LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.81 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141e-il-1000000.txt Download as CSV file: xf-c141e-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0046 0.05298 0.05041 -0.0731 1.0000 0.0163
-14.750 -1.0394 0.04380 0.04096 -0.0805 1.0000 0.0162
-14.500 -1.0571 0.03927 0.03625 -0.0822 1.0000 0.0163
-14.250 -1.0709 0.03627 0.03309 -0.0811 1.0000 0.0164
-14.000 -1.0863 0.03426 0.03094 -0.0776 1.0000 0.0164
-13.750 -1.1080 0.03304 0.02962 -0.0710 1.0000 0.0165
-13.500 -1.1246 0.03198 0.02845 -0.0647 1.0000 0.0165
-13.250 -1.1301 0.03077 0.02711 -0.0601 1.0000 0.0166
-13.000 -1.1302 0.02967 0.02589 -0.0564 1.0000 0.0168
-12.750 -1.1264 0.02866 0.02475 -0.0531 1.0000 0.0169
-12.500 -1.1151 0.02622 0.02206 -0.0524 0.9988 0.0172
-12.250 -1.0951 0.02458 0.02028 -0.0526 0.9974 0.0175
-12.000 -1.0700 0.02369 0.01932 -0.0531 0.9963 0.0178
-11.750 -1.0436 0.02295 0.01852 -0.0537 0.9954 0.0181
-11.500 -1.0164 0.02222 0.01772 -0.0544 0.9946 0.0184
-11.250 -0.9900 0.02148 0.01688 -0.0549 0.9937 0.0188
-11.000 -0.9658 0.02073 0.01603 -0.0549 0.9919 0.0192
-10.750 -0.9395 0.02001 0.01521 -0.0552 0.9903 0.0196
-10.500 -0.9121 0.01938 0.01447 -0.0556 0.9890 0.0199
-10.250 -0.8832 0.01885 0.01384 -0.0563 0.9879 0.0202
-10.000 -0.8578 0.01750 0.01239 -0.0568 0.9867 0.0209
-9.750 -0.8273 0.01704 0.01192 -0.0578 0.9859 0.0215
-9.500 -0.7963 0.01659 0.01142 -0.0588 0.9851 0.0220
-9.250 -0.7650 0.01611 0.01088 -0.0599 0.9845 0.0226
-9.000 -0.7332 0.01563 0.01033 -0.0611 0.9840 0.0232
-8.750 -0.7102 0.01526 0.00989 -0.0602 0.9808 0.0236
-8.500 -0.6832 0.01453 0.00908 -0.0604 0.9788 0.0241
-8.250 -0.6542 0.01391 0.00844 -0.0610 0.9774 0.0249
-8.000 -0.6227 0.01355 0.00808 -0.0620 0.9763 0.0257
-7.750 -0.5902 0.01323 0.00773 -0.0632 0.9755 0.0265
-7.500 -0.5573 0.01290 0.00736 -0.0645 0.9748 0.0273
-7.250 -0.5239 0.01260 0.00702 -0.0658 0.9741 0.0278
-7.000 -0.4933 0.01188 0.00628 -0.0667 0.9733 0.0290
-6.750 -0.4611 0.01156 0.00596 -0.0678 0.9725 0.0300
-6.500 -0.4346 0.01131 0.00570 -0.0676 0.9698 0.0310
-6.250 -0.4082 0.01108 0.00545 -0.0673 0.9666 0.0320
-6.000 -0.3794 0.01074 0.00508 -0.0675 0.9643 0.0329
-5.750 -0.3506 0.01033 0.00468 -0.0678 0.9624 0.0344
-5.500 -0.3204 0.01007 0.00442 -0.0683 0.9607 0.0357
-5.250 -0.2903 0.00986 0.00419 -0.0688 0.9591 0.0372
-5.000 -0.2659 0.00958 0.00391 -0.0680 0.9553 0.0390
-4.750 -0.2401 0.00933 0.00368 -0.0675 0.9516 0.0410
