LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 500,000 Max Cl/Cd: 88.42 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141e-il-500000.txt Download as CSV file: xf-c141e-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL761.11 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6086 0.07247 0.06998 -0.0527 1.0000 0.0280
-10.250 -0.6230 0.06904 0.06657 -0.0544 1.0000 0.0283
-10.000 -0.6454 0.06636 0.06388 -0.0533 1.0000 0.0284
-9.750 -0.6722 0.06475 0.06226 -0.0488 1.0000 0.0285
-9.500 -0.6881 0.06268 0.06017 -0.0456 1.0000 0.0286
-9.250 -0.8272 0.03076 0.02628 -0.0418 0.9955 0.0267
-9.000 -0.8086 0.02709 0.02201 -0.0422 0.9935 0.0274
-8.750 -0.7869 0.02488 0.01936 -0.0421 0.9909 0.0280
-8.500 -0.7616 0.02308 0.01745 -0.0427 0.9888 0.0287
-8.250 -0.7317 0.02231 0.01661 -0.0437 0.9871 0.0294
-8.000 -0.7008 0.02156 0.01575 -0.0449 0.9857 0.0302
-7.750 -0.6691 0.02073 0.01476 -0.0461 0.9846 0.0314
-7.500 -0.6405 0.02000 0.01382 -0.0465 0.9824 0.0323
-7.250 -0.6154 0.01863 0.01232 -0.0464 0.9795 0.0332
-7.000 -0.5856 0.01798 0.01167 -0.0472 0.9774 0.0341
-6.750 -0.5538 0.01745 0.01108 -0.0483 0.9757 0.0352
-6.500 -0.5208 0.01693 0.01048 -0.0495 0.9743 0.0365
-6.250 -0.4867 0.01656 0.01000 -0.0509 0.9732 0.0377
-6.000 -0.4544 0.01558 0.00902 -0.0523 0.9723 0.0393
-5.750 -0.4305 0.01518 0.00863 -0.0515 0.9679 0.0405
-5.500 -0.4005 0.01479 0.00820 -0.0521 0.9652 0.0421
-5.250 -0.3675 0.01449 0.00784 -0.0532 0.9633 0.0437
-5.000 -0.3353 0.01379 0.00717 -0.0544 0.9617 0.0459
-4.750 -0.3007 0.01344 0.00684 -0.0559 0.9605 0.0481
-4.500 -0.2648 0.01316 0.00652 -0.0577 0.9595 0.0506
-4.250 -0.2295 0.01265 0.00607 -0.0594 0.9587 0.0542
-3.750 -0.1769 0.01205 0.00549 -0.0588 0.9502 0.0615
-3.500 -0.1418 0.01181 0.00527 -0.0604 0.9485 0.0669
-3.250 -0.1073 0.01146 0.00496 -0.0618 0.9471 0.0736
-3.000 -0.0722 0.01123 0.00474 -0.0633 0.9457 0.0800
-2.750 -0.0380 0.01088 0.00446 -0.0647 0.9444 0.0893
-2.500 -0.0159 0.01069 0.00430 -0.0634 0.9383 0.0976
-2.250 0.0143 0.01046 0.00410 -0.0638 0.9349 0.1078
-2.000 0.0460 0.01015 0.00388 -0.0646 0.9325 0.1237
-1.750 0.0778 0.00977 0.00364 -0.0654 0.9304 0.1544
-1.500 0.1013 0.00891 0.00344 -0.0649 0.9261 0.3287
-1.250 0.1183 0.00778 0.00333 -0.0630 0.9199 0.6148
-1.000 0.1445 0.00729 0.00322 -0.0623 0.9162 0.7224
-0.750 0.1716 0.00696 0.00310 -0.0616 0.9117 0.7879
-0.500 0.1946 0.00673 0.00305 -0.0599 0.9036 0.8386
-0.250 0.2230 0.00654 0.00295 -0.0592 0.8986 0.8822
0.000 0.2466 0.00649 0.00298 -0.0575 0.8895 0.9189
0.250 0.2757 0.00641 0.00288 -0.0569 0.8804 0.9432
0.500 0.3059 0.00639 0.00283 -0.0568 0.8689 0.9579
0.750 0.3414 0.00641 0.00282 -0.0580 0.8575 0.9676
1.000 0.3829 0.00644 0.00280 -0.0606 0.8441 0.9747
1.250 0.4269 0.00651 0.00282 -0.0637 0.8284 0.9834
1.500 0.4721 0.00654 0.00280 -0.0673 0.8132 0.9874
1.750 0.5092 0.00658 0.00277 -0.0692 0.7916 0.9918
2.000 0.5460 0.00664 0.00274 -0.0710 0.7654 0.9954
2.250 0.5830 0.00674 0.00271 -0.0729 0.7333 0.9988
2.500 0.6101 0.00690 0.00271 -0.0728 0.6919 1.0000
