LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 100,000 Max Cl/Cd: 50.86 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141f-il-100000.txt Download as CSV file: xf-c141f-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL958.89 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4518 0.10119 0.09583 -0.0307 1.0000 0.1036
-8.250 -0.4848 0.09961 0.09438 -0.0313 1.0000 0.1043
-8.000 -0.5195 0.09725 0.09201 -0.0345 1.0000 0.1048
-7.750 -0.5054 0.09217 0.08703 -0.0313 1.0000 0.1061
-7.500 -0.4880 0.08943 0.08435 -0.0267 1.0000 0.1081
-7.250 -0.4877 0.08680 0.08175 -0.0250 1.0000 0.1103
-7.000 -0.4930 0.08392 0.07890 -0.0246 1.0000 0.1129
-6.750 -0.5037 0.08070 0.07566 -0.0262 1.0000 0.1167
-6.500 -0.5242 0.07688 0.07157 -0.0302 1.0000 0.1201
-6.250 -0.5122 0.07331 0.06820 -0.0269 1.0000 0.1220
-6.000 -0.5050 0.07090 0.06584 -0.0245 1.0000 0.1254
-5.750 -0.5102 0.06868 0.06308 -0.0282 1.0000 0.1353
-5.500 -0.4995 0.06423 0.05889 -0.0258 1.0000 0.1373
-5.250 -0.4897 0.06167 0.05640 -0.0239 1.0000 0.1408
-5.000 -0.4813 0.05893 0.05327 -0.0256 1.0000 0.1522
-4.750 -0.4698 0.05584 0.05033 -0.0237 1.0000 0.1553
-4.500 -0.4568 0.05360 0.04780 -0.0243 1.0000 0.1690
-4.250 -0.4436 0.05082 0.04516 -0.0227 1.0000 0.1737
-4.000 -0.4293 0.04851 0.04275 -0.0224 1.0000 0.1892
-3.750 -0.4144 0.04644 0.04063 -0.0217 1.0000 0.2070
-3.500 -0.3989 0.04443 0.03862 -0.0209 1.0000 0.2264
-3.250 -0.3825 0.04258 0.03677 -0.0200 1.0000 0.2486
-3.000 -0.3671 0.04076 0.03497 -0.0190 1.0000 0.2822
-2.750 -0.3501 0.03919 0.03339 -0.0180 1.0000 0.3178
-2.500 -0.2728 0.03313 0.02498 -0.0244 1.0000 0.1325
-2.250 -0.2435 0.03071 0.02207 -0.0241 1.0000 0.1161
-2.000 -0.2180 0.02923 0.02034 -0.0238 1.0000 0.1139
-1.750 -0.1928 0.02815 0.01903 -0.0234 1.0000 0.1139
-1.500 -0.1675 0.02716 0.01783 -0.0230 1.0000 0.1133
-1.250 -0.1425 0.02638 0.01688 -0.0226 1.0000 0.1137
-1.000 -0.1183 0.02590 0.01625 -0.0221 1.0000 0.1167
-0.750 -0.0943 0.02559 0.01578 -0.0215 1.0000 0.1191
-0.500 -0.0689 0.02480 0.01505 -0.0215 1.0000 0.1221
-0.250 -0.0449 0.02448 0.01481 -0.0213 1.0000 0.1278
0.000 -0.0003 0.02440 0.01470 -0.0246 0.9950 0.1353
0.250 0.0404 0.02403 0.01457 -0.0275 0.9894 0.1477
0.750 0.1356 0.02302 0.01445 -0.0359 0.9754 0.2894
1.000 0.1775 0.02145 0.01465 -0.0370 0.9637 1.0000
1.250 0.2308 0.02173 0.01473 -0.0417 0.9484 1.0000
1.500 0.2834 0.02176 0.01466 -0.0461 0.9326 1.0000
1.750 0.3303 0.02165 0.01449 -0.0493 0.9176 1.0000
