LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 500,000 Max Cl/Cd: 62.26 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5c-il-500000-n5.txt Download as CSV file: xf-c5c-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8607 0.05852 0.05524 -0.0705 1.0000 0.0130
-13.500 -0.8863 0.05135 0.04787 -0.0752 1.0000 0.0129
-13.250 -0.9085 0.04655 0.04291 -0.0764 1.0000 0.0129
-13.000 -0.9298 0.04311 0.03931 -0.0752 1.0000 0.0129
-12.750 -0.9513 0.04059 0.03665 -0.0721 1.0000 0.0130
-12.500 -0.9726 0.03868 0.03460 -0.0676 0.9999 0.0130
-12.250 -0.9749 0.03589 0.03158 -0.0671 0.9971 0.0130
-12.000 -0.9717 0.03330 0.02873 -0.0665 0.9944 0.0131
-11.750 -0.9623 0.03120 0.02642 -0.0659 0.9915 0.0132
-11.500 -0.9480 0.02946 0.02450 -0.0656 0.9891 0.0133
-11.250 -0.9297 0.02795 0.02283 -0.0656 0.9872 0.0134
-11.000 -0.9090 0.02662 0.02136 -0.0659 0.9859 0.0136
-10.750 -0.8864 0.02541 0.02001 -0.0663 0.9849 0.0137
-10.500 -0.8681 0.02440 0.01886 -0.0655 0.9824 0.0138
-10.250 -0.8478 0.02340 0.01774 -0.0650 0.9801 0.0140
-10.000 -0.8247 0.02244 0.01665 -0.0651 0.9784 0.0141
-9.750 -0.7998 0.02149 0.01559 -0.0654 0.9770 0.0143
-9.500 -0.7736 0.02059 0.01457 -0.0659 0.9759 0.0145
-9.250 -0.7468 0.01974 0.01360 -0.0665 0.9750 0.0147
-9.000 -0.7195 0.01895 0.01272 -0.0671 0.9741 0.0150
-8.750 -0.6955 0.01829 0.01196 -0.0669 0.9724 0.0153
-8.500 -0.6747 0.01770 0.01130 -0.0659 0.9692 0.0156
-8.250 -0.6495 0.01709 0.01059 -0.0658 0.9671 0.0160
-8.000 -0.6232 0.01650 0.00991 -0.0659 0.9655 0.0163
-7.750 -0.5969 0.01581 0.00917 -0.0661 0.9641 0.0167
-7.500 -0.5694 0.01525 0.00858 -0.0665 0.9628 0.0172
-7.250 -0.5408 0.01479 0.00809 -0.0670 0.9618 0.0178
-7.000 -0.5134 0.01438 0.00763 -0.0673 0.9603 0.0186
-6.750 -0.4935 0.01405 0.00726 -0.0658 0.9565 0.0195
-6.500 -0.4680 0.01371 0.00686 -0.0655 0.9540 0.0204
-6.250 -0.4416 0.01327 0.00641 -0.0655 0.9520 0.0216
-6.000 -0.4139 0.01294 0.00607 -0.0657 0.9504 0.0230
-5.750 -0.3856 0.01264 0.00574 -0.0660 0.9490 0.0244
-5.500 -0.3566 0.01237 0.00543 -0.0665 0.9478 0.0256
-5.250 -0.3290 0.01203 0.00509 -0.0666 0.9462 0.0275
-5.000 -0.3076 0.01183 0.00489 -0.0654 0.9422 0.0292
-4.750 -0.2818 0.01163 0.00466 -0.0651 0.9395 0.0311
-4.500 -0.2546 0.01136 0.00439 -0.0650 0.9371 0.0335
-4.250 -0.2262 0.01109 0.00413 -0.0653 0.9349 0.0372
-4.000 -0.1971 0.01082 0.00387 -0.0656 0.9331 0.0421
-3.750 -0.1700 0.01056 0.00364 -0.0656 0.9306 0.0512
-3.500 -0.1477 0.01026 0.00346 -0.0646 0.9260 0.0736
-3.250 -0.1220 0.00994 0.00330 -0.0643 0.9230 0.1106
-3.000 -0.0943 0.00970 0.00313 -0.0644 0.9206 0.1321
