LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 200,000 Max Cl/Cd: 57.55 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141d-il-200000-n5.txt Download as CSV file: xf-c141d-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7924 0.04784 0.04323 -0.0528 1.0000 0.0191
-10.000 -0.8164 0.04415 0.03925 -0.0478 1.0000 0.0192
-9.750 -0.8290 0.04108 0.03589 -0.0436 1.0000 0.0193
-9.500 -0.8352 0.03825 0.03275 -0.0398 1.0000 0.0195
-9.250 -0.8360 0.03571 0.02990 -0.0365 1.0000 0.0197
-9.000 -0.8207 0.03287 0.02665 -0.0361 0.9978 0.0201
-8.750 -0.8003 0.03028 0.02366 -0.0364 0.9954 0.0206
-8.500 -0.7779 0.02802 0.02098 -0.0365 0.9931 0.0212
-8.250 -0.7548 0.02607 0.01862 -0.0365 0.9905 0.0219
-8.000 -0.7286 0.02495 0.01741 -0.0369 0.9881 0.0224
-7.750 -0.7002 0.02412 0.01649 -0.0377 0.9860 0.0232
-7.500 -0.6709 0.02322 0.01542 -0.0386 0.9843 0.0245
-7.250 -0.6457 0.02217 0.01416 -0.0384 0.9814 0.0259
-7.000 -0.6188 0.02152 0.01349 -0.0387 0.9784 0.0270
-6.750 -0.5901 0.02076 0.01263 -0.0393 0.9760 0.0285
-6.500 -0.5604 0.01992 0.01164 -0.0400 0.9740 0.0303
-6.250 -0.5292 0.01934 0.01105 -0.0411 0.9724 0.0322
-6.000 -0.5044 0.01879 0.01039 -0.0407 0.9685 0.0351
-5.750 -0.4769 0.01834 0.00995 -0.0409 0.9652 0.0380
-5.500 -0.4471 0.01781 0.00936 -0.0416 0.9627 0.0415
-5.250 -0.4155 0.01739 0.00892 -0.0426 0.9607 0.0454
-5.000 -0.3830 0.01698 0.00851 -0.0439 0.9591 0.0499
-4.750 -0.3596 0.01670 0.00818 -0.0431 0.9541 0.0546
-4.500 -0.3312 0.01637 0.00789 -0.0434 0.9506 0.0596
-4.250 -0.3001 0.01602 0.00752 -0.0443 0.9481 0.0651
-4.000 -0.2672 0.01569 0.00720 -0.0455 0.9462 0.0711
-3.750 -0.2337 0.01530 0.00682 -0.0469 0.9446 0.0778
-3.500 -0.2133 0.01507 0.00657 -0.0454 0.9381 0.0840
-3.250 -0.1833 0.01470 0.00625 -0.0460 0.9349 0.0927
-3.000 -0.1507 0.01437 0.00594 -0.0471 0.9326 0.1039
-2.750 -0.1173 0.01402 0.00567 -0.0484 0.9308 0.1209
-2.500 -0.0935 0.01374 0.00549 -0.0477 0.9253 0.1462
-2.250 -0.0666 0.01329 0.00529 -0.0478 0.9209 0.1998
-2.000 -0.0388 0.01249 0.00504 -0.0482 0.9178 0.3330
-1.750 -0.0134 0.01148 0.00489 -0.0480 0.9152 0.5440
-1.500 0.0057 0.01108 0.00496 -0.0460 0.9088 0.6638
-1.250 0.0315 0.01085 0.00497 -0.0451 0.9043 0.7378
-1.000 0.0615 0.01068 0.00495 -0.0450 0.9012 0.7856
-0.750 0.0935 0.01058 0.00500 -0.0451 0.8989 0.8385
-0.500 0.1199 0.01069 0.00521 -0.0441 0.8928 0.8874
-0.250 0.1553 0.01077 0.00532 -0.0450 0.8890 0.9197
0.000 0.1937 0.01079 0.00533 -0.0468 0.8860 0.9389
0.250 0.2352 0.01076 0.00528 -0.0494 0.8834 0.9494
0.500 0.2692 0.01081 0.00533 -0.0505 0.8769 0.9603
0.750 0.3081 0.01076 0.00528 -0.0528 0.8719 0.9668
1.000 0.3460 0.01061 0.00511 -0.0546 0.8638 0.9726
1.250 0.3850 0.01032 0.00478 -0.0564 0.8447 0.9763
1.500 0.4224 0.01004 0.00440 -0.0577 0.8186 0.9805
1.750 0.4568 0.00993 0.00421 -0.0587 0.7881 0.9852
2.000 0.4929 0.00987 0.00406 -0.0602 0.7572 0.9892
2.250 0.5271 0.00989 0.00397 -0.0614 0.7236 0.9937
