LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Reynolds number: 200,000 Max Cl/Cd: 53.57 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5d-il-200000-n5.txt Download as CSV file: xf-c5d-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5721 0.08660 0.08258 -0.0457 1.0000 0.0223
-10.500 -0.6443 0.06518 0.06112 -0.0594 1.0000 0.0213
-10.250 -0.7006 0.05740 0.05316 -0.0601 1.0000 0.0210
-10.000 -0.7438 0.05411 0.04974 -0.0544 1.0000 0.0209
-9.750 -0.7797 0.04983 0.04521 -0.0491 1.0000 0.0207
-9.500 -0.8051 0.04560 0.04064 -0.0442 1.0000 0.0206
-9.250 -0.8191 0.04188 0.03654 -0.0401 1.0000 0.0205
-9.000 -0.8161 0.03822 0.03246 -0.0385 0.9985 0.0206
-8.750 -0.7999 0.03500 0.02880 -0.0388 0.9959 0.0207
-8.500 -0.7804 0.03246 0.02588 -0.0390 0.9938 0.0209
-8.250 -0.7601 0.03035 0.02345 -0.0388 0.9913 0.0211
-8.000 -0.7369 0.02849 0.02130 -0.0390 0.9890 0.0214
-7.750 -0.7116 0.02685 0.01938 -0.0394 0.9870 0.0218
-7.500 -0.6849 0.02540 0.01769 -0.0399 0.9855 0.0223
-7.250 -0.6600 0.02414 0.01621 -0.0399 0.9834 0.0228
-7.000 -0.6350 0.02301 0.01490 -0.0398 0.9808 0.0234
-6.750 -0.6081 0.02198 0.01372 -0.0400 0.9785 0.0240
-6.500 -0.5805 0.02110 0.01281 -0.0406 0.9767 0.0248
-6.250 -0.5510 0.02039 0.01207 -0.0414 0.9750 0.0259
-6.000 -0.5236 0.01972 0.01132 -0.0417 0.9728 0.0272
-5.750 -0.4983 0.01916 0.01066 -0.0415 0.9694 0.0290
-5.500 -0.4703 0.01853 0.01004 -0.0420 0.9667 0.0312
-5.250 -0.4395 0.01804 0.00951 -0.0429 0.9645 0.0341
-5.000 -0.4076 0.01746 0.00887 -0.0441 0.9627 0.0372
-4.750 -0.3814 0.01702 0.00843 -0.0441 0.9590 0.0409
-4.500 -0.3549 0.01658 0.00796 -0.0440 0.9553 0.0457
-4.250 -0.3252 0.01615 0.00754 -0.0447 0.9527 0.0516
-4.000 -0.2937 0.01570 0.00711 -0.0458 0.9506 0.0587
-3.750 -0.2611 0.01528 0.00674 -0.0470 0.9490 0.0705
-3.500 -0.2372 0.01494 0.00648 -0.0465 0.9446 0.0888
-3.250 -0.2103 0.01459 0.00627 -0.0465 0.9407 0.1201
-3.000 -0.1796 0.01422 0.00602 -0.0474 0.9379 0.1516
-2.750 -0.1471 0.01381 0.00579 -0.0487 0.9358 0.1960
-2.500 -0.1138 0.01322 0.00554 -0.0503 0.9340 0.2753
-2.250 -0.0955 0.01244 0.00537 -0.0489 0.9277 0.4212
-2.000 -0.0701 0.01173 0.00537 -0.0485 0.9239 0.5925
-1.750 -0.0400 0.01146 0.00540 -0.0487 0.9213 0.6790
-1.500 -0.0079 0.01131 0.00537 -0.0492 0.9193 0.7284
-1.250 0.0152 0.01128 0.00540 -0.0480 0.9133 0.7555
-1.000 0.0430 0.01121 0.00538 -0.0477 0.9090 0.7808
-0.750 0.0739 0.01111 0.00532 -0.0480 0.9060 0.8032
-0.500 0.1057 0.01101 0.00526 -0.0483 0.9037 0.8256
-0.250 0.1267 0.01103 0.00533 -0.0466 0.8964 0.8463
0.000 0.1558 0.01096 0.00529 -0.0465 0.8923 0.8642
0.250 0.1877 0.01086 0.00521 -0.0469 0.8893 0.8813
0.500 0.2121 0.01084 0.00522 -0.0458 0.8815 0.8965
1.000 0.2757 0.01058 0.00500 -0.0466 0.8675 0.9182
1.250 0.3097 0.01044 0.00487 -0.0476 0.8603 0.9274
1.500 0.3427 0.01028 0.00471 -0.0483 0.8470 0.9356
1.750 0.3785 0.01002 0.00442 -0.0493 0.8278 0.9437
2.000 0.4125 0.00990 0.00427 -0.0502 0.8040 0.9510
2.250 0.4474 0.00980 0.00411 -0.0513 0.7771 0.9588
