LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 500,000 Max Cl/Cd: 62.69 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141c-il-500000-n5.txt Download as CSV file: xf-c141c-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9677 0.05967 0.05644 -0.0605 1.0000 0.0121
-14.500 -0.9958 0.05071 0.04722 -0.0674 1.0000 0.0121
-14.250 -1.0127 0.04520 0.04151 -0.0706 1.0000 0.0121
-14.000 -1.0240 0.04126 0.03739 -0.0717 1.0000 0.0122
-13.750 -1.0320 0.03823 0.03417 -0.0715 1.0000 0.0123
-13.500 -1.0379 0.03581 0.03158 -0.0702 1.0000 0.0124
-13.250 -1.0423 0.03387 0.02948 -0.0681 1.0000 0.0125
-13.000 -1.0476 0.03231 0.02778 -0.0647 1.0000 0.0126
-12.750 -1.0568 0.03116 0.02651 -0.0598 1.0000 0.0127
-12.500 -1.0637 0.03010 0.02534 -0.0548 1.0000 0.0128
-12.250 -1.0661 0.02904 0.02414 -0.0505 1.0000 0.0130
-12.000 -1.0590 0.02784 0.02279 -0.0479 0.9993 0.0132
-11.750 -1.0388 0.02646 0.02122 -0.0480 0.9972 0.0134
-11.500 -1.0170 0.02523 0.01980 -0.0482 0.9954 0.0136
-11.250 -0.9937 0.02412 0.01851 -0.0485 0.9938 0.0138
-11.000 -0.9735 0.02288 0.01717 -0.0483 0.9912 0.0142
-10.750 -0.9497 0.02195 0.01615 -0.0485 0.9890 0.0145
-10.500 -0.9239 0.02119 0.01531 -0.0489 0.9871 0.0149
-10.250 -0.8970 0.02050 0.01453 -0.0495 0.9857 0.0153
-10.000 -0.8692 0.01980 0.01374 -0.0502 0.9845 0.0158
-9.750 -0.8407 0.01908 0.01292 -0.0511 0.9835 0.0164
-9.500 -0.8178 0.01843 0.01217 -0.0506 0.9802 0.0168
-9.250 -0.7917 0.01780 0.01143 -0.0507 0.9779 0.0172
-9.000 -0.7651 0.01705 0.01062 -0.0511 0.9759 0.0179
-8.750 -0.7369 0.01648 0.01001 -0.0517 0.9742 0.0185
-8.500 -0.7079 0.01597 0.00945 -0.0524 0.9727 0.0193
-8.250 -0.6785 0.01548 0.00889 -0.0531 0.9714 0.0201
-8.000 -0.6530 0.01505 0.00840 -0.0529 0.9685 0.0210
-7.750 -0.6287 0.01459 0.00790 -0.0525 0.9650 0.0220
-7.500 -0.6017 0.01418 0.00747 -0.0526 0.9624 0.0233
-7.250 -0.5734 0.01381 0.00706 -0.0530 0.9602 0.0247
-7.000 -0.5447 0.01344 0.00664 -0.0534 0.9582 0.0260
-6.750 -0.5169 0.01302 0.00621 -0.0536 0.9562 0.0277
-6.500 -0.4939 0.01273 0.00591 -0.0528 0.9518 0.0294
-6.250 -0.4676 0.01246 0.00559 -0.0526 0.9484 0.0313
-6.000 -0.4406 0.01213 0.00526 -0.0526 0.9456 0.0337
-5.750 -0.4128 0.01184 0.00497 -0.0527 0.9433 0.0365
-5.500 -0.3856 0.01160 0.00469 -0.0527 0.9407 0.0390
-5.250 -0.3614 0.01133 0.00444 -0.0520 0.9363 0.0425
-5.000 -0.3351 0.01110 0.00420 -0.0518 0.9327 0.0464
-4.750 -0.3081 0.01084 0.00395 -0.0517 0.9297 0.0512
-4.500 -0.2802 0.01060 0.00372 -0.0518 0.9272 0.0567
