LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 100,000 Max Cl/Cd: 48.17 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5c-il-100000.txt Download as CSV file: xf-c5c-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL576 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5218 0.09849 0.09331 -0.0346 1.0000 0.1417
-9.000 -0.5162 0.09583 0.09067 -0.0328 1.0000 0.1449
-8.750 -0.5286 0.09277 0.08768 -0.0326 1.0000 0.1493
-8.500 -0.5916 0.08929 0.08438 -0.0344 1.0000 0.1525
-8.250 -0.6480 0.08554 0.08064 -0.0338 1.0000 0.1541
-8.000 -0.6017 0.08247 0.07765 -0.0303 1.0000 0.1572
-7.750 -0.6049 0.07975 0.07495 -0.0283 1.0000 0.1607
-7.500 -0.6710 0.07606 0.07105 -0.0286 1.0000 0.1690
-7.250 -0.6483 0.07222 0.06737 -0.0263 1.0000 0.1713
-7.000 -0.6426 0.06947 0.06463 -0.0242 1.0000 0.1749
-6.750 -0.6947 0.04777 0.04091 -0.0262 1.0000 0.0840
-6.500 -0.6810 0.04424 0.03718 -0.0246 1.0000 0.0795
-6.250 -0.6694 0.04018 0.03270 -0.0229 1.0000 0.0759
-6.000 -0.6557 0.03564 0.02721 -0.0207 1.0000 0.0720
-5.750 -0.6365 0.03352 0.02486 -0.0196 1.0000 0.0732
-5.500 -0.6161 0.03179 0.02293 -0.0186 1.0000 0.0754
-5.250 -0.5939 0.02995 0.02077 -0.0176 1.0000 0.0773
-5.000 -0.5702 0.02819 0.01865 -0.0167 1.0000 0.0790
-4.750 -0.5465 0.02707 0.01712 -0.0157 1.0000 0.0825
-4.500 -0.5225 0.02540 0.01553 -0.0153 1.0000 0.0870
-4.250 -0.4983 0.02434 0.01437 -0.0145 1.0000 0.0917
-4.000 -0.4743 0.02332 0.01331 -0.0139 1.0000 0.0986
-3.750 -0.4505 0.02250 0.01248 -0.0131 1.0000 0.1067
-3.500 -0.4269 0.02155 0.01164 -0.0125 1.0000 0.1177
-3.250 -0.4032 0.02068 0.01086 -0.0118 1.0000 0.1390
-3.000 -0.3789 0.01906 0.00992 -0.0116 1.0000 0.2166
-2.750 -0.3570 0.01683 0.00970 -0.0110 1.0000 0.5622
-2.500 -0.3423 0.01665 0.01013 -0.0070 1.0000 0.7389
-2.250 -0.3284 0.01678 0.01041 -0.0028 1.0000 0.8201
-2.000 -0.3151 0.01706 0.01078 0.0021 1.0000 0.8928
-1.750 -0.2533 0.01803 0.01158 -0.0025 1.0000 0.9726
-1.500 -0.1693 0.01873 0.01195 -0.0138 1.0000 0.9964
-1.250 -0.1574 0.01848 0.01160 -0.0125 1.0000 1.0000
-1.000 -0.1570 0.01816 0.01120 -0.0089 1.0000 1.0000
-0.750 -0.1504 0.01800 0.01093 -0.0063 1.0000 1.0000
-0.500 -0.1370 0.01802 0.01083 -0.0048 1.0000 1.0000
-0.250 -0.1198 0.01816 0.01086 -0.0038 1.0000 1.0000
0.000 -0.1010 0.01839 0.01098 -0.0032 1.0000 1.0000
0.250 -0.0813 0.01867 0.01118 -0.0027 1.0000 1.0000
0.500 -0.0611 0.01901 0.01143 -0.0023 1.0000 1.0000
