0.01516 -0.0463 0.9931 0.0146
-10.750 -0.9678 0.01929 0.01434 -0.0466 0.9911 0.0150
-10.500 -0.9408 0.01862 0.01360 -0.0471 0.9894 0.0153
-10.250 -0.9129 0.01795 0.01287 -0.0478 0.9880 0.0157
-10.000 -0.8840 0.01730 0.01213 -0.0486 0.9868 0.0161
-9.750 -0.8544 0.01666 0.01142 -0.0495 0.9858 0.0165
-9.500 -0.8238 0.01610 0.01078 -0.0506 0.9850 0.0169
-9.250 -0.7924 0.01563 0.01024 -0.0518 0.9843 0.0172
-9.000 -0.7640 0.01453 0.00906 -0.0527 0.9836 0.0181
-8.750 -0.7398 0.01409 0.00859 -0.0523 0.9804 0.0188
-8.500 -0.7107 0.01369 0.00817 -0.0529 0.9785 0.0195
-8.250 -0.6810 0.01328 0.00771 -0.0536 0.9769 0.0203
-8.000 -0.6509 0.01290 0.00729 -0.0544 0.9753 0.0210
-7.750 -0.6219 0.01232 0.00666 -0.0550 0.9738 0.0221
-7.500 -0.5922 0.01186 0.00619 -0.0557 0.9723 0.0235
-7.250 -0.5622 0.01156 0.00587 -0.0563 0.9708 0.0248
-7.000 -0.5391 0.01134 0.00562 -0.0554 0.9668 0.0259
-6.750 -0.5140 0.01091 0.00517 -0.0550 0.9636 0.0280
-6.500 -0.4864 0.01065 0.00492 -0.0551 0.9611 0.0301
-6.250 -0.4584 0.01043 0.00468 -0.0552 0.9589 0.0318
-6.000 -0.4322 0.01008 0.00432 -0.0550 0.9564 0.0345
-5.750 -0.4079 0.00986 0.00411 -0.0543 0.9526 0.0370
-5.500 -0.3816 0.00969 0.00392 -0.0540 0.9492 0.0390
-5.250 -0.3557 0.00937 0.00361 -0.0536 0.9461 0.0433
-5.000 -0.3287 0.00919 0.00342 -0.0535 0.9434 0.0469
-4.750 -0.3028 0.00895 0.00320 -0.0531 0.9403 0.0522
-4.500 -0.2769 0.00877 0.00304 -0.0527 0.9364 0.0572
-4.250 -0.2508 0.00853 0.00284 -0.0524 0.9328 0.0660
-4.000 -0.2241 0.00831 0.00265 -0.0522 0.9296 0.0765
-3.750 -0.1973 0.00810 0.00249 -0.0520 0.9265 0.0901
-3.500 -0.1714 0.00790 0.00235 -0.0516 0.9223 0.1077
-3.250 -0.1453 0.00765 0.00220 -0.0513 0.9183 0.1335
-3.000 -0.1190 0.00738 0.00206 -0.0511 0.9148 0.1677
-2.750 -0.0929 0.00709 0.00192 -0.0508 0.9111 0.2154
-2.500 -0.0686 0.00668 0.00179 -0.0503 0.9065 0.2903
-2.250 -0.0451 0.00615 0.00165 -0.0496 0.9020 0.3998
-2.000 -0.0212 0.00567 0.00152 -0.0489 0.8978 0.5101
-1.750 0.0027 0.00533 0.00147 -0.0482 0.8930 0.5969
-1.500 0.0281 0.00512 0.00143 -0.0476 0.8880 0.6533
-1.250 0.0546 0.00497 0.00139 -0.0473 0.8835 0.6937
-1.000 0.0809 0.00486 0.00139 -0.0468 0.8786 0.7315
-0.750 0.1075 0.00477 0.00138 -0.0465 0.8731 0.7580
-0.500 0.1347 0.00471 0.00135 -0.0462 0.8671 0.7819
-0.250 0.1609 0.00463 0.00133 -0.0457 0.8589 0.8035
0.000 0.1877 0.00457 0.00130 -0.0452 0.8502 0.8239
0.250 0.2135 0.00451 0.00128 -0.0446 0.8376 0.8458
0.500 0.2389 0.00446 0.00128 -0.0437 0.8230 0.8706
0.750 0.2643 0.00446 0.00133 -0.0429 0.8098 0.8967
1.000 0.2898 0.00450 0.00137 -0.0421 0.7952 0.9149
1.250 0.3158 0.00456 0.00140 -0.0415 0.7794 0.9266
1.500 0.3417 0.00465 0.00143 -0.0409 0.7604 0.9358
1.750 0.3676 0.00475 0.00148 -0.0403 0.7396 0.9443
2.000 0.3924 0.00490 0.00155 -0.0395 0.7144 0.9528
2.250 0.4180 0.00509 0.00163 -0.0389 0.6824 0.9597
2.500 0.4435 0.00533 0.00173 -0.0383 0.6436 0.9669
2.750 0.4700 0.00563 0.00186 -0.0380 0.5958 0.9729
3.000 0.4990 0.00608 0.00203 -0.0384 0.5286 0.9772
3.250 0.5226 0.00670 0.00226 -0.0378 0.4346 0.9832
3.500 0.5535 0.00743 0.00254 -0.0390 0.3299 0.9848
3.750 0.5849 0.00805 0.00279 -0.0403 0.2484 0.9866
4.000 0.6164 0.00855 0.00303 -0.0415 0.1908 0.9888
