LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 200,000 Max Cl/Cd: 67.04 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141d-il-200000.txt Download as CSV file: xf-c141d-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3732 0.10943 0.10571 -0.0363 1.0000 0.0609
-10.750 -0.3964 0.10423 0.10055 -0.0401 1.0000 0.0630
-10.500 -0.4217 0.09848 0.09486 -0.0442 1.0000 0.0634
-10.250 -0.4228 0.09385 0.09026 -0.0434 1.0000 0.0640
-10.000 -0.4093 0.09202 0.08843 -0.0402 1.0000 0.0648
-9.750 -0.4067 0.08938 0.08582 -0.0389 1.0000 0.0657
-9.500 -0.4092 0.08625 0.08271 -0.0382 1.0000 0.0668
-9.250 -0.4164 0.08263 0.07913 -0.0380 1.0000 0.0680
-9.000 -0.4283 0.07856 0.07510 -0.0382 1.0000 0.0691
-8.750 -0.6286 0.07511 0.07132 -0.0432 1.0000 0.0641
-8.500 -0.6104 0.07347 0.06980 -0.0409 1.0000 0.0650
-8.250 -0.6149 0.07127 0.06761 -0.0383 1.0000 0.0657
-8.000 -0.6232 0.06870 0.06502 -0.0359 1.0000 0.0665
-7.750 -0.6316 0.06589 0.06216 -0.0335 1.0000 0.0674
-7.500 -0.6392 0.06285 0.05903 -0.0312 1.0000 0.0688
-7.250 -0.7130 0.03957 0.03365 -0.0236 1.0000 0.0407
-7.000 -0.7033 0.03622 0.03010 -0.0216 1.0000 0.0403
-6.750 -0.6923 0.03296 0.02646 -0.0195 1.0000 0.0401
-6.500 -0.6783 0.03000 0.02299 -0.0176 1.0000 0.0403
-6.250 -0.6610 0.02751 0.02009 -0.0161 1.0000 0.0412
-6.000 -0.6410 0.02680 0.01947 -0.0153 1.0000 0.0429
-5.750 -0.6204 0.02564 0.01812 -0.0143 1.0000 0.0448
-5.500 -0.5984 0.02402 0.01610 -0.0131 1.0000 0.0466
-5.250 -0.5759 0.02253 0.01443 -0.0123 1.0000 0.0486
-5.000 -0.5540 0.02185 0.01373 -0.0115 1.0000 0.0512
-4.750 -0.5232 0.02098 0.01268 -0.0122 0.9984 0.0559
-4.500 -0.4878 0.02055 0.01225 -0.0141 0.9957 0.0615
-4.250 -0.4531 0.01985 0.01154 -0.0158 0.9932 0.0675
-4.000 -0.4196 0.01941 0.01100 -0.0171 0.9898 0.0747
-3.750 -0.3846 0.01901 0.01065 -0.0190 0.9867 0.0826
-3.500 -0.3483 0.01840 0.01009 -0.0210 0.9844 0.0907
-3.250 -0.3170 0.01811 0.00973 -0.0219 0.9800 0.0985
-3.000 -0.2837 0.01746 0.00922 -0.0234 0.9765 0.1089
-2.750 -0.2472 0.01704 0.00888 -0.0255 0.9736 0.1222
-2.500 -0.2141 0.01668 0.00859 -0.0268 0.9698 0.1412
-2.250 -0.1834 0.01615 0.00829 -0.0278 0.9650 0.1767
-2.000 -0.1544 0.01419 0.00811 -0.0293 0.9628 0.5466
-1.750 -0.1257 0.01363 0.00843 -0.0286 0.9601 0.7729
-1.500 -0.1029 0.01366 0.00869 -0.0266 0.9546 0.8562
-1.250 -0.0721 0.01387 0.00895 -0.0262 0.9499 0.9158
-1.000 -0.0260 0.01418 0.00921 -0.0293 0.9479 0.9572
-0.750 0.0330 0.01446 0.00941 -0.0355 0.9474 0.9773
-0.500 0.1116 0.01480 0.00967 -0.0460 0.9499 0.9952
-0.250 0.1651 0.01481 0.00963 -0.0516 0.9480 1.0000
0.000 0.2082 0.01475 0.00953 -0.0551 0.9451 1.0000
0.250 0.2288 0.01468 0.00943 -0.0542 0.9352 1.0000
0.500 0.2717 0.01458 0.00932 -0.0575 0.9318 1.0000
0.750 0.2966 0.01454 0.00926 -0.0572 0.9231 1.0000
1.000 0.3545 0.01410 0.00883 -0.0629 0.9182 1.0000
