LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 500,000 Max Cl/Cd: 80.09 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141c-il-500000.txt Download as CSV file: xf-c141c-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7254 0.06545 0.06281 -0.0592 1.0000 0.0209
-12.000 -0.7630 0.05546 0.05263 -0.0675 1.0000 0.0206
-11.750 -0.7967 0.04953 0.04650 -0.0692 1.0000 0.0204
-11.500 -0.8292 0.04590 0.04269 -0.0660 1.0000 0.0203
-11.250 -0.8626 0.04397 0.04065 -0.0589 1.0000 0.0203
-11.000 -0.8932 0.04167 0.03817 -0.0516 1.0000 0.0202
-10.750 -0.9177 0.03896 0.03522 -0.0451 1.0000 0.0202
-10.500 -0.9347 0.03623 0.03220 -0.0394 1.0000 0.0203
-10.250 -0.9436 0.03368 0.02936 -0.0346 1.0000 0.0204
-10.000 -0.9354 0.03086 0.02614 -0.0330 0.9987 0.0207
-9.750 -0.9149 0.02851 0.02342 -0.0332 0.9967 0.0210
-9.500 -0.8901 0.02695 0.02156 -0.0337 0.9950 0.0213
-9.250 -0.8708 0.02394 0.01824 -0.0337 0.9933 0.0220
-9.000 -0.8458 0.02286 0.01710 -0.0340 0.9911 0.0226
-8.750 -0.8182 0.02215 0.01632 -0.0346 0.9891 0.0234
-8.500 -0.7895 0.02131 0.01537 -0.0354 0.9873 0.0242
-8.250 -0.7599 0.02033 0.01424 -0.0362 0.9858 0.0250
-8.000 -0.7291 0.01948 0.01324 -0.0373 0.9846 0.0258
-7.750 -0.6993 0.01827 0.01188 -0.0382 0.9836 0.0268
-7.500 -0.6769 0.01739 0.01097 -0.0376 0.9802 0.0279
-7.250 -0.6488 0.01687 0.01043 -0.0380 0.9777 0.0291
-7.000 -0.6182 0.01641 0.00991 -0.0388 0.9758 0.0308
-6.750 -0.5864 0.01598 0.00939 -0.0399 0.9742 0.0323
-6.500 -0.5563 0.01509 0.00852 -0.0409 0.9728 0.0348
-6.250 -0.5227 0.01470 0.00810 -0.0424 0.9718 0.0372
-6.000 -0.4884 0.01432 0.00766 -0.0440 0.9709 0.0395
-5.750 -0.4701 0.01375 0.00710 -0.0422 0.9657 0.0426
-5.500 -0.4394 0.01347 0.00681 -0.0430 0.9632 0.0461
-5.250 -0.4081 0.01298 0.00630 -0.0440 0.9614 0.0502
-5.000 -0.3743 0.01265 0.00599 -0.0455 0.9600 0.0552
-4.750 -0.3399 0.01224 0.00558 -0.0471 0.9588 0.0616
-4.500 -0.3043 0.01197 0.00532 -0.0490 0.9579 0.0688
-4.250 -0.2701 0.01157 0.00498 -0.0505 0.9569 0.0800
-4.000 -0.2508 0.01131 0.00478 -0.0488 0.9509 0.0917
-3.750 -0.2209 0.01098 0.00452 -0.0493 0.9480 0.1119
-3.500 -0.1898 0.01057 0.00427 -0.0502 0.9459 0.1458
-3.250 -0.1587 0.01009 0.00403 -0.0512 0.9440 0.2024
-3.000 -0.1293 0.00945 0.00378 -0.0519 0.9422 0.3001
-2.750 -0.1126 0.00881 0.00364 -0.0499 0.9359 0.4281
-2.500 -0.0896 0.00815 0.00350 -0.0490 0.9320 0.5635
-2.250 -0.0630 0.00774 0.00339 -0.0487 0.9293 0.6516
-2.000 -0.0344 0.00748 0.00330 -0.0486 0.9272 0.7082
-1.750 -0.0122 0.00737 0.00331 -0.0472 0.9212 0.7458
-1.500 0.0148 0.00722 0.00324 -0.0467 0.9173 0.7794
-1.250 0.0434 0.00706 0.00316 -0.0466 0.9143 0.8064
-1.000 0.0717 0.00696 0.00310 -0.0464 0.9111 0.8307
-0.750 0.0962 0.00691 0.00313 -0.0453 0.9051 0.8521
-0.500 0.1241 0.00683 0.00309 -0.0450 0.9010 0.8722
-0.250 0.1531 0.00677 0.00305 -0.0448 0.8977 0.8916
0.000 0.1770 0.00683 0.00316 -0.0435 0.8913 0.9126
0.250 0.2045 0.00685 0.00320 -0.0427 0.8855 0.9309
0.500 0.2322 0.00685 0.00319 -0.0421 0.8782 0.9429
0.750 0.2641 0.00679 0.00309 -0.0425 0.8684 0.9490
1.000 0.2918 0.00673 0.00300 -0.0420 0.8551 0.9571
1.250 0.3269 0.00671 0.00296 -0.0433 0.8427 0.9610
1.500 0.3611 0.00672 0.00294 -0.0445 0.8307 0.9661
