LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 100,000 Max Cl/Cd: 44.93 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141c-il-100000-n5.txt Download as CSV file: xf-c141c-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5685 0.08936 0.08384 -0.0442 1.0000 0.0368
-10.500 -0.5911 0.07948 0.07401 -0.0507 1.0000 0.0363
-10.250 -0.6323 0.06883 0.06331 -0.0575 1.0000 0.0353
-10.000 -0.6718 0.06344 0.05784 -0.0565 1.0000 0.0348
-9.750 -0.7056 0.05979 0.05407 -0.0522 1.0000 0.0346
-9.500 -0.7288 0.05631 0.05042 -0.0483 1.0000 0.0346
-9.250 -0.7455 0.05308 0.04697 -0.0443 1.0000 0.0349
-9.000 -0.7576 0.04988 0.04351 -0.0405 1.0000 0.0352
-8.750 -0.7657 0.04666 0.03996 -0.0367 1.0000 0.0356
-8.500 -0.7695 0.04349 0.03642 -0.0332 1.0000 0.0360
-8.000 -0.7642 0.03770 0.02977 -0.0270 1.0000 0.0373
-7.750 -0.7558 0.03512 0.02670 -0.0244 1.0000 0.0383
-7.500 -0.7437 0.03313 0.02435 -0.0222 1.0000 0.0397
-7.250 -0.7284 0.03207 0.02325 -0.0207 1.0000 0.0412
-7.000 -0.7123 0.03087 0.02188 -0.0190 1.0000 0.0430
-6.750 -0.6949 0.02941 0.02014 -0.0175 1.0000 0.0447
-6.500 -0.6760 0.02795 0.01838 -0.0160 1.0000 0.0465
-6.250 -0.6569 0.02676 0.01705 -0.0147 1.0000 0.0488
-6.000 -0.6376 0.02600 0.01626 -0.0136 1.0000 0.0515
-5.750 -0.6117 0.02505 0.01514 -0.0136 0.9986 0.0549
-5.500 -0.5818 0.02404 0.01397 -0.0143 0.9962 0.0587
-5.250 -0.5515 0.02331 0.01327 -0.0154 0.9938 0.0634
-5.000 -0.5222 0.02257 0.01238 -0.0159 0.9908 0.0684
-4.750 -0.4929 0.02186 0.01171 -0.0167 0.9878 0.0745
-4.500 -0.4615 0.02129 0.01104 -0.0177 0.9850 0.0819
-4.250 -0.4320 0.02070 0.01050 -0.0186 0.9820 0.0910
-4.000 -0.4038 0.02015 0.00997 -0.0190 0.9781 0.1020
-3.750 -0.3735 0.01967 0.00953 -0.0200 0.9746 0.1178
-3.500 -0.3414 0.01921 0.00915 -0.0212 0.9718 0.1410
-3.250 -0.3134 0.01868 0.00880 -0.0218 0.9678 0.1771
-3.000 -0.2860 0.01805 0.00851 -0.0222 0.9635 0.2439
-2.750 -0.2582 0.01709 0.00831 -0.0230 0.9602 0.3969
-2.500 -0.2309 0.01629 0.00842 -0.0228 0.9575 0.6031
-2.250 -0.2065 0.01610 0.00860 -0.0214 0.9529 0.7134
-2.000 -0.1795 0.01611 0.00875 -0.0205 0.9482 0.7844
-1.750 -0.1463 0.01626 0.00895 -0.0208 0.9450 0.8385
-1.500 -0.1076 0.01649 0.00917 -0.0223 0.9426 0.8819
-1.250 -0.0670 0.01678 0.00941 -0.0243 0.9399 0.9208
-1.000 -0.0095 0.01719 0.00975 -0.0297 0.9401 0.9580
-0.750 0.0451 0.01736 0.00983 -0.0353 0.9386 0.9732
-0.500 0.0890 0.01740 0.00979 -0.0391 0.9347 0.9824
-0.250 0.1365 0.01739 0.00974 -0.0436 0.9316 0.9892
0.000 0.1847 0.01737 0.00968 -0.0482 0.9290 0.9957
0.250 0.2266 0.01732 0.00962 -0.0516 0.9250 1.0000
0.500 0.2504 0.01727 0.00956 -0.0513 0.9164 1.0000
0.750 0.2882 0.01717 0.00946 -0.0536 0.9124 1.0000
1.000 0.3073 0.01716 0.00946 -0.0522 0.9020 1.0000
