LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 500,000 Max Cl/Cd: 65.12 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141d-il-500000-n5.txt Download as CSV file: xf-c141d-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL610.61 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9354 0.05222 0.04880 -0.0695 1.0000 0.0112
-13.750 -0.9620 0.04502 0.04135 -0.0744 1.0000 0.0111
-13.500 -0.9785 0.04085 0.03697 -0.0752 1.0000 0.0112
-13.250 -0.9917 0.03796 0.03391 -0.0739 1.0000 0.0112
-13.000 -1.0051 0.03590 0.03171 -0.0705 1.0000 0.0112
-12.750 -1.0213 0.03448 0.03017 -0.0651 1.0000 0.0113
-12.500 -1.0347 0.03326 0.02883 -0.0595 1.0000 0.0113
-12.250 -1.0402 0.03194 0.02737 -0.0550 1.0000 0.0114
-12.000 -1.0339 0.03041 0.02568 -0.0529 0.9991 0.0115
-11.750 -1.0163 0.02877 0.02384 -0.0529 0.9972 0.0116
-11.500 -0.9966 0.02726 0.02215 -0.0530 0.9955 0.0118
-11.250 -0.9750 0.02588 0.02058 -0.0532 0.9941 0.0120
-11.000 -0.9546 0.02466 0.01919 -0.0529 0.9918 0.0122
-10.750 -0.9320 0.02352 0.01789 -0.0530 0.9896 0.0123
-10.500 -0.9078 0.02249 0.01670 -0.0532 0.9878 0.0125
-10.250 -0.8824 0.02155 0.01561 -0.0535 0.9864 0.0127
-10.000 -0.8569 0.02052 0.01448 -0.0540 0.9851 0.0129
-9.750 -0.8294 0.01967 0.01356 -0.0547 0.9841 0.0133
-9.500 -0.8064 0.01902 0.01284 -0.0542 0.9812 0.0136
-9.250 -0.7807 0.01840 0.01214 -0.0543 0.9790 0.0140
-9.000 -0.7533 0.01777 0.01144 -0.0547 0.9772 0.0144
-8.750 -0.7247 0.01714 0.01073 -0.0553 0.9757 0.0149
-8.500 -0.6952 0.01653 0.01003 -0.0561 0.9745 0.0153
-8.250 -0.6655 0.01592 0.00934 -0.0569 0.9734 0.0157
-8.000 -0.6355 0.01535 0.00875 -0.0577 0.9724 0.0163
-7.750 -0.6120 0.01492 0.00828 -0.0571 0.9688 0.0169
-7.500 -0.5856 0.01449 0.00780 -0.0570 0.9660 0.0177
-7.250 -0.5572 0.01407 0.00731 -0.0573 0.9638 0.0186
-7.000 -0.5284 0.01363 0.00687 -0.0578 0.9619 0.0197
-6.750 -0.4986 0.01325 0.00646 -0.0584 0.9603 0.0213
-6.500 -0.4686 0.01288 0.00609 -0.0590 0.9589 0.0233
-6.250 -0.4461 0.01261 0.00580 -0.0580 0.9541 0.0256
-6.000 -0.4195 0.01231 0.00551 -0.0578 0.9508 0.0282
-5.750 -0.3912 0.01202 0.00521 -0.0580 0.9483 0.0309
-5.500 -0.3621 0.01175 0.00493 -0.0584 0.9461 0.0339
-5.250 -0.3342 0.01149 0.00466 -0.0584 0.9436 0.0367
-5.000 -0.3098 0.01128 0.00445 -0.0577 0.9389 0.0398
-4.750 -0.2828 0.01103 0.00421 -0.0576 0.9355 0.0432
-4.500 -0.2545 0.01081 0.00397 -0.0577 0.9326 0.0467
-4.250 -0.2257 0.01056 0.00375 -0.0579 0.9302 0.0512