2.500 0.4840 0.00975 0.00391 -0.0527 0.7322 0.9642
2.750 0.5167 0.00989 0.00378 -0.0534 0.6743 0.9711
3.000 0.5475 0.01022 0.00380 -0.0539 0.6099 0.9780
3.250 0.5752 0.01074 0.00394 -0.0539 0.5288 0.9861
3.500 0.6016 0.01147 0.00418 -0.0541 0.4260 0.9944
3.750 0.6233 0.01228 0.00450 -0.0535 0.3283 1.0000
4.000 0.6341 0.01290 0.00477 -0.0504 0.2622 1.0000
4.250 0.6472 0.01349 0.00507 -0.0479 0.2020 1.0000
4.500 0.6630 0.01401 0.00538 -0.0457 0.1676 1.0000
4.750 0.6810 0.01446 0.00568 -0.0440 0.1354 1.0000
5.000 0.6998 0.01493 0.00602 -0.0425 0.1149 1.0000
5.250 0.7197 0.01537 0.00639 -0.0411 0.0988 1.0000
5.500 0.7399 0.01582 0.00679 -0.0398 0.0873 1.0000
5.750 0.7607 0.01625 0.00721 -0.0385 0.0792 1.0000
6.000 0.7809 0.01676 0.00766 -0.0372 0.0727 1.0000
6.250 0.8022 0.01718 0.00813 -0.0361 0.0684 1.0000
6.500 0.8231 0.01765 0.00861 -0.0350 0.0649 1.0000
6.750 0.8432 0.01819 0.00915 -0.0337 0.0623 1.0000
7.000 0.8632 0.01877 0.00974 -0.0324 0.0602 1.0000
7.250 0.8838 0.01930 0.01034 -0.0312 0.0581 1.0000
7.500 0.9042 0.01985 0.01093 -0.0300 0.0560 1.0000
7.750 0.9241 0.02046 0.01157 -0.0288 0.0542 1.0000
8.000 0.9429 0.02119 0.01230 -0.0275 0.0524 1.0000
8.250 0.9620 0.02199 0.01313 -0.0262 0.0506 1.0000
8.500 0.9824 0.02264 0.01388 -0.0251 0.0489 1.0000
8.750 1.0024 0.02333 0.01465 -0.0239 0.0471 1.0000
9.000 1.0214 0.02403 0.01541 -0.0227 0.0452 1.0000
9.250 1.0393 0.02484 0.01624 -0.0214 0.0435 1.0000
9.500 1.0576 0.02598 0.01740 -0.0202 0.0418 1.0000
9.750 1.0762 0.02669 0.01829 -0.0189 0.0402 1.0000
10.000 1.0941 0.02753 0.01926 -0.0175 0.0385 1.0000
10.250 1.1106 0.02833 0.02016 -0.0160 0.0368 1.0000
10.500 1.1257 0.02913 0.02100 -0.0144 0.0354 1.0000
10.750 1.1405 0.03028 0.02219 -0.0129 0.0340 1.0000
11.000 1.1554 0.03123 0.02338 -0.0112 0.0324 1.0000
11.250 1.1689 0.03219 0.02451 -0.0094 0.0308 1.0000
11.500 1.1811 0.03308 0.02551 -0.0076 0.0296 1.0000
11.750 1.1923 0.03401 0.02650 -0.0058 0.0286 1.0000
12.000 1.2021 0.03529 0.02787 -0.0040 0.0277 1.0000
12.250 1.2111 0.03689 0.02975 -0.0020 0.0265 1.0000
12.500 1.2186 0.03837 0.03144 -0.0001 0.0254 1.0000
12.750 1.2255 0.03970 0.03290 0.0018 0.0245 1.0000
13.000 1.2321 0.04094 0.03425 0.0034 0.0237 1.0000
13.250 1.2376 0.04231 0.03567 0.0050 0.0232 1.0000
13.500 1.2389 0.04443 0.03800 0.0067 0.0225 1.0000
13.750 1.2365 0.04711 0.04097 0.0083 0.0217 1.0000
14.000 1.2325 0.04993 0.04403 0.0097 0.0211 1.0000
14.250 1.2272 0.05294 0.04725 0.0107 0.0207 1.0000
14.500 1.2210 0.05616 0.05067 0.0112 0.0203 1.0000
14.750 1.2132 0.05972 0.05442 0.0112 0.0200 1.0000
15.000 1.2041 0.06370 0.05856 0.0106 0.0197 1.0000
15.250 1.1929 0.06823 0.06327 0.0093 0.0195 1.0000
15.500 1.1782 0.07366 0.06889 0.0072 0.0193 1.0000
15.750 1.1593 0.08034 0.07577 0.0040 0.0193 1.0000
16.000 1.1275 0.09021 0.08591 -0.0017 0.0193 1.0000
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Polar data table (+)
Polar graphs
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