-4.500 -0.2120 0.00913 0.00347 -0.0675 0.9487 0.0432
-4.250 -0.1841 0.00885 0.00320 -0.0674 0.9461 0.0463
-4.000 -0.1561 0.00868 0.00304 -0.0674 0.9434 0.0497
-3.750 -0.1309 0.00847 0.00286 -0.0667 0.9388 0.0540
-3.500 -0.1036 0.00831 0.00272 -0.0665 0.9350 0.0582
-3.250 -0.0760 0.00809 0.00254 -0.0663 0.9316 0.0639
-3.000 -0.0476 0.00797 0.00241 -0.0663 0.9285 0.0686
-2.750 -0.0216 0.00779 0.00229 -0.0659 0.9235 0.0762
-2.500 0.0059 0.00765 0.00216 -0.0657 0.9190 0.0823
-2.250 0.0338 0.00749 0.00203 -0.0656 0.9152 0.0903
-2.000 0.0612 0.00734 0.00193 -0.0654 0.9105 0.1000
-1.750 0.0881 0.00719 0.00182 -0.0651 0.9042 0.1129
-1.500 0.1158 0.00699 0.00168 -0.0649 0.8978 0.1355
-1.250 0.1409 0.00665 0.00158 -0.0644 0.8891 0.2022
-1.000 0.1643 0.00590 0.00141 -0.0637 0.8816 0.3942
-0.750 0.1861 0.00520 0.00134 -0.0627 0.8716 0.5878
-0.500 0.2108 0.00493 0.00129 -0.0618 0.8592 0.6730
-0.250 0.2362 0.00477 0.00126 -0.0611 0.8461 0.7293
0.000 0.2618 0.00465 0.00125 -0.0604 0.8344 0.7758
0.250 0.2868 0.00456 0.00127 -0.0595 0.8205 0.8223
0.500 0.3106 0.00449 0.00133 -0.0582 0.8049 0.8758
0.750 0.3347 0.00452 0.00138 -0.0570 0.7863 0.9093
1.000 0.3599 0.00458 0.00143 -0.0561 0.7701 0.9296
1.250 0.3853 0.00468 0.00148 -0.0552 0.7522 0.9454
1.500 0.4102 0.00482 0.00154 -0.0543 0.7255 0.9585
1.750 0.4357 0.00503 0.00163 -0.0534 0.6923 0.9714
2.000 0.4690 0.00529 0.00175 -0.0545 0.6558 0.9787
2.250 0.5009 0.00564 0.00188 -0.0554 0.6018 0.9844
2.500 0.5323 0.00624 0.00206 -0.0564 0.5038 0.9868
2.750 0.5607 0.00707 0.00232 -0.0570 0.3752 0.9900
3.000 0.5892 0.00775 0.00258 -0.0576 0.2813 0.9935
3.250 0.6214 0.00821 0.00277 -0.0589 0.2254 0.9952
3.500 0.6549 0.00853 0.00293 -0.0603 0.1931 0.9970
3.750 0.6881 0.00884 0.00309 -0.0617 0.1640 0.9988
4.000 0.7177 0.00918 0.00327 -0.0623 0.1320 1.0000
4.250 0.7364 0.00947 0.00343 -0.0606 0.1083 1.0000
4.500 0.7557 0.00971 0.00360 -0.0589 0.0956 1.0000
4.750 0.7756 0.00992 0.00376 -0.0572 0.0875 1.0000
5.000 0.7953 0.01015 0.00395 -0.0556 0.0799 1.0000
5.250 0.8161 0.01033 0.00411 -0.0542 0.0747 1.0000
5.500 0.8362 0.01058 0.00432 -0.0526 0.0677 1.0000
5.750 0.8576 0.01078 0.00449 -0.0513 0.0624 1.0000
6.000 0.8785 0.01103 0.00471 -0.0499 0.0554 1.0000
6.250 0.8993 0.01132 0.00494 -0.0485 0.0480 1.0000
6.500 0.9205 0.01164 0.00521 -0.0472 0.0423 1.0000
6.750 0.9424 0.01195 0.00549 -0.0461 0.0387 1.0000
7.000 0.9644 0.01228 0.00582 -0.0450 0.0363 1.0000
7.250 0.9871 0.01257 0.00612 -0.0440 0.0347 1.0000
7.500 1.0093 0.01293 0.00646 -0.0430 0.0331 1.0000
