LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Reynolds number: 50,000 Max Cl/Cd: 31.01 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5d-il-50000-n5.txt Download as CSV file: xf-c5d-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL758.6 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5239 0.09831 0.09040 -0.0418 1.0000 0.0599
-9.750 -0.5335 0.09307 0.08522 -0.0440 1.0000 0.0591
-9.500 -0.5484 0.08693 0.07915 -0.0471 1.0000 0.0581
-9.250 -0.5735 0.08086 0.07314 -0.0495 1.0000 0.0571
-9.000 -0.6058 0.07621 0.06852 -0.0487 1.0000 0.0563
-8.750 -0.6328 0.07161 0.06384 -0.0472 1.0000 0.0556
-8.500 -0.6552 0.06716 0.05921 -0.0451 1.0000 0.0550
-8.250 -0.6711 0.06295 0.05474 -0.0427 1.0000 0.0546
-8.000 -0.6797 0.05912 0.05061 -0.0403 1.0000 0.0544
-7.750 -0.6819 0.05569 0.04690 -0.0381 1.0000 0.0545
-7.500 -0.6780 0.05293 0.04393 -0.0361 1.0000 0.0551
-7.250 -0.6712 0.05047 0.04127 -0.0342 1.0000 0.0562
-7.000 -0.6632 0.04799 0.03853 -0.0323 1.0000 0.0575
-6.750 -0.6536 0.04538 0.03559 -0.0305 1.0000 0.0591
-6.500 -0.6420 0.04271 0.03250 -0.0288 1.0000 0.0606
-6.250 -0.6276 0.04008 0.02940 -0.0272 1.0000 0.0619
-6.000 -0.6104 0.03764 0.02647 -0.0257 1.0000 0.0633
-5.750 -0.5921 0.03581 0.02445 -0.0245 1.0000 0.0658
-5.500 -0.5730 0.03444 0.02298 -0.0234 1.0000 0.0693
-5.250 -0.5518 0.03288 0.02114 -0.0223 1.0000 0.0730
-5.000 -0.5291 0.03133 0.01928 -0.0212 1.0000 0.0765
-4.750 -0.5083 0.03027 0.01826 -0.0203 1.0000 0.0818
-4.500 -0.4853 0.02920 0.01695 -0.0192 1.0000 0.0884
-4.250 -0.4632 0.02821 0.01602 -0.0183 1.0000 0.0948
-4.000 -0.4409 0.02738 0.01510 -0.0173 1.0000 0.1051
-3.750 -0.4186 0.02655 0.01420 -0.0163 1.0000 0.1176
-3.500 -0.3967 0.02567 0.01340 -0.0155 1.0000 0.1361
-3.250 -0.3747 0.02475 0.01261 -0.0149 1.0000 0.1652
-3.000 -0.3536 0.02372 0.01187 -0.0143 1.0000 0.2142
-2.750 -0.3329 0.02241 0.01124 -0.0139 1.0000 0.3197
-2.500 -0.3215 0.02103 0.01157 -0.0099 1.0000 0.6204
-2.250 -0.3095 0.02103 0.01193 -0.0049 1.0000 0.7662
-2.000 -0.2919 0.02120 0.01212 -0.0012 1.0000 0.8455
-1.750 -0.2601 0.02146 0.01225 -0.0008 1.0000 0.9059
-1.500 -0.2053 0.02187 0.01239 -0.0056 1.0000 0.9604
-1.250 -0.1339 0.02225 0.01247 -0.0147 1.0000 1.0000
-1.000 -0.1304 0.02204 0.01214 -0.0115 1.0000 1.0000
-0.750 -0.1239 0.02192 0.01188 -0.0088 1.0000 1.0000
-0.500 -0.1132 0.02190 0.01172 -0.0068 1.0000 1.0000
-0.250 -0.0776 0.02220 0.01184 -0.0094 0.9933 1.0000
0.000 -0.0427 0.02252 0.01201 -0.0118 0.9863 1.0000
0.250 -0.0089 0.02283 0.01219 -0.0140 0.9789 1.0000
0.500 0.0259 0.02318 0.01244 -0.0163 0.9719 1.0000
