LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 100,000 Max Cl/Cd: 46.83 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5b-il-100000.txt Download as CSV file: xf-c5b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL488.2 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 -0.5154 0.10304 0.09770 -0.0334 1.0000 0.1453
-9.500 -0.5189 0.09990 0.09461 -0.0333 1.0000 0.1498
-9.250 -0.6066 0.09487 0.08985 -0.0402 1.0000 0.1547
-9.000 -0.5540 0.09187 0.08677 -0.0349 1.0000 0.1579
-8.750 -0.5489 0.08927 0.08419 -0.0330 1.0000 0.1615
-8.500 -0.5778 0.08560 0.08064 -0.0334 1.0000 0.1664
-8.250 -0.6859 0.08279 0.07780 -0.0321 1.0000 0.1697
-8.000 -0.6432 0.07821 0.07339 -0.0303 1.0000 0.1728
-7.750 -0.6397 0.07556 0.07074 -0.0279 1.0000 0.1764
-7.000 -0.7260 0.04716 0.04015 -0.0242 1.0000 0.0822
-6.750 -0.7162 0.04321 0.03593 -0.0223 1.0000 0.0784
-6.500 -0.7071 0.03911 0.03068 -0.0189 1.0000 0.0718
-6.250 -0.6896 0.03632 0.02760 -0.0176 1.0000 0.0710
-6.000 -0.6709 0.03374 0.02469 -0.0162 1.0000 0.0707
-5.750 -0.6507 0.03177 0.02234 -0.0149 1.0000 0.0711
-5.500 -0.6289 0.02943 0.01980 -0.0142 1.0000 0.0732
-5.250 -0.6064 0.02798 0.01828 -0.0135 1.0000 0.0761
-5.000 -0.5827 0.02663 0.01678 -0.0127 1.0000 0.0787
-4.750 -0.5586 0.02540 0.01537 -0.0118 1.0000 0.0820
-4.500 -0.5352 0.02416 0.01412 -0.0110 1.0000 0.0875
-4.250 -0.5122 0.02327 0.01324 -0.0102 1.0000 0.0942
-4.000 -0.4893 0.02228 0.01232 -0.0093 1.0000 0.1026
-3.750 -0.4668 0.02142 0.01153 -0.0085 1.0000 0.1164
-3.500 -0.4442 0.02036 0.01064 -0.0077 1.0000 0.1419
-3.250 -0.4220 0.01758 0.00952 -0.0078 1.0000 0.3667
-3.000 -0.4071 0.01660 0.00997 -0.0043 1.0000 0.6616
-2.750 -0.3914 0.01676 0.01028 -0.0008 1.0000 0.7469
-2.500 -0.3768 0.01699 0.01055 0.0030 1.0000 0.8026
-2.250 -0.3662 0.01729 0.01090 0.0080 1.0000 0.8520
-2.000 -0.3549 0.01766 0.01129 0.0133 1.0000 0.9009
-1.750 -0.3217 0.01823 0.01173 0.0137 1.0000 0.9435
-1.500 -0.2666 0.01876 0.01205 0.0083 1.0000 0.9650
-1.250 -0.1856 0.01953 0.01256 -0.0023 1.0000 0.9851
-1.000 -0.1128 0.01996 0.01280 -0.0120 1.0000 1.0000
-0.750 -0.1165 0.01958 0.01238 -0.0081 1.0000 1.0000
-0.500 -0.1200 0.01922 0.01198 -0.0040 1.0000 1.0000
-0.250 -0.1211 0.01893 0.01165 -0.0004 1.0000 1.0000
0.000 -0.1152 0.01882 0.01147 0.0022 1.0000 1.0000
0.250 -0.1016 0.01890 0.01148 0.0034 1.0000 1.0000
0.500 -0.0842 0.01912 0.01162 0.0040 1.0000 1.0000
0.750 -0.0652 0.01943 0.01186 0.0044 1.0000 1.0000
1.000 -0.0185 0.02015 0.01252 -0.0005 0.9920 1.0000
1.250 0.0273 0.02087 0.01319 -0.0051 0.9838 1.0000
1.500 0.0712 0.02148 0.01377 -0.0092 0.9748 1.0000
1.750 0.1109 0.02195 0.01425 -0.0125 0.9644 1.0000
2.000 0.1494 0.02239 0.01470 -0.0154 0.9537 1.0000
2.250 0.1889 0.02281 0.01515 -0.0184 0.9429 1.0000
2.500 0.2347 0.02314 0.01552 -0.0222 0.9312 1.0000
2.750 0.2847 0.02319 0.01565 -0.0265 0.9171 1.0000
3.000 0.3333 0.02292 0.01548 -0.0299 0.9001 1.0000
3.250 0.3845 0.02231 0.01498 -0.0334 0.8820 1.0000
3.500 0.4358 0.02151 0.01433 -0.0365 0.8653 1.0000
3.750 0.4840 0.02065 0.01363 -0.0390 0.8498 1.0000
4.000 0.5380 0.01926 0.01244 -0.0419 0.8328 1.0000
4.250 0.5883 0.01758 0.01095 -0.0434 0.8085 1.0000
4.500 0.6275 0.01627 0.00977 -0.0432 0.7719 1.0000
4.750 0.6663 0.01538 0.00890 -0.0432 0.7145 1.0000
5.000 0.7114 0.01519 0.00803 -0.0441 0.5453 1.0000
5.250 0.7088 0.01686 0.00836 -0.0380 0.3365 1.0000
5.500 0.7108 0.01861 0.00924 -0.0334 0.2307 1.0000
5.750 0.7216 0.02002 0.01018 -0.0305 0.1850 1.0000
6.000 0.7383 0.02134 0.01122 -0.0285 0.1613 1.0000
6.250 0.7611 0.02254 0.01227 -0.0276 0.1469 1.0000
6.500 0.7865 0.02365 0.01338 -0.0272 0.1361 1.0000
6.750 0.8149 0.02503 0.01469 -0.0274 0.1278 1.0000
7.000 0.8427 0.02627 0.01600 -0.0273 0.1213 1.0000
7.250 0.8727 0.02803 0.01768 -0.0280 0.1149 1.0000
7.500 0.8974 0.02929 0.01920 -0.0272 0.1094 1.0000
7.750 0.9225 0.03075 0.02067 -0.0270 0.1038 1.0000
8.000 0.9465 0.03282 0.02297 -0.0264 0.0996 1.0000
8.250 0.9663 0.03439 0.02488 -0.0249 0.0952 1.0000
8.500 0.9879 0.03610 0.02673 -0.0240 0.0913 1.0000
8.750 1.0095 0.03884 0.02958 -0.0234 0.0886 1.0000
9.000 1.0224 0.04178 0.03295 -0.0212 0.0869 1.0000
9.250 1.0305 0.04424 0.03595 -0.0180 0.0851 1.0000
9.500 1.0360 0.04715 0.03932 -0.0148 0.0834 1.0000
9.750 1.0385 0.05072 0.04333 -0.0115 0.0831 1.0000
10.000 1.0366 0.05468 0.04772 -0.0081 0.0836 1.0000
10.250 1.0310 0.05891 0.05230 -0.0046 0.0845 1.0000
10.500 1.0238 0.06331 0.05699 -0.0015 0.0856 1.0000
10.750 1.0162 0.06780 0.06169 0.0013 0.0865 1.0000
11.000 1.0094 0.07258 0.06662 0.0035 0.0871 1.0000
11.250 0.7773 0.10961 0.10455 -0.0111 0.1767 1.0000
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Polar data table (+)
Polar graphs
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