-4.250 -0.2551 0.01039 0.00353 -0.0513 0.9229 0.0632
-4.000 -0.2289 0.01018 0.00334 -0.0510 0.9187 0.0711
-3.750 -0.2019 0.00996 0.00315 -0.0508 0.9153 0.0815
-3.500 -0.1741 0.00973 0.00296 -0.0509 0.9124 0.0945
-3.250 -0.1487 0.00952 0.00282 -0.0504 0.9077 0.1112
-3.000 -0.1226 0.00928 0.00267 -0.0502 0.9033 0.1347
-2.750 -0.0958 0.00901 0.00251 -0.0500 0.8995 0.1671
-2.500 -0.0695 0.00870 0.00235 -0.0498 0.8958 0.2105
-2.250 -0.0450 0.00836 0.00224 -0.0493 0.8906 0.2715
-2.000 -0.0204 0.00793 0.00210 -0.0489 0.8859 0.3537
-1.750 0.0041 0.00744 0.00196 -0.0484 0.8820 0.4568
-1.500 0.0263 0.00702 0.00190 -0.0473 0.8762 0.5556
-1.250 0.0510 0.00675 0.00187 -0.0466 0.8708 0.6230
-1.000 0.0771 0.00656 0.00183 -0.0462 0.8664 0.6732
-0.750 0.1021 0.00644 0.00184 -0.0455 0.8601 0.7128
-0.500 0.1285 0.00633 0.00183 -0.0450 0.8543 0.7451
-0.250 0.1550 0.00624 0.00183 -0.0445 0.8487 0.7761
0.000 0.1802 0.00615 0.00187 -0.0437 0.8416 0.8156
0.250 0.2061 0.00607 0.00192 -0.0429 0.8338 0.8522
0.500 0.2325 0.00605 0.00193 -0.0423 0.8220 0.8728
0.750 0.2593 0.00606 0.00191 -0.0418 0.8048 0.8852
1.000 0.2853 0.00609 0.00187 -0.0411 0.7784 0.8969
1.250 0.3111 0.00618 0.00187 -0.0404 0.7502 0.9082
1.500 0.3377 0.00630 0.00190 -0.0399 0.7233 0.9179
1.750 0.3634 0.00646 0.00195 -0.0393 0.6940 0.9282
2.000 0.3889 0.00666 0.00203 -0.0387 0.6591 0.9382
2.250 0.4150 0.00693 0.00213 -0.0382 0.6168 0.9460
2.500 0.4383 0.00727 0.00225 -0.0372 0.5640 0.9547
2.750 0.4631 0.00777 0.00244 -0.0368 0.4889 0.9605
3.000 0.4855 0.00839 0.00267 -0.0359 0.4003 0.9679
3.250 0.5110 0.00902 0.00293 -0.0358 0.3190 0.9730
3.500 0.5391 0.00957 0.00319 -0.0363 0.2521 0.9773
3.750 0.5660 0.01006 0.00344 -0.0365 0.2004 0.9823
4.000 0.5969 0.01049 0.00369 -0.0376 0.1611 0.9850
4.250 0.6286 0.01086 0.00392 -0.0387 0.1332 0.9876
4.500 0.6594 0.01121 0.00417 -0.0397 0.1118 0.9908
4.750 0.6894 0.01154 0.00442 -0.0405 0.0952 0.9940
5.000 0.7215 0.01186 0.00467 -0.0417 0.0813 0.9961
5.250 0.7531 0.01219 0.00495 -0.0428 0.0696 0.9986
5.500 0.7793 0.01251 0.00522 -0.0428 0.0610 1.0000
5.750 0.7976 0.01278 0.00546 -0.0410 0.0544 1.0000
6.000 0.8164 0.01304 0.00572 -0.0393 0.0495 1.0000
6.250 0.8348 0.01334 0.00599 -0.0375 0.0447 1.0000
6.500 0.8538 0.01362 0.00627 -0.0358 0.0414 1.0000
6.750 0.8727 0.01392 0.00657 -0.0342 0.0382 1.0000
7.000 0.8913 0.01427 0.00691 -0.0325 0.0353 1.0000
7.250 0.9109 0.01457 0.00724 -0.0310 0.0330 1.0000
7.500 0.9303 0.01493 0.00759 -0.0295 0.0304 1.0000