1.250 0.3442 0.01703 0.00936 -0.0541 0.8975 1.0000
1.500 0.3634 0.01702 0.00937 -0.0526 0.8867 1.0000
1.750 0.3957 0.01684 0.00923 -0.0534 0.8786 1.0000
2.000 0.4287 0.01654 0.00899 -0.0540 0.8680 1.0000
2.250 0.4618 0.01603 0.00853 -0.0542 0.8520 1.0000
2.500 0.4858 0.01563 0.00816 -0.0527 0.8309 1.0000
2.750 0.5110 0.01529 0.00786 -0.0514 0.8101 1.0000
3.000 0.5384 0.01498 0.00759 -0.0506 0.7893 1.0000
3.250 0.5618 0.01479 0.00743 -0.0492 0.7635 1.0000
3.500 0.5887 0.01457 0.00722 -0.0483 0.7322 1.0000
3.750 0.6160 0.01443 0.00701 -0.0474 0.6893 1.0000
4.000 0.6429 0.01442 0.00681 -0.0464 0.6255 1.0000
4.250 0.6636 0.01477 0.00674 -0.0443 0.5325 1.0000
4.500 0.6752 0.01556 0.00692 -0.0410 0.4194 1.0000
4.750 0.6841 0.01654 0.00732 -0.0376 0.3202 1.0000
5.000 0.6955 0.01746 0.00781 -0.0347 0.2480 1.0000
5.250 0.7093 0.01826 0.00832 -0.0323 0.1992 1.0000
5.500 0.7245 0.01899 0.00888 -0.0302 0.1658 1.0000
5.750 0.7404 0.01970 0.00945 -0.0282 0.1416 1.0000
6.000 0.7570 0.02039 0.01006 -0.0263 0.1231 1.0000
6.250 0.7738 0.02109 0.01071 -0.0244 0.1089 1.0000
6.500 0.7904 0.02184 0.01143 -0.0226 0.0978 1.0000
6.750 0.8071 0.02262 0.01216 -0.0208 0.0885 1.0000
7.000 0.8250 0.02337 0.01296 -0.0191 0.0804 1.0000
7.250 0.8414 0.02428 0.01381 -0.0174 0.0744 1.0000
7.500 0.8601 0.02507 0.01473 -0.0159 0.0682 1.0000
7.750 0.8770 0.02605 0.01566 -0.0144 0.0637 1.0000
8.000 0.8965 0.02702 0.01676 -0.0131 0.0593 1.0000
8.250 0.9149 0.02795 0.01773 -0.0118 0.0553 1.0000
8.500 0.9330 0.02920 0.01896 -0.0106 0.0525 1.0000
8.750 0.9538 0.03041 0.02039 -0.0095 0.0495 1.0000
9.000 0.9724 0.03154 0.02163 -0.0083 0.0466 1.0000
9.250 0.9897 0.03269 0.02279 -0.0071 0.0444 1.0000
9.500 1.0091 0.03437 0.02459 -0.0061 0.0427 1.0000
9.750 1.0278 0.03619 0.02674 -0.0050 0.0411 1.0000
10.000 1.0436 0.03801 0.02881 -0.0035 0.0395 1.0000
10.250 1.0569 0.03961 0.03060 -0.0019 0.0381 1.0000
10.500 1.0689 0.04104 0.03213 -0.0002 0.0368 1.0000
10.750 1.0809 0.04281 0.03394 0.0013 0.0357 1.0000
11.000 1.0833 0.04521 0.03678 0.0043 0.0349 1.0000
11.250 1.0819 0.04787 0.03983 0.0075 0.0343 1.0000
11.500 1.0762 0.05072 0.04303 0.0108 0.0338 1.0000
11.750 1.0667 0.05378 0.04643 0.0139 0.0334 1.0000
12.000 1.0534 0.05714 0.05010 0.0167 0.0332 1.0000
12.250 1.0364 0.06090 0.05416 0.0190 0.0330 1.0000
12.500 1.0158 0.06523 0.05877 0.0203 0.0329 1.0000
12.750 0.9913 0.07036 0.06418 0.0205 0.0329 1.0000
13.000 0.9624 0.07670 0.07077 0.0188 0.0330 1.0000
13.250 0.9282 0.08502 0.07932 0.0147 0.0333 1.0000
13.500 0.8849 0.09738 0.09187 0.0064 0.0338 1.0000
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Polar data table (+)
Polar graphs
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