1.750 0.3947 0.00673 0.00293 -0.0455 0.8174 0.9714
2.000 0.4342 0.00674 0.00292 -0.0480 0.8009 0.9739
2.250 0.4713 0.00678 0.00291 -0.0499 0.7804 0.9776
2.500 0.5031 0.00687 0.00292 -0.0506 0.7543 0.9832
2.750 0.5398 0.00698 0.00290 -0.0525 0.7187 0.9855
3.000 0.5743 0.00719 0.00293 -0.0540 0.6723 0.9888
3.250 0.6055 0.00756 0.00303 -0.0548 0.6066 0.9930
3.500 0.6356 0.00820 0.00320 -0.0557 0.5020 0.9962
3.750 0.6639 0.00916 0.00351 -0.0566 0.3638 0.9995
4.000 0.6815 0.00986 0.00379 -0.0550 0.2740 1.0000
4.250 0.6970 0.01042 0.00404 -0.0529 0.2109 1.0000
4.500 0.7135 0.01086 0.00428 -0.0509 0.1696 1.0000
4.750 0.7305 0.01125 0.00451 -0.0490 0.1393 1.0000
5.000 0.7473 0.01164 0.00477 -0.0470 0.1156 1.0000
5.250 0.7648 0.01198 0.00503 -0.0450 0.0984 1.0000
5.500 0.7821 0.01232 0.00531 -0.0431 0.0851 1.0000
5.750 0.7991 0.01270 0.00562 -0.0410 0.0743 1.0000
6.000 0.8171 0.01301 0.00591 -0.0391 0.0665 1.0000
6.250 0.8348 0.01336 0.00626 -0.0372 0.0600 1.0000
6.500 0.8519 0.01378 0.00663 -0.0352 0.0542 1.0000
6.750 0.8699 0.01416 0.00703 -0.0333 0.0501 1.0000
7.000 0.8881 0.01454 0.00741 -0.0315 0.0461 1.0000
7.250 0.9046 0.01509 0.00796 -0.0294 0.0425 1.0000
7.500 0.9244 0.01544 0.00834 -0.0280 0.0396 1.0000
7.750 0.9420 0.01600 0.00888 -0.0262 0.0367 1.0000
8.000 0.9592 0.01664 0.00957 -0.0243 0.0347 1.0000
8.250 0.9789 0.01711 0.01009 -0.0229 0.0329 1.0000
8.500 0.9980 0.01762 0.01063 -0.0215 0.0313 1.0000
8.750 1.0139 0.01846 0.01146 -0.0196 0.0297 1.0000
9.000 1.0306 0.01931 0.01238 -0.0179 0.0285 1.0000
9.250 1.0496 0.01985 0.01300 -0.0165 0.0275 1.0000
9.500 1.0673 0.02046 0.01367 -0.0149 0.0265 1.0000
9.750 1.0842 0.02113 0.01438 -0.0132 0.0256 1.0000
10.000 1.1004 0.02189 0.01516 -0.0115 0.0248 1.0000
10.250 1.1147 0.02310 0.01643 -0.0097 0.0240 1.0000
10.500 1.1300 0.02456 0.01800 -0.0081 0.0234 1.0000
10.750 1.1462 0.02542 0.01898 -0.0064 0.0230 1.0000
11.000 1.1615 0.02643 0.02011 -0.0048 0.0226 1.0000
11.250 1.1760 0.02747 0.02127 -0.0031 0.0220 1.0000
11.500 1.1894 0.02849 0.02240 -0.0013 0.0215 1.0000
11.750 1.2016 0.02951 0.02352 0.0006 0.0210 1.0000
12.000 1.2130 0.03056 0.02466 0.0025 0.0205 1.0000
12.250 1.2232 0.03177 0.02595 0.0043 0.0202 1.0000
12.500 1.2322 0.03316 0.02743 0.0062 0.0198 1.0000
12.750 1.2385 0.03506 0.02944 0.0082 0.0195 1.0000
13.000 1.2374 0.03820 0.03280 0.0107 0.0191 1.0000
13.250 1.2349 0.04059 0.03542 0.0132 0.0190 1.0000
13.500 1.2326 0.04269 0.03774 0.0155 0.0189 1.0000
13.750 1.2277 0.04518 0.04044 0.0175 0.0187 1.0000
14.000 1.2200 0.04806 0.04353 0.0192 0.0186 1.0000
14.250 1.2092 0.05142 0.04712 0.0205 0.0185 1.0000
14.500 1.1951 0.05538 0.05130 0.0211 0.0184 1.0000
14.750 1.1782 0.05995 0.05610 0.0210 0.0184 1.0000
15.000 1.1584 0.06535 0.06171 0.0198 0.0183 1.0000
15.250 1.1353 0.07176 0.06834 0.0174 0.0183 1.0000
15.500 1.1090 0.07953 0.07632 0.0135 0.0184 1.0000
15.750 1.0784 0.08913 0.08613 0.0077 0.0185 1.0000
16.000 1.0409 0.10142 0.09862 -0.0003 0.0187 1.0000
16.250 0.9840 0.11941 0.11680 -0.0115 0.0190 1.0000
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Polar data table (+)
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