LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Reynolds number: 200,000 Max Cl/Cd: 48.81 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141b-il-200000-n5.txt Download as CSV file: xf-c141b-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL113.6 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8154 0.07851 0.07391 -0.0622 1.0000 0.0236
-14.500 -0.8558 0.06745 0.06259 -0.0697 1.0000 0.0233
-14.250 -0.8843 0.06005 0.05495 -0.0740 1.0000 0.0233
-14.000 -0.9067 0.05455 0.04920 -0.0761 1.0000 0.0234
-13.750 -0.9252 0.05021 0.04462 -0.0766 1.0000 0.0236
-13.500 -0.9413 0.04667 0.04084 -0.0759 1.0000 0.0239
-13.250 -0.9557 0.04376 0.03769 -0.0740 1.0000 0.0241
-13.000 -0.9686 0.04139 0.03507 -0.0712 1.0000 0.0244
-12.750 -0.9750 0.03980 0.03341 -0.0681 1.0000 0.0246
-12.500 -0.9812 0.03855 0.03211 -0.0644 1.0000 0.0248
-12.250 -0.9891 0.03751 0.03100 -0.0600 1.0000 0.0251
-12.000 -0.9993 0.03663 0.03005 -0.0547 1.0000 0.0253
-11.750 -1.0095 0.03582 0.02916 -0.0491 1.0000 0.0255
-11.500 -1.0131 0.03486 0.02810 -0.0446 1.0000 0.0259
-11.250 -1.0140 0.03385 0.02698 -0.0405 1.0000 0.0263
-11.000 -1.0121 0.03279 0.02576 -0.0368 0.9999 0.0268
-10.750 -0.9925 0.03130 0.02405 -0.0367 0.9976 0.0277
-10.500 -0.9722 0.02990 0.02237 -0.0365 0.9955 0.0287
-10.250 -0.9504 0.02886 0.02129 -0.0365 0.9936 0.0296
-10.000 -0.9296 0.02806 0.02042 -0.0362 0.9911 0.0306
-9.750 -0.9070 0.02718 0.01942 -0.0360 0.9886 0.0319
-9.500 -0.8828 0.02621 0.01826 -0.0361 0.9864 0.0333
-9.250 -0.8581 0.02525 0.01722 -0.0364 0.9846 0.0345
-9.000 -0.8338 0.02454 0.01646 -0.0365 0.9828 0.0359
-8.750 -0.8133 0.02390 0.01574 -0.0356 0.9799 0.0375
-8.500 -0.7894 0.02324 0.01493 -0.0353 0.9773 0.0395
-8.250 -0.7647 0.02253 0.01423 -0.0354 0.9750 0.0413
-8.000 -0.7377 0.02196 0.01360 -0.0358 0.9731 0.0435
-7.750 -0.7099 0.02141 0.01293 -0.0363 0.9717 0.0461
-7.500 -0.6891 0.02083 0.01236 -0.0354 0.9688 0.0484
-7.250 -0.6666 0.02037 0.01186 -0.0347 0.9655 0.0510
-7.000 -0.6407 0.01993 0.01133 -0.0347 0.9629 0.0541
-6.750 -0.6141 0.01937 0.01080 -0.0349 0.9608 0.0574
-6.500 -0.5844 0.01894 0.01032 -0.0357 0.9590 0.0614
-6.250 -0.5539 0.01845 0.00982 -0.0367 0.9575 0.0658
-6.000 -0.5362 0.01811 0.00947 -0.0348 0.9526 0.0698
-5.750 -0.5110 0.01773 0.00906 -0.0346 0.9494 0.0749
-5.500 -0.4832 0.01734 0.00869 -0.0349 0.9470 0.0815
-5.250 -0.4534 0.01696 0.00832 -0.0356 0.9450 0.0892
-5.000 -0.4223 0.01661 0.00797 -0.0366 0.9435 0.0993
-4.750 -0.3992 0.01631 0.00771 -0.0359 0.9400 0.1105
-4.500 -0.3783 0.01602 0.00747 -0.0347 0.9355 0.1240
-4.250 -0.3508 0.01568 0.00720 -0.0349 0.9326 0.1430
-4.000 -0.3213 0.01529 0.00694 -0.0355 0.9304 0.1700
-3.750 -0.2905 0.01486 0.00668 -0.0365 0.9287 0.2076
-3.500 -0.2595 0.01433 0.00640 -0.0376 0.9273 0.2648
-3.250 -0.2486 0.01396 0.00629 -0.0344 0.9201 0.3234
-3.000 -0.2252 0.01331 0.00609 -0.0338 0.9167 0.4258
-2.750 -0.1988 0.01275 0.00598 -0.0337 0.9143 0.5287
-2.500 -0.1691 0.01241 0.00593 -0.0339 0.9125 0.6029
-2.250 -0.1478 0.01230 0.00597 -0.0324 0.9076 0.6484
-2.000 -0.1239 0.01221 0.00598 -0.0314 0.9028 0.6843
-1.750 -0.0941 0.01210 0.00593 -0.0315 0.8999 0.7147
-1.500 -0.0625 0.01198 0.00586 -0.0321 0.8977 0.7407
-1.250 -0.0296 0.01185 0.00580 -0.0328 0.8959 0.7640
-1.000 -0.0111 0.01189 0.00591 -0.0306 0.8886 0.7858
-0.750 0.0177 0.01184 0.00596 -0.0303 0.8849 0.8138
-0.500 0.0491 0.01179 0.00597 -0.0305 0.8822 0.8389
-0.250 0.0840 0.01171 0.00593 -0.0316 0.8801 0.8524