7.750 1.0306 0.01338 0.00692 -0.0418 0.0316 1.0000
8.000 1.0536 0.01368 0.00724 -0.0410 0.0308 1.0000
8.250 1.0761 0.01402 0.00760 -0.0401 0.0298 1.0000
8.500 1.0982 0.01439 0.00799 -0.0391 0.0289 1.0000
8.750 1.1192 0.01486 0.00847 -0.0379 0.0280 1.0000
9.000 1.1372 0.01556 0.00920 -0.0363 0.0270 1.0000
9.250 1.1592 0.01592 0.00960 -0.0353 0.0266 1.0000
9.500 1.1804 0.01632 0.01005 -0.0343 0.0261 1.0000
9.750 1.2011 0.01674 0.01050 -0.0331 0.0255 1.0000
10.000 1.2210 0.01719 0.01097 -0.0319 0.0249 1.0000
10.250 1.2396 0.01766 0.01147 -0.0304 0.0243 1.0000
10.500 1.2563 0.01824 0.01208 -0.0286 0.0238 1.0000
10.750 1.2692 0.01910 0.01298 -0.0263 0.0232 1.0000
11.000 1.2826 0.01994 0.01389 -0.0241 0.0227 1.0000
11.250 1.3003 0.02044 0.01445 -0.0226 0.0225 1.0000
11.500 1.3171 0.02102 0.01509 -0.0210 0.0221 1.0000
11.750 1.3330 0.02166 0.01579 -0.0193 0.0218 1.0000
12.000 1.3483 0.02234 0.01653 -0.0176 0.0214 1.0000
12.250 1.3631 0.02303 0.01728 -0.0159 0.0210 1.0000
12.500 1.3776 0.02374 0.01804 -0.0143 0.0207 1.0000
12.750 1.3915 0.02449 0.01882 -0.0126 0.0203 1.0000
13.000 1.4037 0.02537 0.01975 -0.0108 0.0200 1.0000
13.250 1.4120 0.02655 0.02099 -0.0085 0.0196 1.0000
13.500 1.4124 0.02845 0.02300 -0.0056 0.0192 1.0000
13.750 1.4225 0.02954 0.02418 -0.0038 0.0191 1.0000
14.000 1.4333 0.03057 0.02529 -0.0023 0.0189 1.0000
14.250 1.4425 0.03175 0.02657 -0.0007 0.0187 1.0000
14.500 1.4505 0.03306 0.02797 0.0009 0.0185 1.0000
14.750 1.4573 0.03450 0.02951 0.0025 0.0183 1.0000
15.000 1.4629 0.03610 0.03121 0.0039 0.0181 1.0000
15.250 1.4675 0.03782 0.03303 0.0053 0.0179 1.0000
15.500 1.4711 0.03969 0.03500 0.0065 0.0177 1.0000
15.750 1.4736 0.04175 0.03715 0.0075 0.0175 1.0000
16.000 1.4751 0.04396 0.03946 0.0084 0.0174 1.0000
16.250 1.4756 0.04638 0.04198 0.0090 0.0172 1.0000
16.500 1.4748 0.04907 0.04476 0.0093 0.0171 1.0000
16.750 1.4728 0.05201 0.04780 0.0094 0.0169 1.0000
17.000 1.4689 0.05535 0.05124 0.0091 0.0168 1.0000
17.250 1.4638 0.05904 0.05503 0.0085 0.0167 1.0000
17.500 1.4569 0.06316 0.05925 0.0074 0.0166 1.0000
17.750 1.4468 0.06791 0.06411 0.0059 0.0165 1.0000
18.000 1.4336 0.07336 0.06970 0.0038 0.0164 1.0000
18.250 1.4172 0.07959 0.07606 0.0011 0.0163 1.0000
18.500 1.3971 0.08669 0.08331 -0.0023 0.0162 1.0000
18.750 1.3747 0.09445 0.09123 -0.0062 0.0161 1.0000
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Polar data table (+)
Polar graphs
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