LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 50,000 Max Cl/Cd: 30.79 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141c-il-50000-n5.txt Download as CSV file: xf-c141c-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5362 0.10051 0.09268 -0.0396 1.0000 0.0643
-10.250 -0.5448 0.09494 0.08718 -0.0423 1.0000 0.0638
-10.000 -0.5577 0.08852 0.08082 -0.0459 1.0000 0.0630
-9.750 -0.5805 0.08145 0.07382 -0.0501 1.0000 0.0620
-9.500 -0.6119 0.07609 0.06847 -0.0507 1.0000 0.0610
-9.250 -0.6418 0.07184 0.06419 -0.0487 1.0000 0.0604
-9.000 -0.6643 0.06779 0.06001 -0.0463 1.0000 0.0600
-8.750 -0.6808 0.06402 0.05607 -0.0437 1.0000 0.0599
-8.500 -0.6921 0.06047 0.05230 -0.0408 1.0000 0.0600
-8.250 -0.6985 0.05714 0.04872 -0.0380 1.0000 0.0603
-8.000 -0.7010 0.05398 0.04529 -0.0353 1.0000 0.0608
-7.750 -0.6993 0.05118 0.04222 -0.0327 1.0000 0.0620
-7.500 -0.6955 0.04850 0.03922 -0.0302 1.0000 0.0638
-7.250 -0.6900 0.04569 0.03596 -0.0277 1.0000 0.0659
-7.000 -0.6820 0.04281 0.03253 -0.0252 1.0000 0.0679
-6.750 -0.6699 0.04015 0.02939 -0.0231 1.0000 0.0694
-6.500 -0.6542 0.03837 0.02755 -0.0217 1.0000 0.0719
-6.250 -0.6378 0.03682 0.02581 -0.0202 1.0000 0.0757
-6.000 -0.6197 0.03499 0.02355 -0.0186 1.0000 0.0797
-5.750 -0.5997 0.03322 0.02150 -0.0173 1.0000 0.0830
-5.500 -0.5802 0.03203 0.02028 -0.0162 1.0000 0.0882
-5.250 -0.5585 0.03076 0.01870 -0.0150 1.0000 0.0943
-5.000 -0.5369 0.02955 0.01750 -0.0140 1.0000 0.0998
-4.750 -0.5149 0.02862 0.01636 -0.0129 1.0000 0.1085
-4.500 -0.4930 0.02765 0.01544 -0.0119 1.0000 0.1167
-4.250 -0.4710 0.02682 0.01455 -0.0109 1.0000 0.1284
-4.000 -0.4490 0.02603 0.01371 -0.0100 1.0000 0.1421
-3.750 -0.4273 0.02524 0.01298 -0.0092 1.0000 0.1610
-3.500 -0.4058 0.02443 0.01226 -0.0084 1.0000 0.1876
-3.250 -0.3859 0.02352 0.01161 -0.0075 1.0000 0.2314
-3.000 -0.3675 0.02225 0.01104 -0.0065 1.0000 0.3329
-2.750 -0.3544 0.02091 0.01108 -0.0033 1.0000 0.5748
-2.500 -0.3374 0.02073 0.01145 0.0008 1.0000 0.7499
-2.250 -0.3054 0.02106 0.01186 0.0019 1.0000 0.8601
-2.000 -0.2452 0.02171 0.01227 -0.0031 1.0000 0.9443
-1.750 -0.1397 0.02237 0.01246 -0.0181 1.0000 1.0000
-1.500 -0.1365 0.02218 0.01215 -0.0148 1.0000 1.0000
-1.250 -0.1313 0.02206 0.01189 -0.0117 1.0000 1.0000
-1.000 -0.1241 0.02200 0.01170 -0.0090 1.0000 1.0000
-0.750 -0.1150 0.02200 0.01158 -0.0065 1.0000 1.0000
-0.500 -0.0840 0.02225 0.01165 -0.0082 0.9945 1.0000
-0.250 -0.0509 0.02251 0.01178 -0.0102 0.9874 1.0000
0.000 -0.0178 0.02282 0.01196 -0.0122 0.9806 1.0000
0.250 0.0152 0.02313 0.01218 -0.0141 0.9733 1.0000