7.750 0.9499 0.01532 0.00799 -0.0280 0.0284 1.0000
8.000 0.9701 0.01568 0.00840 -0.0267 0.0267 1.0000
8.250 0.9901 0.01609 0.00882 -0.0254 0.0252 1.0000
8.500 1.0092 0.01660 0.00933 -0.0240 0.0237 1.0000
8.750 1.0292 0.01703 0.00981 -0.0227 0.0228 1.0000
9.000 1.0489 0.01749 0.01033 -0.0215 0.0218 1.0000
9.250 1.0683 0.01797 0.01085 -0.0202 0.0208 1.0000
9.500 1.0867 0.01849 0.01139 -0.0187 0.0199 1.0000
9.750 1.1029 0.01914 0.01207 -0.0169 0.0190 1.0000
10.000 1.1205 0.01966 0.01265 -0.0153 0.0185 1.0000
10.250 1.1374 0.02024 0.01331 -0.0137 0.0179 1.0000
10.500 1.1539 0.02085 0.01399 -0.0121 0.0174 1.0000
10.750 1.1700 0.02150 0.01470 -0.0104 0.0169 1.0000
11.000 1.1858 0.02218 0.01544 -0.0088 0.0164 1.0000
11.250 1.2006 0.02293 0.01624 -0.0071 0.0160 1.0000
11.500 1.2140 0.02379 0.01717 -0.0053 0.0156 1.0000
11.750 1.2245 0.02487 0.01831 -0.0032 0.0153 1.0000
12.000 1.2378 0.02574 0.01929 -0.0014 0.0151 1.0000
12.250 1.2502 0.02669 0.02034 0.0003 0.0148 1.0000
12.500 1.2620 0.02768 0.02144 0.0020 0.0145 1.0000
12.750 1.2730 0.02873 0.02260 0.0037 0.0142 1.0000
13.000 1.2834 0.02985 0.02382 0.0054 0.0139 1.0000
13.250 1.2929 0.03104 0.02511 0.0070 0.0136 1.0000
13.500 1.3012 0.03233 0.02651 0.0086 0.0134 1.0000
13.750 1.3085 0.03374 0.02802 0.0102 0.0131 1.0000
14.000 1.3147 0.03527 0.02966 0.0117 0.0130 1.0000
14.250 1.3195 0.03696 0.03145 0.0131 0.0128 1.0000
14.500 1.3227 0.03885 0.03344 0.0144 0.0126 1.0000
14.750 1.3238 0.04098 0.03570 0.0156 0.0125 1.0000
15.000 1.3226 0.04347 0.03830 0.0166 0.0123 1.0000
15.250 1.3182 0.04639 0.04135 0.0173 0.0122 1.0000
15.500 1.3120 0.04969 0.04478 0.0177 0.0121 1.0000
15.750 1.3080 0.05295 0.04820 0.0176 0.0120 1.0000
16.000 1.3017 0.05667 0.05209 0.0171 0.0119 1.0000
16.250 1.2934 0.06093 0.05652 0.0161 0.0119 1.0000
16.500 1.2833 0.06576 0.06153 0.0144 0.0118 1.0000
16.750 1.2702 0.07135 0.06729 0.0121 0.0117 1.0000
17.000 1.2545 0.07775 0.07386 0.0090 0.0117 1.0000
17.250 1.2358 0.08510 0.08140 0.0051 0.0117 1.0000
17.500 1.2134 0.09350 0.08998 0.0004 0.0117 1.0000
17.750 1.1873 0.10298 0.09964 -0.0049 0.0117 1.0000
18.000 1.1578 0.11345 0.11028 -0.0107 0.0117 1.0000
18.250 1.1245 0.12494 0.12193 -0.0171 0.0118 1.0000
18.500 1.0867 0.13792 0.13508 -0.0244 0.0118 1.0000
18.750 1.0005 0.16453 0.16197 -0.0394 0.0120 1.0000
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Polar data table (+)
Polar graphs
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