2.750 0.6292 0.00719 0.00273 -0.0709 0.6324 1.0000
3.000 0.6444 0.00769 0.00283 -0.0684 0.5461 1.0000
3.250 0.6548 0.00850 0.00305 -0.0651 0.4248 1.0000
3.500 0.6660 0.00931 0.00335 -0.0620 0.3185 1.0000
4.000 0.6992 0.01024 0.00379 -0.0578 0.2200 1.0000
4.250 0.7175 0.01061 0.00400 -0.0560 0.1902 1.0000
5.000 0.7734 0.01172 0.00469 -0.0507 0.1107 1.0000
5.250 0.7930 0.01207 0.00497 -0.0491 0.0988 1.0000
5.500 0.8127 0.01243 0.00527 -0.0475 0.0896 1.0000
5.750 0.8335 0.01276 0.00556 -0.0461 0.0818 1.0000
6.000 0.8546 0.01309 0.00588 -0.0448 0.0739 1.0000
6.250 0.8753 0.01349 0.00624 -0.0435 0.0657 1.0000
6.500 0.8955 0.01397 0.00665 -0.0421 0.0582 1.0000
6.750 0.9177 0.01430 0.00698 -0.0410 0.0533 1.0000
7.000 0.9378 0.01482 0.00748 -0.0396 0.0493 1.0000
7.250 0.9598 0.01518 0.00786 -0.0386 0.0465 1.0000
7.500 0.9798 0.01572 0.00836 -0.0372 0.0438 1.0000
7.750 1.0001 0.01624 0.00892 -0.0359 0.0421 1.0000
8.000 1.0210 0.01670 0.00941 -0.0347 0.0405 1.0000
8.250 1.0414 0.01720 0.00992 -0.0335 0.0391 1.0000
8.500 1.0596 0.01788 0.01060 -0.0319 0.0377 1.0000
8.750 1.0776 0.01861 0.01137 -0.0303 0.0366 1.0000
9.000 1.0977 0.01913 0.01195 -0.0290 0.0356 1.0000
9.250 1.1162 0.01971 0.01258 -0.0275 0.0346 1.0000
9.500 1.1339 0.02033 0.01323 -0.0259 0.0338 1.0000
9.750 1.1508 0.02102 0.01394 -0.0242 0.0330 1.0000
10.000 1.1659 0.02204 0.01498 -0.0224 0.0322 1.0000
10.250 1.1821 0.02312 0.01613 -0.0207 0.0315 1.0000
10.500 1.1994 0.02380 0.01690 -0.0192 0.0309 1.0000
10.750 1.2161 0.02455 0.01774 -0.0176 0.0302 1.0000
11.000 1.2320 0.02535 0.01862 -0.0160 0.0295 1.0000
11.250 1.2474 0.02622 0.01955 -0.0143 0.0289 1.0000
11.500 1.2621 0.02714 0.02053 -0.0127 0.0284 1.0000
11.750 1.2763 0.02817 0.02160 -0.0110 0.0279 1.0000
12.000 1.2901 0.02964 0.02311 -0.0095 0.0274 1.0000
12.250 1.3026 0.03153 0.02514 -0.0079 0.0269 1.0000
12.500 1.3123 0.03264 0.02641 -0.0057 0.0266 1.0000
12.750 1.3208 0.03393 0.02786 -0.0036 0.0263 1.0000
13.000 1.3280 0.03532 0.02941 -0.0015 0.0259 1.0000
13.250 1.3340 0.03681 0.03104 0.0007 0.0255 1.0000
13.500 1.3390 0.03837 0.03274 0.0027 0.0251 1.0000
13.750 1.3433 0.04000 0.03449 0.0046 0.0247 1.0000
14.000 1.3457 0.04182 0.03644 0.0064 0.0244 1.0000
14.250 1.3465 0.04383 0.03859 0.0082 0.0242 1.0000
14.500 1.3464 0.04599 0.04087 0.0097 0.0240 1.0000
14.750 1.3452 0.04834 0.04333 0.0110 0.0237 1.0000
15.000 1.3426 0.05095 0.04607 0.0121 0.0235 1.0000
15.250 1.3379 0.05394 0.04917 0.0129 0.0234 1.0000
15.500 1.3289 0.05755 0.05292 0.0135 0.0232 1.0000
15.750 1.3147 0.06199 0.05754 0.0135 0.0231 1.0000
16.000 1.2954 0.06727 0.06303 0.0128 0.0230 1.0000
16.250 1.2725 0.07345 0.06943 0.0110 0.0229 1.0000
16.500 1.2490 0.08024 0.07643 0.0082 0.0229 1.0000
16.750 1.2249 0.08781 0.08420 0.0041 0.0229 1.0000
17.000 1.2003 0.09627 0.09287 -0.0011 0.0229 1.0000
17.250 1.1714 0.10656 0.10338 -0.0082 0.0230 1.0000
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Polar data table (+)
Polar graphs
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