LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 50,000 Max Cl/Cd: 34.61 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141f-il-50000.txt Download as CSV file: xf-c141f-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4335 0.10391 0.09649 -0.0187 1.0000 0.2549
-7.750 -0.4242 0.10033 0.09297 -0.0169 1.0000 0.2657
-7.500 -0.4548 0.10002 0.09283 -0.0150 1.0000 0.2752
-7.250 -0.4402 0.09641 0.08925 -0.0127 1.0000 0.2921
-7.000 -0.4350 0.09352 0.08642 -0.0102 1.0000 0.3085
-6.750 -0.4364 0.09108 0.08406 -0.0074 1.0000 0.3254
-6.500 -0.4399 0.08885 0.08193 -0.0042 1.0000 0.3441
-6.250 -0.4436 0.08678 0.07993 -0.0007 1.0000 0.3654
-6.000 -0.4564 0.08520 0.07848 0.0031 1.0000 0.3886
-5.750 -0.4391 0.08235 0.07566 0.0071 1.0000 0.4228
-5.500 -0.4350 0.08046 0.07385 0.0119 1.0000 0.4631
-5.250 -0.4219 0.07871 0.07214 0.0176 1.0000 0.5222
-5.000 -0.3182 0.07307 0.06630 0.0173 1.0000 0.6523
-4.750 -0.2102 0.06645 0.05948 0.0115 1.0000 0.8085
-4.000 -0.1075 0.05499 0.04800 0.0001 1.0000 0.9161
-3.750 -0.1989 0.05750 0.05082 0.0169 1.0000 0.8352
-3.500 -0.2800 0.05818 0.05179 0.0284 1.0000 0.7607
-3.250 -0.3531 0.05857 0.05243 0.0401 1.0000 0.7348
-3.000 -0.3294 0.04069 0.03161 -0.0258 1.0000 0.2106
-2.750 -0.2993 0.03835 0.02871 -0.0265 1.0000 0.1948
-2.500 -0.2687 0.03659 0.02626 -0.0269 1.0000 0.1824
-2.250 -0.2421 0.03481 0.02422 -0.0268 1.0000 0.1801
-2.000 -0.2154 0.03340 0.02253 -0.0267 1.0000 0.1799
-1.750 -0.1888 0.03214 0.02101 -0.0264 1.0000 0.1793
-1.500 -0.1625 0.03110 0.01972 -0.0260 1.0000 0.1804
-1.250 -0.1366 0.03037 0.01871 -0.0255 1.0000 0.1838
-1.000 -0.1110 0.02933 0.01766 -0.0251 1.0000 0.1877
-0.750 -0.0863 0.02864 0.01697 -0.0244 1.0000 0.1943
-0.500 -0.0610 0.02822 0.01641 -0.0237 1.0000 0.2026
-0.250 -0.0347 0.02764 0.01592 -0.0234 1.0000 0.2135
0.000 -0.0090 0.02719 0.01555 -0.0231 1.0000 0.2301
0.250 0.0173 0.02675 0.01524 -0.0230 1.0000 0.2562
0.500 0.0431 0.02398 0.01533 -0.0216 1.0000 0.8038
0.750 0.0604 0.02405 0.01492 -0.0194 1.0000 1.0000
1.000 0.0819 0.02456 0.01504 -0.0187 1.0000 1.0000
1.250 0.1028 0.02510 0.01535 -0.0182 1.0000 1.0000
1.500 0.1234 0.02569 0.01577 -0.0178 1.0000 1.0000
1.750 0.1437 0.02632 0.01629 -0.0175 1.0000 1.0000
2.000 0.1637 0.02700 0.01688 -0.0172 1.0000 1.0000
2.250 0.1834 0.02773 0.01755 -0.0170 1.0000 1.0000
2.500 0.2027 0.02852 0.01830 -0.0168 1.0000 1.0000
2.750 0.2216 0.02937 0.01914 -0.0167 1.0000 1.0000
3.000 0.2571 0.03060 0.02038 -0.0198 0.9930 1.0000
3.250 0.3276 0.03213 0.02198 -0.0290 0.9644 1.0000
3.500 0.3884 0.03308 0.02305 -0.0356 0.9362 1.0000
3.750 0.4493 0.03350 0.02361 -0.0413 0.9060 1.0000
4.000 0.5097 0.03318 0.02351 -0.0460 0.8729 1.0000
4.250 0.5811 0.03166 0.02230 -0.0505 0.8352 1.0000
4.500 0.6613 0.02769 0.01870 -0.0526 0.7825 1.0000
4.750 0.7282 0.02324 0.01443 -0.0509 0.6915 1.0000
5.000 0.7739 0.02236 0.01240 -0.0485 0.5101 1.0000
5.250 0.7952 0.02393 0.01303 -0.0463 0.4240 1.0000
5.500 0.8227 0.02563 0.01421 -0.0458 0.3661 1.0000
5.750 0.8542 0.02739 0.01563 -0.0461 0.3245 1.0000
6.000 0.8875 0.02924 0.01721 -0.0468 0.2965 1.0000
6.250 0.9160 0.03097 0.01892 -0.0467 0.2767 1.0000
6.500 0.9446 0.03282 0.02068 -0.0467 0.2617 1.0000
6.750 0.9679 0.03452 0.02264 -0.0458 0.2496 1.0000
7.000 0.9911 0.03652 0.02480 -0.0450 0.2395 1.0000
7.250 1.0145 0.03847 0.02685 -0.0442 0.2301 1.0000
7.500 1.0326 0.04074 0.02942 -0.0427 0.2219 1.0000
7.750 1.0516 0.04284 0.03172 -0.0414 0.2134 1.0000
8.000 1.0670 0.04542 0.03454 -0.0397 0.2061 1.0000
8.250 1.0776 0.04786 0.03737 -0.0373 0.1984 1.0000
8.500 1.0958 0.05054 0.04004 -0.0362 0.1906 1.0000
8.750 1.0947 0.05374 0.04384 -0.0327 0.1854 1.0000
9.000 1.1049 0.05645 0.04673 -0.0307 0.1787 1.0000
9.250 1.1127 0.05998 0.05042 -0.0287 0.1735 1.0000
9.500 1.0987 0.06426 0.05520 -0.0249 0.1716 1.0000
9.750 1.0816 0.06883 0.06015 -0.0215 0.1705 1.0000
10.000 1.0597 0.07376 0.06537 -0.0184 0.1705 1.0000
10.250 1.0333 0.07891 0.07073 -0.0157 0.1715 1.0000
10.500 1.0073 0.08441 0.07634 -0.0139 0.1729 1.0000
10.750 0.9871 0.09045 0.08246 -0.0136 0.1742 1.0000
11.000 0.9757 0.09679 0.08885 -0.0141 0.1752 1.0000
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Polar data table (+)
Polar graphs
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