2.000 0.3715 0.02160 0.01442 -0.0515 0.9055 1.0000
2.250 0.4223 0.02138 0.01420 -0.0553 0.8966 1.0000
2.500 0.4576 0.02114 0.01399 -0.0561 0.8830 1.0000
2.750 0.4954 0.02077 0.01367 -0.0573 0.8696 1.0000
3.000 0.5402 0.01994 0.01292 -0.0590 0.8543 1.0000
3.250 0.5980 0.01813 0.01121 -0.0617 0.8356 1.0000
3.500 0.6405 0.01670 0.00984 -0.0618 0.8095 1.0000
3.750 0.6803 0.01567 0.00886 -0.0619 0.7785 1.0000
4.000 0.7144 0.01499 0.00813 -0.0611 0.7274 1.0000
4.250 0.7472 0.01469 0.00741 -0.0599 0.6092 1.0000
4.500 0.7606 0.01584 0.00738 -0.0561 0.4296 1.0000
4.750 0.7729 0.01712 0.00796 -0.0532 0.3515 1.0000
5.000 0.7902 0.01817 0.00865 -0.0512 0.3067 1.0000
5.250 0.8092 0.01924 0.00941 -0.0496 0.2715 1.0000
5.500 0.8298 0.02039 0.01024 -0.0483 0.2425 1.0000
5.750 0.8527 0.02145 0.01115 -0.0474 0.2197 1.0000
6.000 0.8775 0.02253 0.01211 -0.0468 0.2039 1.0000
6.250 0.9040 0.02370 0.01307 -0.0466 0.1917 1.0000
6.500 0.9287 0.02455 0.01404 -0.0459 0.1818 1.0000
6.750 0.9561 0.02578 0.01515 -0.0459 0.1739 1.0000
7.000 0.9801 0.02665 0.01619 -0.0451 0.1662 1.0000
7.250 1.0071 0.02794 0.01729 -0.0452 0.1592 1.0000
7.500 1.0286 0.02876 0.01840 -0.0439 0.1521 1.0000
7.750 1.0533 0.02982 0.01930 -0.0436 0.1452 1.0000
8.000 1.0734 0.03082 0.02059 -0.0422 0.1382 1.0000
8.250 1.0970 0.03184 0.02149 -0.0417 0.1317 1.0000
8.500 1.1157 0.03310 0.02307 -0.0401 0.1249 1.0000
8.750 1.1392 0.03430 0.02410 -0.0398 0.1186 1.0000
9.000 1.1544 0.03573 0.02594 -0.0376 0.1120 1.0000
9.250 1.1773 0.03728 0.02732 -0.0373 0.1061 1.0000
9.500 1.1884 0.03898 0.02951 -0.0345 0.1002 1.0000
9.750 1.2119 0.04081 0.03111 -0.0345 0.0951 1.0000
10.000 1.2149 0.04310 0.03408 -0.0306 0.0909 1.0000
10.250 1.2326 0.04470 0.03570 -0.0295 0.0868 1.0000
10.500 1.2421 0.04759 0.03880 -0.0274 0.0840 1.0000
10.750 1.2353 0.05082 0.04264 -0.0230 0.0817 1.0000
11.000 1.2324 0.05372 0.04589 -0.0196 0.0795 1.0000
11.250 1.2546 0.05504 0.04706 -0.0193 0.0765 1.0000
11.500 1.2551 0.05869 0.05088 -0.0169 0.0752 1.0000
11.750 1.2345 0.06247 0.05511 -0.0121 0.0749 1.0000
12.000 1.2103 0.06615 0.05912 -0.0073 0.0748 1.0000
12.250 1.1848 0.07021 0.06346 -0.0035 0.0748 1.0000
12.500 1.1583 0.07474 0.06823 -0.0009 0.0749 1.0000
12.750 1.1318 0.07984 0.07353 0.0003 0.0751 1.0000
13.000 1.1069 0.08552 0.07938 0.0003 0.0754 1.0000
13.250 0.9533 0.11525 0.10962 -0.0178 0.0848 1.0000
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Polar data table (+)
Polar graphs
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