0.000 0.1062 0.01178 0.00602 -0.0303 0.8728 0.8641
0.250 0.1365 0.01172 0.00597 -0.0306 0.8685 0.8754
0.500 0.1733 0.01165 0.00592 -0.0322 0.8656 0.8831
0.750 0.2028 0.01162 0.00592 -0.0323 0.8603 0.8934
1.000 0.2336 0.01164 0.00596 -0.0327 0.8537 0.9018
1.250 0.2695 0.01149 0.00583 -0.0341 0.8488 0.9100
1.500 0.3019 0.01130 0.00566 -0.0345 0.8348 0.9170
1.750 0.3339 0.01100 0.00532 -0.0347 0.8160 0.9255
2.000 0.3681 0.01089 0.00522 -0.0356 0.7966 0.9312
2.250 0.3978 0.01081 0.00513 -0.0356 0.7765 0.9399
2.750 0.4731 0.01068 0.00484 -0.0390 0.7159 0.9484
3.000 0.5034 0.01078 0.00475 -0.0391 0.6736 0.9556
3.250 0.5363 0.01105 0.00479 -0.0400 0.6160 0.9596
3.500 0.5633 0.01154 0.00491 -0.0398 0.5396 0.9659
3.750 0.5850 0.01228 0.00516 -0.0389 0.4416 0.9732
4.000 0.6072 0.01318 0.00555 -0.0384 0.3399 0.9805
4.250 0.6333 0.01397 0.00594 -0.0387 0.2626 0.9862
4.500 0.6620 0.01464 0.00633 -0.0396 0.2092 0.9916
4.750 0.6927 0.01519 0.00670 -0.0408 0.1717 0.9961
5.000 0.7226 0.01571 0.00707 -0.0418 0.1446 1.0000
5.250 0.7354 0.01605 0.00734 -0.0391 0.1291 1.0000
5.500 0.7483 0.01640 0.00763 -0.0364 0.1161 1.0000
5.750 0.7615 0.01675 0.00793 -0.0337 0.1052 1.0000
6.000 0.7752 0.01709 0.00825 -0.0311 0.0963 1.0000
6.250 0.7885 0.01748 0.00860 -0.0284 0.0887 1.0000
6.500 0.8025 0.01785 0.00897 -0.0259 0.0820 1.0000
6.750 0.8161 0.01827 0.00937 -0.0233 0.0765 1.0000
7.000 0.8304 0.01866 0.00977 -0.0208 0.0713 1.0000
7.250 0.8435 0.01915 0.01022 -0.0182 0.0671 1.0000
7.500 0.8578 0.01956 0.01068 -0.0158 0.0631 1.0000
7.750 0.8710 0.02004 0.01115 -0.0132 0.0595 1.0000
8.000 0.8849 0.02056 0.01169 -0.0108 0.0564 1.0000
8.250 0.9003 0.02106 0.01223 -0.0087 0.0532 1.0000
8.500 0.9149 0.02165 0.01282 -0.0067 0.0505 1.0000
8.750 0.9303 0.02227 0.01349 -0.0047 0.0481 1.0000
9.000 0.9464 0.02288 0.01415 -0.0029 0.0457 1.0000
9.250 0.9619 0.02353 0.01481 -0.0012 0.0436 1.0000
9.500 0.9767 0.02430 0.01562 0.0006 0.0417 1.0000
9.750 0.9928 0.02502 0.01643 0.0023 0.0398 1.0000
10.000 1.0080 0.02579 0.01725 0.0039 0.0383 1.0000
10.250 1.0224 0.02660 0.01809 0.0056 0.0369 1.0000
10.500 1.0362 0.02755 0.01910 0.0073 0.0357 1.0000
10.750 1.0512 0.02845 0.02012 0.0088 0.0342 1.0000
11.000 1.0653 0.02936 0.02112 0.0104 0.0329 1.0000
11.250 1.0783 0.03030 0.02211 0.0120 0.0319 1.0000
11.500 1.0899 0.03137 0.02323 0.0137 0.0311 1.0000
11.750 1.1016 0.03261 0.02457 0.0153 0.0303 1.0000
12.000 1.1132 0.03388 0.02601 0.0170 0.0295 1.0000
12.250 1.1236 0.03521 0.02747 0.0186 0.0287 1.0000
12.500 1.1329 0.03655 0.02894 0.0202 0.0279 1.0000
12.750 1.1413 0.03792 0.03042 0.0218 0.0273 1.0000
13.000 1.1486 0.03934 0.03191 0.0233 0.0267 1.0000
13.250 1.1549 0.04090 0.03353 0.0247 0.0262 1.0000
13.500 1.1591 0.04279 0.03556 0.0262 0.0257 1.0000
13.750 1.1612 0.04493 0.03793 0.0277 0.0252 1.0000
14.000 1.1616 0.04725 0.04047 0.0290 0.0247 1.0000
14.250 1.1603 0.04978 0.04320 0.0301 0.0243 1.0000
14.500 1.1572 0.05256 0.04618 0.0310 0.0240 1.0000
14.750 1.1525 0.05560 0.04941 0.0315 0.0237 1.0000
15.000 1.1460 0.05896 0.05295 0.0316 0.0234 1.0000
15.250 1.1379 0.06271 0.05687 0.0313 0.0232 1.0000
15.500 1.1279 0.06690 0.06125 0.0304 0.0230 1.0000
15.750 1.1158 0.07168 0.06621 0.0289 0.0229 1.0000
16.000 1.1008 0.07726 0.07198 0.0267 0.0228 1.0000
16.250 1.0816 0.08400 0.07893 0.0233 0.0227 1.0000
16.500 1.0548 0.09275 0.08794 0.0184 0.0227 1.0000
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Polar data table (+)
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