LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.56 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141d-il-1000000.txt Download as CSV file: xf-c141d-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9053 0.06192 0.05955 -0.0610 1.0000 0.0121
-14.000 -0.9477 0.04868 0.04602 -0.0728 1.0000 0.0120
-13.750 -0.9718 0.04246 0.03957 -0.0764 1.0000 0.0120
-13.500 -0.9896 0.03849 0.03541 -0.0766 1.0000 0.0120
-13.250 -1.0063 0.03580 0.03256 -0.0741 1.0000 0.0120
-13.000 -1.0263 0.03408 0.03071 -0.0689 1.0000 0.0120
-12.750 -1.0514 0.03310 0.02964 -0.0611 1.0000 0.0120
-12.500 -1.0644 0.03175 0.02816 -0.0554 1.0000 0.0121
-12.250 -1.0713 0.03038 0.02664 -0.0506 1.0000 0.0121
-12.000 -1.0606 0.02864 0.02472 -0.0493 0.9991 0.0122
-11.750 -1.0410 0.02696 0.02284 -0.0496 0.9976 0.0124
-11.500 -1.0193 0.02551 0.02121 -0.0499 0.9963 0.0125
-11.250 -0.9954 0.02424 0.01978 -0.0504 0.9952 0.0126
-11.000 -0.9695 0.02316 0.01855 -0.0511 0.9943 0.0127
-10.750 -0.9481 0.02184 0.01707 -0.0509 0.9924 0.0128
-10.500 -0.9282 0.02003 0.01507 -0.0506 0.9903 0.0130
-10.250 -0.9034 0.01889 0.01382 -0.0509 0.9887 0.0133
-10.000 -0.8759 0.01803 0.01289 -0.0516 0.9874 0.0135
-9.750 -0.8469 0.01731 0.01210 -0.0524 0.9864 0.0137
-9.500 -0.8171 0.01664 0.01137 -0.0534 0.9856 0.0140
-9.250 -0.7866 0.01600 0.01066 -0.0544 0.9849 0.0143
-9.000 -0.7555 0.01539 0.00999 -0.0555 0.9843 0.0147
-8.750 -0.7314 0.01487 0.00940 -0.0550 0.9814 0.0150
-8.500 -0.7035 0.01438 0.00884 -0.0553 0.9793 0.0153
-8.250 -0.6738 0.01382 0.00822 -0.0560 0.9778 0.0156
-8.000 -0.6440 0.01311 0.00748 -0.0569 0.9766 0.0163
-7.750 -0.6119 0.01269 0.00704 -0.0581 0.9757 0.0171
-7.500 -0.5797 0.01231 0.00663 -0.0592 0.9748 0.0178
-7.250 -0.5478 0.01195 0.00623 -0.0603 0.9739 0.0185
-7.000 -0.5169 0.01143 0.00569 -0.0612 0.9729 0.0197
-6.750 -0.4899 0.01112 0.00538 -0.0611 0.9703 0.0209
-6.500 -0.4647 0.01081 0.00504 -0.0606 0.9668 0.0225
-6.250 -0.4367 0.01049 0.00474 -0.0607 0.9643 0.0250
-6.000 -0.4077 0.01018 0.00446 -0.0610 0.9622 0.0284
-5.750 -0.3783 0.00992 0.00421 -0.0614 0.9604 0.0322
-5.500 -0.3501 0.00975 0.00403 -0.0615 0.9581 0.0356
-5.250 -0.3261 0.00954 0.00385 -0.0607 0.9538 0.0390
-5.000 -0.2991 0.00933 0.00363 -0.0605 0.9505 0.0419
-4.750 -0.2715 0.00910 0.00342 -0.0604 0.9477 0.0453
-4.500 -0.2436 0.00891 0.00321 -0.0604 0.9452 0.0482
-4.250 -0.2182 0.00871 0.00304 -0.0599 0.9411 0.0522
-4.000 -0.1916 0.00853 0.00287 -0.0595 0.9370 0.0562