-4.000 -0.2004 0.01038 0.00359 -0.0574 0.9256 0.0563
-3.750 -0.1737 0.01019 0.00343 -0.0572 0.9213 0.0623
-3.500 -0.1459 0.00997 0.00324 -0.0571 0.9177 0.0685
-3.250 -0.1169 0.00978 0.00305 -0.0574 0.9148 0.0750
-3.000 -0.0912 0.00962 0.00291 -0.0569 0.9095 0.0824
-2.750 -0.0643 0.00945 0.00276 -0.0567 0.9045 0.0896
-2.500 -0.0361 0.00926 0.00259 -0.0567 0.9005 0.0990
-2.250 -0.0091 0.00906 0.00246 -0.0565 0.8958 0.1148
-2.000 0.0168 0.00883 0.00236 -0.0562 0.8900 0.1459
-1.750 0.0437 0.00852 0.00222 -0.0560 0.8853 0.1955
-1.500 0.0692 0.00813 0.00210 -0.0557 0.8801 0.2744
-1.250 0.0930 0.00761 0.00198 -0.0551 0.8739 0.3920
-1.000 0.1165 0.00702 0.00187 -0.0544 0.8685 0.5343
-0.750 0.1396 0.00664 0.00186 -0.0533 0.8619 0.6387
-0.500 0.1654 0.00645 0.00185 -0.0527 0.8555 0.6924
-0.250 0.1921 0.00633 0.00183 -0.0523 0.8496 0.7324
0.000 0.2166 0.00617 0.00187 -0.0513 0.8411 0.7862
0.250 0.2411 0.00605 0.00190 -0.0501 0.8283 0.8365
0.500 0.2663 0.00603 0.00188 -0.0491 0.8056 0.8663
0.750 0.2912 0.00608 0.00186 -0.0480 0.7743 0.8890
1.000 0.3162 0.00619 0.00187 -0.0470 0.7435 0.9084
1.250 0.3410 0.00637 0.00190 -0.0460 0.7056 0.9227
1.500 0.3666 0.00659 0.00197 -0.0453 0.6670 0.9356
1.750 0.3928 0.00682 0.00206 -0.0448 0.6304 0.9465
2.000 0.4173 0.00713 0.00217 -0.0440 0.5825 0.9558
2.250 0.4432 0.00757 0.00232 -0.0436 0.5158 0.9623
2.500 0.4664 0.00810 0.00251 -0.0428 0.4382 0.9701
2.750 0.4927 0.00874 0.00275 -0.0429 0.3482 0.9748
3.000 0.5201 0.00933 0.00300 -0.0432 0.2742 0.9796
3.250 0.5481 0.00979 0.00322 -0.0435 0.2215 0.9842
3.500 0.5797 0.01022 0.00344 -0.0447 0.1795 0.9866
4.000 0.6410 0.01095 0.00388 -0.0465 0.1212 0.9931
4.250 0.6724 0.01127 0.00410 -0.0475 0.1048 0.9955
4.500 0.7045 0.01156 0.00433 -0.0487 0.0942 0.9980
4.750 0.7343 0.01182 0.00456 -0.0493 0.0868 1.0000
5.000 0.7537 0.01205 0.00476 -0.0477 0.0812 1.0000
5.250 0.7734 0.01228 0.00497 -0.0461 0.0767 1.0000
5.500 0.7933 0.01249 0.00518 -0.0445 0.0724 1.0000
5.750 0.8128 0.01277 0.00542 -0.0429 0.0679 1.0000
6.000 0.8333 0.01298 0.00565 -0.0415 0.0643 1.0000
6.250 0.8533 0.01325 0.00589 -0.0400 0.0600 1.0000
6.500 0.8739 0.01351 0.00615 -0.0386 0.0563 1.0000
6.750 0.8947 0.01379 0.00642 -0.0373 0.0524 1.0000
7.000 0.9157 0.01409 0.00671 -0.0361 0.0490 1.0000
7.250 0.9371 0.01439 0.00701 -0.0349 0.0454 1.0000
7.500 0.9583 0.01473 0.00734 -0.0338 0.0423 1.0000
7.750 0.9797 0.01506 0.00768 -0.0327 0.0393 1.0000
