LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 50,000 Max Cl/Cd: 31.7 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5e-il-50000.txt Download as CSV file: xf-c5e-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5143 0.10842 0.10094 -0.0065 1.0000 0.2693
-8.500 -0.5017 0.10468 0.09724 -0.0053 1.0000 0.2857
-8.250 -0.5014 0.10175 0.09437 -0.0047 1.0000 0.3028
-8.000 -0.4645 0.09719 0.08975 -0.0014 1.0000 0.3268
-7.750 -0.4736 0.09533 0.08800 -0.0005 1.0000 0.3517
-7.500 -0.4477 0.09187 0.08454 0.0021 1.0000 0.3804
-7.250 -0.4470 0.09019 0.08293 0.0047 1.0000 0.4161
-7.000 -0.4115 0.08694 0.07965 0.0079 1.0000 0.4599
-6.750 -0.3968 0.08535 0.07810 0.0118 1.0000 0.5132
-6.500 -0.3657 0.08232 0.07507 0.0144 1.0000 0.5668
-6.250 -0.3437 0.07980 0.07256 0.0166 1.0000 0.6156
-6.000 -0.3257 0.07771 0.07050 0.0189 1.0000 0.6639
-5.750 -0.2875 0.07345 0.06621 0.0182 1.0000 0.7129
-5.500 -0.2664 0.06946 0.06225 0.0164 1.0000 0.7230
-5.000 -0.5044 0.05044 0.04298 -0.0204 1.0000 0.3027
-4.750 -0.4686 0.04564 0.03668 -0.0259 1.0000 0.2034
-4.500 -0.4495 0.04226 0.03299 -0.0253 1.0000 0.1884
-4.250 -0.4306 0.03981 0.03031 -0.0244 1.0000 0.1814
-4.000 -0.4111 0.03755 0.02771 -0.0237 1.0000 0.1768
-3.750 -0.3910 0.03572 0.02557 -0.0229 1.0000 0.1770
-3.500 -0.3699 0.03405 0.02361 -0.0222 1.0000 0.1779
-3.250 -0.3474 0.03246 0.02174 -0.0215 1.0000 0.1779
-3.000 -0.3243 0.03105 0.02006 -0.0209 1.0000 0.1790
-2.750 -0.3010 0.02998 0.01870 -0.0203 1.0000 0.1842
-2.500 -0.2777 0.02872 0.01735 -0.0198 1.0000 0.1903
-2.250 -0.2538 0.02768 0.01625 -0.0191 1.0000 0.1966
-2.000 -0.2294 0.02678 0.01528 -0.0185 1.0000 0.2061
-1.750 -0.2057 0.02604 0.01452 -0.0177 1.0000 0.2201
-1.500 -0.1826 0.02523 0.01376 -0.0167 1.0000 0.2361
-1.250 -0.1595 0.02418 0.01296 -0.0161 1.0000 0.2636
-1.000 -0.1333 0.02269 0.01195 -0.0167 1.0000 0.3197
-0.750 -0.1346 0.02095 0.01279 -0.0081 1.0000 0.8080
-0.500 -0.0901 0.02143 0.01310 -0.0064 1.0000 1.0000
-0.250 -0.0841 0.02149 0.01295 -0.0043 1.0000 1.0000
0.000 -0.0717 0.02167 0.01292 -0.0033 1.0000 1.0000
0.250 -0.0553 0.02196 0.01301 -0.0031 1.0000 1.0000
0.500 -0.0366 0.02233 0.01321 -0.0032 1.0000 1.0000
0.750 -0.0167 0.02278 0.01350 -0.0035 1.0000 1.0000
1.000 0.0038 0.02329 0.01389 -0.0040 1.0000 1.0000
1.250 0.0246 0.02387 0.01436 -0.0045 1.0000 1.0000
1.500 0.0455 0.02451 0.01490 -0.0051 1.0000 1.0000
1.750 0.0768 0.02537 0.01569 -0.0077 0.9956 1.0000
2.000 0.1240 0.02653 0.01679 -0.0130 0.9844 1.0000
2.250 0.1666 0.02762 0.01785 -0.0175 0.9730 1.0000
2.500 0.2063 0.02867 0.01890 -0.0213 0.9611 1.0000
2.750 0.2438 0.02971 0.01997 -0.0247 0.9490 1.0000
3.000 0.2818 0.03079 0.02110 -0.0281 0.9366 1.0000
3.250 0.3221 0.03189 0.02228 -0.0317 0.9232 1.0000
3.500 0.3689 0.03270 0.02321 -0.0356 0.8998 1.0000
3.750 0.4486 0.03248 0.02323 -0.0420 0.8593 1.0000
4.000 0.5138 0.03145 0.02245 -0.0448 0.8196 1.0000
4.250 0.5790 0.02965 0.02096 -0.0460 0.7849 1.0000
4.500 0.6280 0.02779 0.01938 -0.0444 0.7517 1.0000
4.750 0.6688 0.02500 0.01679 -0.0396 0.7031 1.0000
5.000 0.6922 0.02229 0.01410 -0.0320 0.6208 1.0000
5.250 0.6956 0.02194 0.01225 -0.0226 0.3852 1.0000
5.500 0.7042 0.02434 0.01343 -0.0194 0.2878 1.0000
5.750 0.7271 0.02629 0.01493 -0.0183 0.2475 1.0000
6.000 0.7564 0.02811 0.01636 -0.0182 0.2224 1.0000
6.250 0.7881 0.02987 0.01796 -0.0183 0.2065 1.0000
6.500 0.8181 0.03158 0.01983 -0.0182 0.1960 1.0000
6.750 0.8465 0.03357 0.02187 -0.0181 0.1872 1.0000
7.000 0.8732 0.03553 0.02393 -0.0178 0.1796 1.0000
7.250 0.9002 0.03812 0.02660 -0.0177 0.1754 1.0000
7.500 0.9209 0.04044 0.02942 -0.0167 0.1720 1.0000
7.750 0.9402 0.04292 0.03228 -0.0157 0.1676 1.0000
8.000 0.9596 0.04564 0.03525 -0.0149 0.1644 1.0000
8.250 0.9763 0.04883 0.03877 -0.0139 0.1632 1.0000
8.500 0.9965 0.05257 0.04256 -0.0136 0.1608 1.0000
8.750 1.0027 0.05611 0.04661 -0.0120 0.1600 1.0000
9.000 1.0077 0.06012 0.05105 -0.0107 0.1599 1.0000
9.250 0.9924 0.06492 0.05660 -0.0087 0.1640 1.0000
9.500 0.9634 0.07136 0.06355 -0.0077 0.1698 1.0000
9.750 0.9541 0.07701 0.06936 -0.0077 0.1736 1.0000
10.000 0.9685 0.08238 0.07474 -0.0079 0.1760 1.0000
10.250 0.8540 0.09908 0.09172 -0.0182 0.2066 1.0000
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Polar data table (+)
Polar graphs
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