-3.750 -0.1644 0.00833 0.00271 -0.0593 0.9335 0.0621
-3.500 -0.1367 0.00814 0.00255 -0.0592 0.9304 0.0697
-3.250 -0.1104 0.00799 0.00243 -0.0589 0.9261 0.0780
-3.000 -0.0833 0.00785 0.00231 -0.0587 0.9216 0.0852
-2.750 -0.0561 0.00765 0.00214 -0.0585 0.9177 0.0957
-2.500 -0.0283 0.00748 0.00200 -0.0584 0.9140 0.1085
-2.250 -0.0024 0.00725 0.00190 -0.0581 0.9089 0.1390
-2.000 0.0233 0.00691 0.00177 -0.0577 0.9038 0.1985
-1.750 0.0483 0.00640 0.00162 -0.0573 0.8992 0.3104
-1.500 0.0709 0.00578 0.00151 -0.0565 0.8934 0.4587
-1.250 0.0944 0.00530 0.00143 -0.0556 0.8876 0.5832
-1.000 0.1201 0.00504 0.00139 -0.0551 0.8824 0.6568
-0.750 0.1460 0.00489 0.00137 -0.0546 0.8757 0.7028
-0.500 0.1721 0.00474 0.00132 -0.0540 0.8669 0.7458
-0.250 0.1972 0.00462 0.00129 -0.0531 0.8537 0.7832
0.000 0.2228 0.00455 0.00126 -0.0524 0.8383 0.8100
0.250 0.2484 0.00451 0.00125 -0.0516 0.8228 0.8377
0.500 0.2735 0.00448 0.00129 -0.0507 0.8081 0.8726
0.750 0.2979 0.00450 0.00134 -0.0496 0.7903 0.9032
1.000 0.3231 0.00457 0.00138 -0.0487 0.7731 0.9221
1.250 0.3487 0.00465 0.00143 -0.0479 0.7551 0.9348
1.500 0.3737 0.00478 0.00149 -0.0470 0.7323 0.9465
1.750 0.3976 0.00493 0.00156 -0.0459 0.7071 0.9581
2.000 0.4247 0.00513 0.00165 -0.0456 0.6768 0.9662
2.250 0.4512 0.00540 0.00176 -0.0451 0.6341 0.9738
2.500 0.4813 0.00577 0.00190 -0.0457 0.5767 0.9784
2.750 0.5076 0.00628 0.00208 -0.0455 0.4966 0.9839
3.000 0.5384 0.00705 0.00233 -0.0467 0.3793 0.9857
3.250 0.5691 0.00772 0.00259 -0.0477 0.2853 0.9879
3.500 0.5995 0.00828 0.00283 -0.0487 0.2151 0.9905
3.750 0.6297 0.00873 0.00304 -0.0495 0.1666 0.9933
4.000 0.6618 0.00914 0.00325 -0.0508 0.1275 0.9950
4.250 0.6950 0.00947 0.00345 -0.0522 0.1059 0.9965
4.500 0.7282 0.00973 0.00364 -0.0536 0.0950 0.9981
4.750 0.7615 0.00996 0.00384 -0.0549 0.0872 0.9996
5.000 0.7851 0.01018 0.00402 -0.0542 0.0810 1.0000
5.250 0.8049 0.01036 0.00418 -0.0526 0.0765 1.0000
5.500 0.8245 0.01054 0.00435 -0.0510 0.0721 1.0000
5.750 0.8434 0.01077 0.00455 -0.0492 0.0673 1.0000
6.000 0.8636 0.01092 0.00471 -0.0477 0.0642 1.0000
6.250 0.8829 0.01116 0.00491 -0.0460 0.0600 1.0000
6.500 0.9031 0.01136 0.00511 -0.0445 0.0568 1.0000
6.750 0.9234 0.01158 0.00531 -0.0430 0.0532 1.0000
7.000 0.9435 0.01184 0.00556 -0.0415 0.0495 1.0000
7.250 0.9645 0.01207 0.00577 -0.0402 0.0461 1.0000
7.500 0.9852 0.01236 0.00605 -0.0389 0.0425 1.0000
7.750 1.0068 0.01264 0.00631 -0.0377 0.0394 1.0000
8.000 1.0281 0.01297 0.00664 -0.0366 0.0365 1.0000