0.500 0.0466 0.02343 0.01241 -0.0156 0.9657 1.0000
0.750 0.0807 0.02379 0.01270 -0.0176 0.9584 1.0000
1.000 0.1103 0.02408 0.01297 -0.0187 0.9498 1.0000
1.250 0.1461 0.02446 0.01332 -0.0209 0.9427 1.0000
1.500 0.1737 0.02474 0.01361 -0.0215 0.9328 1.0000
1.750 0.2086 0.02508 0.01397 -0.0235 0.9249 1.0000
2.000 0.2390 0.02537 0.01431 -0.0245 0.9151 1.0000
2.250 0.2685 0.02566 0.01465 -0.0253 0.9046 1.0000
2.500 0.3054 0.02592 0.01499 -0.0273 0.8953 1.0000
2.750 0.3393 0.02609 0.01528 -0.0287 0.8835 1.0000
3.000 0.3705 0.02621 0.01551 -0.0294 0.8697 1.0000
3.250 0.4044 0.02622 0.01565 -0.0303 0.8551 1.0000
3.500 0.4460 0.02588 0.01550 -0.0321 0.8377 1.0000
3.750 0.4811 0.02534 0.01513 -0.0322 0.8148 1.0000
4.000 0.5240 0.02443 0.01445 -0.0331 0.7912 1.0000
4.250 0.5516 0.02384 0.01403 -0.0316 0.7636 1.0000
4.500 0.5813 0.02315 0.01351 -0.0301 0.7316 1.0000
4.750 0.6073 0.02263 0.01311 -0.0282 0.6899 1.0000
5.000 0.6374 0.02206 0.01259 -0.0266 0.6289 1.0000
5.250 0.6710 0.02179 0.01190 -0.0253 0.5127 1.0000
5.500 0.6848 0.02274 0.01200 -0.0220 0.3793 1.0000
5.750 0.6916 0.02414 0.01277 -0.0185 0.2915 1.0000
6.000 0.7016 0.02551 0.01369 -0.0158 0.2360 1.0000
6.250 0.7153 0.02678 0.01470 -0.0138 0.1986 1.0000
6.500 0.7310 0.02802 0.01575 -0.0121 0.1722 1.0000
6.750 0.7501 0.02920 0.01688 -0.0108 0.1512 1.0000
7.000 0.7710 0.03038 0.01805 -0.0098 0.1344 1.0000
7.250 0.7952 0.03161 0.01930 -0.0093 0.1208 1.0000
7.500 0.8206 0.03292 0.02065 -0.0089 0.1095 1.0000
7.750 0.8459 0.03434 0.02201 -0.0087 0.1007 1.0000
8.000 0.8718 0.03582 0.02374 -0.0084 0.0922 1.0000
8.250 0.8975 0.03755 0.02547 -0.0082 0.0864 1.0000
8.500 0.9197 0.03930 0.02754 -0.0074 0.0802 1.0000
8.750 0.9413 0.04111 0.02942 -0.0068 0.0762 1.0000
9.000 0.9604 0.04346 0.03211 -0.0057 0.0725 1.0000
9.250 0.9750 0.04570 0.03472 -0.0041 0.0687 1.0000
9.500 0.9888 0.04784 0.03707 -0.0026 0.0659 1.0000
9.750 1.0025 0.05027 0.03964 -0.0013 0.0641 1.0000
10.000 1.0093 0.05324 0.04296 0.0009 0.0626 1.0000
10.250 1.0064 0.05649 0.04673 0.0040 0.0611 1.0000
10.500 0.9996 0.05976 0.05042 0.0072 0.0598 1.0000
10.750 0.9888 0.06299 0.05398 0.0104 0.0588 1.0000
11.000 0.9738 0.06629 0.05755 0.0136 0.0581 1.0000
11.250 0.9553 0.06999 0.06150 0.0162 0.0577 1.0000
11.500 0.9327 0.07433 0.06608 0.0177 0.0576 1.0000
11.750 0.9055 0.07963 0.07159 0.0178 0.0578 1.0000
12.000 0.8740 0.08636 0.07848 0.0158 0.0583 1.0000
12.250 0.8403 0.09498 0.08722 0.0112 0.0592 1.0000
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Polar data table (+)
Polar graphs
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