LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Reynolds number: 50,000 Max Cl/Cd: 27.24 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5a-il-50000.txt Download as CSV file: xf-c5a-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL0 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6622 0.09001 0.08264 -0.0444 1.0000 0.1488
-10.000 -0.6816 0.08396 0.07658 -0.0454 1.0000 0.1407
-9.750 -0.7581 0.07866 0.07127 -0.0425 1.0000 0.1345
-9.500 -0.7812 0.07463 0.06710 -0.0398 1.0000 0.1299
-9.250 -0.7931 0.07059 0.06297 -0.0373 1.0000 0.1269
-9.000 -0.8153 0.06646 0.05858 -0.0337 1.0000 0.1232
-8.750 -0.8478 0.06299 0.05438 -0.0282 1.0000 0.1179
-8.500 -0.8440 0.05925 0.05045 -0.0260 1.0000 0.1169
-8.250 -0.8416 0.05583 0.04675 -0.0234 1.0000 0.1162
-8.000 -0.8373 0.05259 0.04315 -0.0207 1.0000 0.1157
-7.750 -0.8298 0.04948 0.03967 -0.0182 1.0000 0.1153
-7.500 -0.8184 0.04650 0.03632 -0.0160 1.0000 0.1149
-7.250 -0.8037 0.04368 0.03311 -0.0140 1.0000 0.1147
-7.000 -0.7861 0.04111 0.03015 -0.0122 1.0000 0.1152
-6.750 -0.7667 0.03888 0.02751 -0.0105 1.0000 0.1170
-6.500 -0.7439 0.03660 0.02510 -0.0095 1.0000 0.1215
-6.250 -0.7191 0.03478 0.02320 -0.0086 1.0000 0.1279
-6.000 -0.6900 0.03295 0.02127 -0.0079 1.0000 0.1347
-5.750 -0.6627 0.03146 0.01981 -0.0069 1.0000 0.1476
-5.500 -0.6387 0.02987 0.01845 -0.0056 1.0000 0.1662
-5.250 -0.6239 0.02799 0.01691 -0.0031 1.0000 0.1978
-5.000 -0.6272 0.02441 0.01491 0.0012 1.0000 0.3271
-4.750 -0.6379 0.02528 0.01757 0.0147 1.0000 0.6576
-4.500 -0.6227 0.02790 0.02004 0.0234 1.0000 0.7196
-4.250 -0.5074 0.03658 0.02802 0.0263 1.0000 0.8146
-4.000 -0.4248 0.03744 0.02829 0.0191 1.0000 0.8524
-3.750 -0.3435 0.03739 0.02775 0.0105 1.0000 0.8859
-3.500 -0.2878 0.03655 0.02660 0.0046 1.0000 0.9062
-3.250 -0.2453 0.03565 0.02549 0.0007 1.0000 0.9246
-3.000 -0.2030 0.03474 0.02436 -0.0035 1.0000 0.9424
-2.750 -0.1622 0.03381 0.02327 -0.0077 1.0000 0.9582
-2.500 -0.1218 0.03290 0.02221 -0.0120 1.0000 0.9721
-2.250 -0.0791 0.03200 0.02118 -0.0168 1.0000 0.9849
-2.000 -0.0322 0.03105 0.02011 -0.0226 1.0000 0.9966
-1.750 -0.0137 0.03048 0.01950 -0.0229 1.0000 1.0000
-1.500 -0.0083 0.03007 0.01909 -0.0206 1.0000 1.0000
-1.250 -0.0034 0.02969 0.01871 -0.0182 1.0000 1.0000
-1.000 0.0009 0.02935 0.01838 -0.0157 1.0000 1.0000
-0.750 0.0044 0.02904 0.01808 -0.0130 1.0000 1.0000
-0.500 0.0072 0.02877 0.01782 -0.0102 1.0000 1.0000
-0.250 0.0093 0.02852 0.01759 -0.0073 1.0000 1.0000
0.000 0.0106 0.02830 0.01739 -0.0043 1.0000 1.0000
0.250 0.0110 0.02810 0.01721 -0.0012 1.0000 1.0000
0.500 0.0106 0.02792 0.01706 0.0020 1.0000 1.0000
0.750 0.0093 0.02776 0.01692 0.0054 1.0000 1.0000
1.000 0.0071 0.02762 0.01681 0.0088 1.0000 1.0000
1.250 0.0041 0.02748 0.01670 0.0123 1.0000 1.0000
1.500 0.0007 0.02735 0.01660 0.0159 1.0000 1.0000
1.750 -0.0029 0.02725 0.01652 0.0194 1.0000 1.0000
2.000 -0.0055 0.02718 0.01647 0.0227 1.0000 1.0000
2.250 -0.0058 0.02718 0.01650 0.0256 1.0000 1.0000
2.500 -0.0005 0.02736 0.01669 0.0274 1.0000 1.0000
2.750 0.0098 0.02771 0.01706 0.0284 1.0000 1.0000
3.000 0.0232 0.02821 0.01759 0.0288 1.0000 1.0000
3.250 0.0383 0.02883 0.01824 0.0288 1.0000 1.0000
3.500 0.0544 0.02955 0.01902 0.0286 1.0000 1.0000
3.750 0.0734 0.03042 0.01996 0.0278 0.9988 1.0000
4.000 0.1480 0.03257 0.02233 0.0168 0.9720 1.0000
4.250 0.2150 0.03391 0.02393 0.0082 0.9404 1.0000
4.500 0.2954 0.03433 0.02470 -0.0009 0.8980 1.0000
4.750 0.3815 0.03368 0.02447 -0.0093 0.8599 1.0000
5.000 0.4381 0.03267 0.02387 -0.0123 0.8242 1.0000
5.250 0.5901 0.02506 0.01725 -0.0201 0.7332 1.0000
5.500 0.6410 0.02353 0.01403 -0.0152 0.4049 1.0000
5.750 0.6449 0.02579 0.01513 -0.0108 0.3009 1.0000
6.000 0.6773 0.02798 0.01675 -0.0116 0.2433 1.0000
6.250 0.7177 0.02988 0.01853 -0.0135 0.2158 1.0000
6.500 0.7493 0.03160 0.02016 -0.0140 0.1991 1.0000
6.750 0.7766 0.03340 0.02211 -0.0138 0.1883 1.0000
7.000 0.8060 0.03566 0.02433 -0.0141 0.1808 1.0000
7.250 0.8221 0.03743 0.02655 -0.0119 0.1748 1.0000
7.500 0.8445 0.03958 0.02871 -0.0112 0.1678 1.0000
7.750 0.8611 0.04218 0.03168 -0.0094 0.1649 1.0000
8.000 0.8715 0.04466 0.03467 -0.0066 0.1622 1.0000
8.250 0.8807 0.04725 0.03766 -0.0040 0.1586 1.0000
8.500 0.8904 0.05011 0.04084 -0.0016 0.1560 1.0000
8.750 0.8951 0.05349 0.04461 0.0011 0.1557 1.0000
9.000 0.8988 0.05692 0.04836 0.0037 0.1546 1.0000
9.500 0.8780 0.06497 0.05722 0.0103 0.1566 1.0000
9.750 0.8561 0.06976 0.06233 0.0134 0.1601 1.0000
10.000 0.8413 0.07461 0.06735 0.0153 0.1632 1.0000
10.250 0.5924 0.11611 0.10878 -0.0219 0.4018 1.0000
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Polar data table (+)
Polar graphs
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