8.250 1.0500 0.01328 0.00694 -0.0355 0.0339 1.0000
8.500 1.0712 0.01368 0.00733 -0.0344 0.0314 1.0000
8.750 1.0932 0.01401 0.00768 -0.0334 0.0294 1.0000
9.000 1.1134 0.01450 0.00816 -0.0321 0.0272 1.0000
9.250 1.1354 0.01483 0.00853 -0.0312 0.0259 1.0000
9.500 1.1563 0.01525 0.00895 -0.0301 0.0244 1.0000
9.750 1.1756 0.01581 0.00952 -0.0287 0.0230 1.0000
10.000 1.1965 0.01620 0.00996 -0.0276 0.0221 1.0000
10.250 1.2164 0.01664 0.01042 -0.0264 0.0212 1.0000
10.500 1.2342 0.01716 0.01097 -0.0248 0.0204 1.0000
10.750 1.2486 0.01792 0.01176 -0.0227 0.0196 1.0000
11.000 1.2670 0.01838 0.01228 -0.0212 0.0192 1.0000
11.250 1.2846 0.01890 0.01286 -0.0197 0.0187 1.0000
11.500 1.3016 0.01946 0.01347 -0.0181 0.0182 1.0000
11.750 1.3181 0.02005 0.01411 -0.0165 0.0178 1.0000
12.000 1.3336 0.02071 0.01481 -0.0148 0.0174 1.0000
12.250 1.3469 0.02153 0.01567 -0.0128 0.0170 1.0000
12.500 1.3552 0.02268 0.01690 -0.0102 0.0165 1.0000
12.750 1.3670 0.02360 0.01790 -0.0082 0.0163 1.0000
13.000 1.3810 0.02436 0.01874 -0.0066 0.0161 1.0000
13.250 1.3939 0.02521 0.01966 -0.0049 0.0158 1.0000
13.500 1.4060 0.02611 0.02065 -0.0032 0.0156 1.0000
13.750 1.4170 0.02710 0.02171 -0.0014 0.0153 1.0000
14.000 1.4267 0.02820 0.02289 0.0003 0.0151 1.0000
14.250 1.4356 0.02937 0.02414 0.0021 0.0149 1.0000
14.500 1.4435 0.03066 0.02551 0.0038 0.0147 1.0000
14.750 1.4502 0.03205 0.02699 0.0054 0.0145 1.0000
15.000 1.4556 0.03360 0.02862 0.0070 0.0144 1.0000
15.250 1.4589 0.03539 0.03049 0.0086 0.0142 1.0000
15.500 1.4597 0.03745 0.03264 0.0100 0.0141 1.0000
15.750 1.4573 0.03991 0.03520 0.0114 0.0139 1.0000
16.000 1.4508 0.04290 0.03832 0.0126 0.0138 1.0000
16.250 1.4401 0.04650 0.04207 0.0134 0.0136 1.0000
16.500 1.4310 0.05018 0.04589 0.0137 0.0135 1.0000
16.750 1.4273 0.05347 0.04930 0.0135 0.0135 1.0000
17.000 1.4217 0.05719 0.05315 0.0129 0.0134 1.0000
17.250 1.4146 0.06135 0.05745 0.0118 0.0134 1.0000
17.500 1.4045 0.06618 0.06242 0.0102 0.0134 1.0000
17.750 1.3922 0.07157 0.06796 0.0080 0.0133 1.0000
18.000 1.3771 0.07771 0.07424 0.0052 0.0133 1.0000
18.250 1.3592 0.08466 0.08135 0.0017 0.0133 1.0000
18.500 1.3379 0.09243 0.08926 -0.0023 0.0133 1.0000
18.750 1.3141 0.10092 0.09791 -0.0069 0.0133 1.0000
19.000 1.2882 0.11002 0.10717 -0.0118 0.0133 1.0000
19.250 1.2597 0.11977 0.11706 -0.0172 0.0133 1.0000
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Polar data table (+)
Polar graphs
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