0.750 -0.0407 0.01940 0.01175 -0.0020 1.0000 1.0000
1.000 -0.0034 0.02006 0.01235 -0.0050 0.9952 1.0000
1.250 0.0419 0.02079 0.01304 -0.0094 0.9866 1.0000
1.500 0.0859 0.02145 0.01367 -0.0135 0.9767 1.0000
1.750 0.1288 0.02203 0.01424 -0.0172 0.9657 1.0000
2.000 0.1703 0.02253 0.01475 -0.0206 0.9544 1.0000
2.250 0.2150 0.02305 0.01530 -0.0244 0.9447 1.0000
2.500 0.2569 0.02340 0.01569 -0.0276 0.9333 1.0000
2.750 0.3050 0.02345 0.01581 -0.0314 0.9184 1.0000
3.000 0.3640 0.02305 0.01553 -0.0366 0.9022 1.0000
3.250 0.4043 0.02260 0.01517 -0.0382 0.8841 1.0000
3.500 0.4505 0.02202 0.01472 -0.0407 0.8687 1.0000
3.750 0.4975 0.02111 0.01397 -0.0429 0.8518 1.0000
4.000 0.5459 0.01991 0.01296 -0.0449 0.8343 1.0000
4.250 0.6020 0.01803 0.01128 -0.0473 0.8139 1.0000
4.500 0.6405 0.01663 0.01002 -0.0468 0.7819 1.0000
4.750 0.6717 0.01575 0.00921 -0.0455 0.7340 1.0000
5.000 0.7240 0.01503 0.00803 -0.0474 0.5922 1.0000
5.250 0.7269 0.01667 0.00821 -0.0418 0.3558 1.0000
5.500 0.7283 0.01856 0.00909 -0.0372 0.2306 1.0000
5.750 0.7398 0.01999 0.01006 -0.0344 0.1854 1.0000
6.000 0.7565 0.02134 0.01112 -0.0324 0.1619 1.0000
6.250 0.7787 0.02254 0.01215 -0.0314 0.1466 1.0000
6.500 0.8029 0.02356 0.01315 -0.0308 0.1351 1.0000
6.750 0.8315 0.02491 0.01450 -0.0308 0.1274 1.0000
7.000 0.8599 0.02622 0.01575 -0.0310 0.1205 1.0000
7.250 0.8884 0.02775 0.01739 -0.0311 0.1144 1.0000
7.500 0.9155 0.02920 0.01896 -0.0310 0.1093 1.0000
7.750 0.9447 0.03144 0.02114 -0.0316 0.1040 1.0000
8.000 0.9656 0.03288 0.02299 -0.0300 0.1004 1.0000
8.250 0.9872 0.03458 0.02494 -0.0290 0.0961 1.0000
8.500 1.0103 0.03666 0.02703 -0.0286 0.0920 1.0000
8.750 1.0279 0.03972 0.03042 -0.0272 0.0899 1.0000
9.000 1.0393 0.04188 0.03312 -0.0243 0.0879 1.0000
9.250 1.0487 0.04441 0.03611 -0.0214 0.0855 1.0000
9.500 1.0559 0.04739 0.03951 -0.0186 0.0842 1.0000
9.750 1.0586 0.05101 0.04358 -0.0153 0.0841 1.0000
10.000 1.0559 0.05508 0.04808 -0.0117 0.0848 1.0000
10.250 1.0483 0.05936 0.05274 -0.0080 0.0859 1.0000
10.500 1.0370 0.06364 0.05735 -0.0044 0.0869 1.0000
10.750 1.0237 0.06792 0.06188 -0.0011 0.0878 1.0000
11.000 1.0093 0.07211 0.06625 0.0020 0.0887 1.0000
11.250 1.0028 0.07693 0.07116 0.0038 0.0897 1.0000
11.500 0.6432 0.11230 0.10735 -0.0047 0.1913 1.0000
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Polar data table (+)
Polar graphs
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