1.250 0.4162 0.01314 0.00789 -0.0684 0.9078 1.0000
1.500 0.4682 0.01212 0.00689 -0.0719 0.8972 1.0000
1.750 0.4983 0.01157 0.00634 -0.0715 0.8838 1.0000
2.000 0.5223 0.01124 0.00604 -0.0702 0.8700 1.0000
2.250 0.5472 0.01095 0.00576 -0.0691 0.8558 1.0000
2.500 0.5725 0.01068 0.00549 -0.0680 0.8397 1.0000
2.750 0.5980 0.01044 0.00526 -0.0670 0.8209 1.0000
3.000 0.6211 0.01029 0.00509 -0.0655 0.7970 1.0000
3.250 0.6446 0.01016 0.00492 -0.0640 0.7673 1.0000
3.500 0.6672 0.01012 0.00477 -0.0624 0.7257 1.0000
3.750 0.6878 0.01026 0.00466 -0.0603 0.6627 1.0000
4.000 0.7013 0.01076 0.00467 -0.0569 0.5622 1.0000
4.250 0.7032 0.01182 0.00495 -0.0516 0.4161 1.0000
4.500 0.7037 0.01312 0.00547 -0.0467 0.2814 1.0000
4.750 0.7116 0.01417 0.00601 -0.0431 0.2045 1.0000
5.000 0.7249 0.01492 0.00653 -0.0404 0.1700 1.0000
5.250 0.7405 0.01555 0.00701 -0.0381 0.1510 1.0000
5.500 0.7575 0.01612 0.00751 -0.0361 0.1378 1.0000
5.750 0.7747 0.01676 0.00808 -0.0342 0.1276 1.0000
6.000 0.7928 0.01739 0.00863 -0.0324 0.1186 1.0000
6.250 0.8124 0.01799 0.00924 -0.0309 0.1109 1.0000
6.500 0.8310 0.01886 0.00999 -0.0294 0.1035 1.0000
6.750 0.8522 0.01937 0.01060 -0.0282 0.0970 1.0000
7.000 0.8726 0.02041 0.01150 -0.0271 0.0903 1.0000
7.250 0.8940 0.02091 0.01212 -0.0259 0.0847 1.0000
7.500 0.9152 0.02181 0.01293 -0.0250 0.0791 1.0000
7.750 0.9370 0.02256 0.01381 -0.0239 0.0740 1.0000
8.000 0.9579 0.02327 0.01447 -0.0230 0.0694 1.0000
8.250 0.9806 0.02441 0.01569 -0.0222 0.0652 1.0000
8.500 1.0012 0.02511 0.01646 -0.0211 0.0612 1.0000
8.750 1.0240 0.02642 0.01771 -0.0206 0.0578 1.0000
9.000 1.0442 0.02734 0.01885 -0.0193 0.0548 1.0000
9.250 1.0648 0.02831 0.01988 -0.0183 0.0523 1.0000
9.500 1.0881 0.03004 0.02158 -0.0181 0.0500 1.0000
9.750 1.1047 0.03126 0.02312 -0.0162 0.0479 1.0000
10.000 1.1225 0.03240 0.02440 -0.0149 0.0459 1.0000
10.250 1.1407 0.03357 0.02562 -0.0137 0.0444 1.0000
10.500 1.1598 0.03600 0.02813 -0.0131 0.0432 1.0000
10.750 1.1676 0.03814 0.03072 -0.0102 0.0424 1.0000
11.000 1.1727 0.04077 0.03375 -0.0073 0.0417 1.0000
11.250 1.1740 0.04357 0.03694 -0.0041 0.0410 1.0000
11.500 1.1709 0.04632 0.04003 -0.0005 0.0405 1.0000
11.750 1.1632 0.04896 0.04294 0.0035 0.0400 1.0000
12.000 1.1532 0.05165 0.04589 0.0073 0.0396 1.0000
12.250 1.1417 0.05445 0.04891 0.0106 0.0393 1.0000
12.500 1.1220 0.05810 0.05284 0.0138 0.0392 1.0000
12.750 1.0835 0.06394 0.05906 0.0165 0.0396 1.0000
13.000 1.0380 0.07139 0.06686 0.0167 0.0403 1.0000
13.250 0.9948 0.07989 0.07562 0.0140 0.0411 1.0000
13.500 0.9553 0.08965 0.08557 0.0085 0.0419 1.0000
13.750 0.9222 0.10034 0.09637 0.0016 0.0426 1.0000
14.000 0.9016 0.10951 0.10557 -0.0036 0.0432 1.0000
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Polar data table (+)
Polar graphs
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