LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 100,000 Max Cl/Cd: 46.43 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5e-il-100000.txt Download as CSV file: xf-c5e-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL1256 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5096 0.11077 0.10524 -0.0121 1.0000 0.1090
-9.500 -0.5005 0.10759 0.10206 -0.0121 1.0000 0.1126
-9.250 -0.5011 0.10403 0.09854 -0.0144 1.0000 0.1168
-9.000 -0.5317 0.09971 0.09434 -0.0243 1.0000 0.1201
-8.750 -0.5693 0.09555 0.09015 -0.0324 1.0000 0.1206
-8.500 -0.5107 0.09123 0.08591 -0.0221 1.0000 0.1243
-8.250 -0.5014 0.08816 0.08286 -0.0217 1.0000 0.1280
-8.000 -0.5103 0.08388 0.07864 -0.0255 1.0000 0.1324
-7.750 -0.5540 0.07976 0.07435 -0.0345 1.0000 0.1363
-7.500 -0.5456 0.07422 0.06889 -0.0341 1.0000 0.1388
-7.250 -0.5245 0.07141 0.06620 -0.0315 1.0000 0.1436
-7.000 -0.5458 0.06966 0.06409 -0.0342 1.0000 0.1527
-6.750 -0.5375 0.06434 0.05889 -0.0334 1.0000 0.1556
-6.500 -0.5247 0.06121 0.05587 -0.0318 1.0000 0.1593
-6.250 -0.5340 0.05988 0.05410 -0.0316 1.0000 0.1707
-6.000 -0.5207 0.05548 0.04995 -0.0300 1.0000 0.1738
-5.750 -0.5127 0.05311 0.04758 -0.0281 1.0000 0.1801
-5.500 -0.5117 0.05059 0.04493 -0.0266 1.0000 0.1904
-5.250 -0.5092 0.04896 0.04312 -0.0247 1.0000 0.2050
-5.000 -0.5000 0.04635 0.04066 -0.0225 1.0000 0.2124
-4.750 -0.4938 0.04417 0.03843 -0.0207 1.0000 0.2274
-4.500 -0.4545 0.03671 0.02919 -0.0224 1.0000 0.1179
-4.250 -0.4330 0.03326 0.02493 -0.0212 1.0000 0.1048
-4.000 -0.4136 0.03146 0.02286 -0.0203 1.0000 0.1050
-3.750 -0.3929 0.02990 0.02100 -0.0195 1.0000 0.1057
-3.500 -0.3708 0.02812 0.01899 -0.0190 1.0000 0.1059
-3.250 -0.3474 0.02643 0.01714 -0.0188 1.0000 0.1066
-3.000 -0.3236 0.02514 0.01576 -0.0186 1.0000 0.1083
-2.750 -0.2967 0.02431 0.01492 -0.0190 0.9989 0.1121
-2.500 -0.2532 0.02351 0.01393 -0.0222 0.9937 0.1187
-2.250 -0.2130 0.02233 0.01273 -0.0248 0.9879 0.1241
-2.000 -0.1692 0.02173 0.01211 -0.0281 0.9827 0.1348
-1.750 -0.1318 0.02088 0.01142 -0.0303 0.9757 0.1468
-1.500 -0.0884 0.02016 0.01085 -0.0335 0.9706 0.1677
-1.250 -0.0541 0.01937 0.01033 -0.0352 0.9625 0.1978
-1.000 -0.0103 0.01809 0.00954 -0.0391 0.9575 0.2804
-0.750 0.0010 0.01683 0.01038 -0.0339 0.9490 0.7910
-0.500 0.0201 0.01724 0.01090 -0.0296 0.9408 0.8672
-0.250 0.0373 0.01748 0.01116 -0.0254 0.9308 0.9162
0.000 0.0917 0.01768 0.01127 -0.0288 0.9271 0.9557
0.250 0.1844 0.01780 0.01128 -0.0406 0.9268 0.9778
0.500 0.2715 0.01767 0.01109 -0.0521 0.9243 0.9938
0.750 0.3266 0.01748 0.01089 -0.0578 0.9154 1.0000
1.000 0.3607 0.01736 0.01076 -0.0595 0.9037 1.0000
1.250 0.4001 0.01707 0.01047 -0.0615 0.8930 1.0000
1.500 0.4288 0.01685 0.01025 -0.0615 0.8787 1.0000
1.750 0.4519 0.01670 0.01011 -0.0603 0.8632 1.0000
2.000 0.4728 0.01656 0.00997 -0.0587 0.8473 1.0000
2.250 0.4921 0.01646 0.00988 -0.0566 0.8314 1.0000
2.500 0.5113 0.01627 0.00969 -0.0543 0.8145 1.0000
2.750 0.5312 0.01594 0.00933 -0.0516 0.7958 1.0000
3.000 0.5476 0.01570 0.00906 -0.0485 0.7738 1.0000
3.250 0.5660 0.01542 0.00875 -0.0456 0.7513 1.0000
3.500 0.5871 0.01510 0.00837 -0.0431 0.7287 1.0000
3.750 0.6061 0.01491 0.00818 -0.0406 0.7012 1.0000
4.000 0.6275 0.01469 0.00792 -0.0385 0.6708 1.0000
4.250 0.6493 0.01451 0.00772 -0.0364 0.6335 1.0000
4.500 0.6691 0.01441 0.00744 -0.0338 0.5675 1.0000
4.750 0.6748 0.01560 0.00733 -0.0291 0.3299 1.0000
5.000 0.6816 0.01787 0.00845 -0.0262 0.2048 1.0000
5.250 0.6981 0.01931 0.00953 -0.0245 0.1736 1.0000
5.500 0.7189 0.02050 0.01057 -0.0233 0.1560 1.0000
5.750 0.7419 0.02172 0.01156 -0.0226 0.1445 1.0000
6.000 0.7670 0.02272 0.01251 -0.0221 0.1353 1.0000
6.250 0.7937 0.02410 0.01378 -0.0219 0.1294 1.0000
6.500 0.8208 0.02526 0.01501 -0.0216 0.1243 1.0000
6.750 0.8479 0.02662 0.01627 -0.0216 0.1195 1.0000
7.000 0.8746 0.02816 0.01790 -0.0214 0.1153 1.0000
7.250 0.9006 0.02959 0.01954 -0.0210 0.1121 1.0000
7.500 0.9262 0.03109 0.02113 -0.0207 0.1087 1.0000
7.750 0.9517 0.03310 0.02306 -0.0207 0.1051 1.0000
8.000 0.9730 0.03491 0.02528 -0.0197 0.1028 1.0000
8.250 0.9933 0.03686 0.02762 -0.0186 0.1001 1.0000
8.500 1.0133 0.03882 0.02983 -0.0177 0.0973 1.0000
8.750 1.0341 0.04096 0.03209 -0.0171 0.0951 1.0000
9.000 1.0547 0.04414 0.03527 -0.0169 0.0929 1.0000
9.250 1.0643 0.04696 0.03864 -0.0149 0.0917 1.0000
9.500 1.0720 0.05028 0.04244 -0.0130 0.0910 1.0000
9.750 1.0787 0.05415 0.04668 -0.0113 0.0912 1.0000
10.000 1.0844 0.05838 0.05119 -0.0099 0.0918 1.0000
10.250 1.0950 0.06343 0.05636 -0.0094 0.0927 1.0000
10.500 1.0288 0.07157 0.06565 -0.0044 0.1025 1.0000
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Polar data table (+)
Polar graphs
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