2.500 0.5614 0.00998 0.00389 -0.0626 0.6783 0.9974
2.750 0.5887 0.01023 0.00386 -0.0624 0.6191 1.0000
3.000 0.6047 0.01064 0.00393 -0.0599 0.5457 1.0000
3.250 0.6165 0.01127 0.00409 -0.0567 0.4540 1.0000
3.500 0.6266 0.01203 0.00437 -0.0535 0.3597 1.0000
3.750 0.6388 0.01272 0.00468 -0.0506 0.2851 1.0000
4.000 0.6530 0.01332 0.00499 -0.0482 0.2289 1.0000
4.250 0.6689 0.01383 0.00529 -0.0461 0.1896 1.0000
4.500 0.6858 0.01430 0.00560 -0.0441 0.1596 1.0000
4.750 0.7035 0.01472 0.00590 -0.0422 0.1377 1.0000
5.000 0.7216 0.01513 0.00624 -0.0404 0.1228 1.0000
5.250 0.7400 0.01553 0.00659 -0.0387 0.1119 1.0000
5.750 0.7780 0.01634 0.00735 -0.0354 0.0962 1.0000
6.000 0.7965 0.01683 0.00777 -0.0338 0.0900 1.0000
6.250 0.8170 0.01720 0.00819 -0.0324 0.0845 1.0000
6.500 0.8361 0.01769 0.00864 -0.0310 0.0793 1.0000
6.750 0.8563 0.01812 0.00913 -0.0296 0.0746 1.0000
7.000 0.8763 0.01858 0.00959 -0.0283 0.0700 1.0000
7.250 0.8958 0.01910 0.01012 -0.0270 0.0658 1.0000
7.500 0.9162 0.01956 0.01063 -0.0257 0.0615 1.0000
7.750 0.9352 0.02013 0.01117 -0.0244 0.0578 1.0000
8.000 0.9555 0.02061 0.01173 -0.0232 0.0539 1.0000
8.250 0.9745 0.02118 0.01229 -0.0218 0.0507 1.0000
8.500 0.9938 0.02176 0.01295 -0.0205 0.0475 1.0000
8.750 1.0127 0.02234 0.01356 -0.0192 0.0447 1.0000
9.000 1.0299 0.02302 0.01427 -0.0176 0.0423 1.0000
9.250 1.0476 0.02366 0.01500 -0.0161 0.0398 1.0000
9.500 1.0641 0.02433 0.01569 -0.0145 0.0378 1.0000
9.750 1.0800 0.02516 0.01660 -0.0127 0.0362 1.0000
10.000 1.0960 0.02599 0.01752 -0.0111 0.0345 1.0000
10.250 1.1113 0.02681 0.01840 -0.0094 0.0331 1.0000
10.500 1.1248 0.02775 0.01936 -0.0076 0.0319 1.0000
10.750 1.1399 0.02874 0.02051 -0.0060 0.0306 1.0000
11.000 1.1537 0.02973 0.02161 -0.0043 0.0293 1.0000
11.250 1.1665 0.03072 0.02268 -0.0026 0.0284 1.0000
11.500 1.1776 0.03184 0.02385 -0.0008 0.0276 1.0000
11.750 1.1883 0.03317 0.02531 0.0011 0.0270 1.0000
12.000 1.1984 0.03459 0.02691 0.0029 0.0263 1.0000
12.250 1.2073 0.03608 0.02858 0.0047 0.0256 1.0000
12.500 1.2148 0.03763 0.03027 0.0065 0.0250 1.0000
12.750 1.2212 0.03922 0.03200 0.0083 0.0245 1.0000
13.000 1.2266 0.04087 0.03376 0.0099 0.0241 1.0000
13.250 1.2309 0.04262 0.03560 0.0115 0.0237 1.0000
13.500 1.2339 0.04455 0.03762 0.0129 0.0234 1.0000
13.750 1.2331 0.04700 0.04029 0.0144 0.0230 1.0000
14.000 1.2296 0.04981 0.04336 0.0156 0.0226 1.0000
14.250 1.2239 0.05293 0.04673 0.0165 0.0223 1.0000
14.500 1.2160 0.05644 0.05047 0.0169 0.0220 1.0000
14.750 1.2059 0.06038 0.05463 0.0168 0.0217 1.0000
15.000 1.1935 0.06489 0.05936 0.0161 0.0215 1.0000
15.250 1.1779 0.07017 0.06487 0.0145 0.0214 1.0000
15.500 1.1586 0.07651 0.07145 0.0117 0.0213 1.0000
15.750 1.1341 0.08448 0.07967 0.0075 0.0213 1.0000
16.000 1.0996 0.09544 0.09091 0.0007 0.0214 1.0000
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Polar data table (+)
Polar graphs
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