8.000 1.0008 0.01544 0.00805 -0.0315 0.0367 1.0000
8.250 1.0221 0.01580 0.00844 -0.0305 0.0342 1.0000
8.500 1.0427 0.01623 0.00886 -0.0293 0.0319 1.0000
8.750 1.0637 0.01662 0.00928 -0.0282 0.0298 1.0000
9.000 1.0840 0.01708 0.00974 -0.0270 0.0279 1.0000
9.250 1.1040 0.01754 0.01024 -0.0258 0.0265 1.0000
9.500 1.1236 0.01800 0.01074 -0.0245 0.0251 1.0000
9.750 1.1420 0.01850 0.01127 -0.0230 0.0239 1.0000
10.000 1.1596 0.01905 0.01185 -0.0214 0.0229 1.0000
10.250 1.1775 0.01958 0.01244 -0.0199 0.0220 1.0000
10.500 1.1949 0.02014 0.01305 -0.0183 0.0211 1.0000
10.750 1.2118 0.02075 0.01370 -0.0168 0.0203 1.0000
11.000 1.2272 0.02147 0.01444 -0.0150 0.0196 1.0000
11.250 1.2438 0.02209 0.01515 -0.0135 0.0190 1.0000
11.500 1.2596 0.02276 0.01590 -0.0119 0.0184 1.0000
11.750 1.2748 0.02349 0.01670 -0.0103 0.0178 1.0000
12.000 1.2892 0.02426 0.01754 -0.0086 0.0174 1.0000
12.250 1.3026 0.02511 0.01844 -0.0069 0.0170 1.0000
12.500 1.3142 0.02608 0.01947 -0.0050 0.0166 1.0000
12.750 1.3248 0.02713 0.02061 -0.0031 0.0163 1.0000
13.000 1.3362 0.02814 0.02171 -0.0014 0.0161 1.0000
13.250 1.3466 0.02923 0.02291 0.0004 0.0158 1.0000
13.500 1.3560 0.03041 0.02419 0.0021 0.0155 1.0000
13.750 1.3645 0.03168 0.02557 0.0038 0.0152 1.0000
14.000 1.3719 0.03306 0.02705 0.0054 0.0150 1.0000
14.250 1.3784 0.03454 0.02864 0.0070 0.0148 1.0000
14.500 1.3839 0.03615 0.03036 0.0085 0.0146 1.0000
14.750 1.3882 0.03792 0.03223 0.0098 0.0144 1.0000
15.000 1.3912 0.03986 0.03428 0.0110 0.0143 1.0000
15.250 1.3924 0.04204 0.03657 0.0121 0.0141 1.0000
15.500 1.3920 0.04449 0.03914 0.0129 0.0140 1.0000
15.750 1.3894 0.04727 0.04203 0.0135 0.0138 1.0000
16.000 1.3844 0.05049 0.04536 0.0137 0.0137 1.0000
16.250 1.3767 0.05420 0.04920 0.0135 0.0136 1.0000
16.500 1.3707 0.05798 0.05313 0.0128 0.0135 1.0000
16.750 1.3628 0.06228 0.05759 0.0117 0.0134 1.0000
17.000 1.3526 0.06718 0.06266 0.0099 0.0133 1.0000
17.250 1.3401 0.07273 0.06837 0.0076 0.0133 1.0000
17.500 1.3240 0.07922 0.07503 0.0045 0.0132 1.0000
17.750 1.3050 0.08660 0.08259 0.0006 0.0132 1.0000
18.000 1.2822 0.09496 0.09113 -0.0039 0.0132 1.0000
18.250 1.2557 0.10433 0.10067 -0.0090 0.0132 1.0000
18.500 1.2268 0.11433 0.11083 -0.0145 0.0132 1.0000
18.750 1.1967 0.12471 0.12137 -0.0202 0.0132 1.0000
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Polar data table (+)
Polar graphs
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