4.250 0.6478 0.00894 0.00325 -0.0426 0.1540 0.9913
4.500 0.6782 0.00931 0.00347 -0.0434 0.1244 0.9940
4.750 0.7115 0.00965 0.00369 -0.0450 0.1002 0.9952
5.000 0.7447 0.00995 0.00390 -0.0464 0.0833 0.9967
5.250 0.7775 0.01025 0.00413 -0.0478 0.0704 0.9983
5.500 0.8102 0.01055 0.00437 -0.0491 0.0605 0.9998
5.750 0.8307 0.01084 0.00460 -0.0478 0.0527 1.0000
6.000 0.8499 0.01103 0.00480 -0.0462 0.0489 1.0000
6.250 0.8673 0.01134 0.00506 -0.0441 0.0434 1.0000
6.500 0.8864 0.01153 0.00527 -0.0424 0.0405 1.0000
6.750 0.9038 0.01185 0.00555 -0.0404 0.0366 1.0000
7.000 0.9225 0.01209 0.00582 -0.0387 0.0343 1.0000
7.250 0.9413 0.01236 0.00608 -0.0369 0.0319 1.0000
7.500 0.9584 0.01278 0.00649 -0.0349 0.0290 1.0000
7.750 0.9784 0.01302 0.00676 -0.0334 0.0277 1.0000
8.000 0.9980 0.01333 0.00707 -0.0319 0.0260 1.0000
8.250 1.0159 0.01382 0.00756 -0.0301 0.0240 1.0000
8.500 1.0363 0.01417 0.00795 -0.0288 0.0230 1.0000
8.750 1.0572 0.01452 0.00832 -0.0276 0.0220 1.0000
9.000 1.0779 0.01490 0.00873 -0.0264 0.0211 1.0000
9.250 1.0979 0.01536 0.00920 -0.0252 0.0202 1.0000
9.500 1.1140 0.01613 0.01002 -0.0233 0.0192 1.0000
9.750 1.1336 0.01662 0.01056 -0.0219 0.0188 1.0000
10.000 1.1534 0.01707 0.01106 -0.0207 0.0184 1.0000
10.250 1.1717 0.01756 0.01160 -0.0192 0.0179 1.0000
10.500 1.1891 0.01807 0.01216 -0.0176 0.0174 1.0000
10.750 1.2064 0.01860 0.01273 -0.0160 0.0170 1.0000
11.000 1.2237 0.01913 0.01329 -0.0144 0.0165 1.0000
11.250 1.2390 0.01981 0.01401 -0.0126 0.0161 1.0000
11.500 1.2499 0.02082 0.01509 -0.0102 0.0156 1.0000
11.750 1.2580 0.02209 0.01647 -0.0075 0.0152 1.0000
12.000 1.2736 0.02275 0.01720 -0.0060 0.0151 1.0000
12.250 1.2879 0.02351 0.01804 -0.0043 0.0149 1.0000
12.500 1.3013 0.02434 0.01895 -0.0026 0.0147 1.0000
12.750 1.3136 0.02525 0.01995 -0.0008 0.0144 1.0000
13.000 1.3249 0.02623 0.02102 0.0010 0.0142 1.0000
13.250 1.3354 0.02728 0.02216 0.0028 0.0140 1.0000
13.500 1.3450 0.02841 0.02337 0.0046 0.0137 1.0000
13.750 1.3538 0.02961 0.02466 0.0064 0.0135 1.0000
14.000 1.3621 0.03086 0.02598 0.0080 0.0133 1.0000
14.250 1.3697 0.03219 0.02739 0.0096 0.0131 1.0000
14.500 1.3764 0.03361 0.02888 0.0111 0.0129 1.0000
14.750 1.3802 0.03532 0.03068 0.0126 0.0127 1.0000
15.000 1.3801 0.03748 0.03294 0.0142 0.0125 1.0000
15.250 1.3741 0.04030 0.03590 0.0157 0.0123 1.0000
15.500 1.3625 0.04387 0.03964 0.0171 0.0122 1.0000
15.750 1.3471 0.04806 0.04403 0.0180 0.0121 1.0000
16.000 1.3448 0.05103 0.04712 0.0180 0.0120 1.0000
16.250 1.3398 0.05449 0.05072 0.0177 0.0120 1.0000
16.500 1.3342 0.05825 0.05461 0.0169 0.0119 1.0000
16.750 1.3251 0.06276 0.05927 0.0155 0.0119 1.0000
17.000 1.3140 0.06786 0.06451 0.0135 0.0118 1.0000
17.250 1.2998 0.07374 0.07054 0.0109 0.0118 1.0000
17.500 1.2825 0.08053 0.07749 0.0075 0.0118 1.0000
17.750 1.2612 0.08841 0.08553 0.0032 0.0118 1.0000
18.000 1.2366 0.09725 0.09454 -0.0017 0.0118 1.0000
18.250 1.2070 0.10742 0.10488 -0.0074 0.0118 1.0000
18.500 1.1712 0.11912 0.11675 -0.0140 0.0119 1.0000
18.750 1.1296 0.13260 0.13041 -0.0217 0.0119 1.0000
19.000 0.9852 0.17506 0.17331 -0.0458 0.0124 1.0000
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Polar data table (+)
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