0.750 0.0598 0.02353 0.01270 -0.0183 0.9642 1.0000
1.000 0.0918 0.02385 0.01296 -0.0199 0.9558 1.0000
1.250 0.1287 0.02424 0.01331 -0.0224 0.9488 1.0000
1.500 0.1581 0.02453 0.01358 -0.0235 0.9389 1.0000
1.750 0.1929 0.02488 0.01393 -0.0254 0.9306 1.0000
2.000 0.2268 0.02518 0.01425 -0.0272 0.9208 1.0000
2.250 0.2578 0.02544 0.01455 -0.0283 0.9096 1.0000
2.500 0.2925 0.02570 0.01487 -0.0300 0.8995 1.0000
2.750 0.3287 0.02593 0.01519 -0.0319 0.8895 1.0000
3.000 0.3585 0.02612 0.01547 -0.0325 0.8767 1.0000
3.250 0.3921 0.02617 0.01563 -0.0335 0.8625 1.0000
3.500 0.4293 0.02600 0.01561 -0.0348 0.8462 1.0000
3.750 0.4698 0.02556 0.01535 -0.0361 0.8284 1.0000
4.000 0.5018 0.02501 0.01496 -0.0356 0.8042 1.0000
4.250 0.5398 0.02405 0.01419 -0.0355 0.7774 1.0000
4.500 0.5697 0.02330 0.01359 -0.0341 0.7444 1.0000
4.750 0.6018 0.02259 0.01303 -0.0330 0.7055 1.0000
5.000 0.6348 0.02198 0.01245 -0.0320 0.6513 1.0000
5.250 0.6696 0.02159 0.01166 -0.0308 0.5352 1.0000
5.500 0.6848 0.02257 0.01162 -0.0275 0.3762 1.0000
5.750 0.6925 0.02406 0.01239 -0.0243 0.2781 1.0000
6.000 0.7044 0.02544 0.01335 -0.0220 0.2184 1.0000
6.250 0.7187 0.02679 0.01436 -0.0202 0.1836 1.0000
6.500 0.7364 0.02802 0.01547 -0.0188 0.1601 1.0000
6.750 0.7569 0.02920 0.01664 -0.0177 0.1447 1.0000
7.000 0.7801 0.03034 0.01778 -0.0171 0.1328 1.0000
7.250 0.8057 0.03152 0.01893 -0.0168 0.1230 1.0000
7.500 0.8333 0.03273 0.02019 -0.0168 0.1149 1.0000
7.750 0.8654 0.03420 0.02176 -0.0174 0.1094 1.0000
8.000 0.8941 0.03565 0.02338 -0.0176 0.1034 1.0000
8.250 0.9213 0.03724 0.02487 -0.0178 0.0983 1.0000
8.500 0.9479 0.03909 0.02715 -0.0175 0.0944 1.0000
8.750 0.9711 0.04098 0.02931 -0.0170 0.0904 1.0000
9.000 0.9922 0.04274 0.03112 -0.0164 0.0865 1.0000
9.250 1.0108 0.04507 0.03374 -0.0154 0.0835 1.0000
9.500 1.0239 0.04763 0.03682 -0.0135 0.0807 1.0000
9.750 1.0350 0.04997 0.03949 -0.0117 0.0774 1.0000
10.000 1.0467 0.05214 0.04186 -0.0101 0.0747 1.0000
10.250 1.0601 0.05467 0.04445 -0.0090 0.0725 1.0000
10.500 1.0553 0.05792 0.04822 -0.0056 0.0709 1.0000
10.750 1.0457 0.06129 0.05207 -0.0021 0.0693 1.0000
11.000 1.0328 0.06464 0.05578 0.0014 0.0681 1.0000
11.250 1.0160 0.06806 0.05949 0.0047 0.0672 1.0000
11.500 0.9956 0.07193 0.06362 0.0074 0.0668 1.0000
11.750 0.9710 0.07646 0.06838 0.0090 0.0667 1.0000
12.000 0.9418 0.08199 0.07412 0.0090 0.0669 1.0000
12.250 0.9084 0.08901 0.08132 0.0067 0.0674 1.0000
12.500 0.8728 0.09811 0.09053 0.0017 0.0682 1.0000
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Polar data table (+)
Polar graphs
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