-2.750 -0.0663 0.00942 0.00297 -0.0645 0.9186 0.1608
-2.500 -0.0377 0.00914 0.00279 -0.0648 0.9167 0.1941
-2.250 -0.0158 0.00883 0.00270 -0.0638 0.9113 0.2481
-2.000 0.0087 0.00833 0.00254 -0.0633 0.9074 0.3411
-1.750 0.0321 0.00760 0.00237 -0.0628 0.9043 0.4909
-1.500 0.0567 0.00712 0.00230 -0.0622 0.9015 0.6003
-1.250 0.0809 0.00698 0.00230 -0.0614 0.8960 0.6448
-1.000 0.1087 0.00683 0.00220 -0.0612 0.8906 0.6727
-0.750 0.1366 0.00671 0.00212 -0.0610 0.8846 0.6937
-0.500 0.1635 0.00663 0.00208 -0.0607 0.8783 0.7116
-0.250 0.1928 0.00652 0.00201 -0.0609 0.8736 0.7328
0.000 0.2189 0.00645 0.00199 -0.0603 0.8642 0.7531
0.250 0.2464 0.00636 0.00192 -0.0600 0.8517 0.7713
0.500 0.2733 0.00628 0.00186 -0.0595 0.8358 0.7893
0.750 0.2997 0.00623 0.00180 -0.0589 0.8142 0.8072
1.000 0.3253 0.00624 0.00175 -0.0582 0.7828 0.8236
1.250 0.3495 0.00633 0.00172 -0.0571 0.7402 0.8388
1.500 0.3721 0.00650 0.00175 -0.0557 0.6965 0.8545
1.750 0.3925 0.00679 0.00185 -0.0540 0.6464 0.8696
2.000 0.4112 0.00718 0.00199 -0.0519 0.5799 0.8836
2.250 0.4301 0.00761 0.00215 -0.0500 0.5114 0.8968
2.500 0.4470 0.00823 0.00238 -0.0479 0.4163 0.9106
2.750 0.4667 0.00878 0.00263 -0.0463 0.3385 0.9244
3.000 0.4893 0.00927 0.00285 -0.0454 0.2744 0.9375
3.250 0.5141 0.00971 0.00306 -0.0450 0.2208 0.9494
3.500 0.5405 0.01015 0.00330 -0.0449 0.1763 0.9612
3.750 0.5695 0.01058 0.00354 -0.0455 0.1334 0.9713
4.000 0.6011 0.01092 0.00377 -0.0466 0.1118 0.9794
4.250 0.6332 0.01120 0.00400 -0.0477 0.1008 0.9866
4.500 0.6652 0.01150 0.00426 -0.0489 0.0900 0.9927
4.750 0.6978 0.01178 0.00449 -0.0502 0.0780 0.9968
5.000 0.7267 0.01209 0.00472 -0.0507 0.0648 1.0000
5.250 0.7459 0.01234 0.00493 -0.0490 0.0581 1.0000
5.500 0.7659 0.01259 0.00516 -0.0475 0.0543 1.0000
5.750 0.7867 0.01285 0.00541 -0.0462 0.0519 1.0000
6.000 0.8079 0.01314 0.00569 -0.0450 0.0496 1.0000
6.250 0.8290 0.01347 0.00603 -0.0438 0.0473 1.0000
6.500 0.8505 0.01382 0.00638 -0.0426 0.0453 1.0000
6.750 0.8730 0.01409 0.00668 -0.0417 0.0438 1.0000
7.000 0.8952 0.01440 0.00702 -0.0407 0.0422 1.0000
7.250 0.9171 0.01473 0.00738 -0.0397 0.0407 1.0000
7.500 0.9386 0.01512 0.00778 -0.0386 0.0392 1.0000
7.750 0.9590 0.01560 0.00827 -0.0374 0.0377 1.0000
8.000 0.9798 0.01604 0.00875 -0.0363 0.0366 1.0000
8.250 1.0017 0.01637 0.00914 -0.0353 0.0357 1.0000
8.500 1.0232 0.01674 0.00955 -0.0343 0.0345 1.0000
8.750 1.0438 0.01712 0.00997 -0.0331 0.0332 1.0000
9.000 1.0640 0.01751 0.01040 -0.0319 0.0320 1.0000
9.250 1.0832 0.01798 0.01087 -0.0305 0.0307 1.0000
9.500 1.1019 0.01848 0.01142 -0.0291 0.0295 1.0000
9.750 1.1220 0.01888 0.01188 -0.0279 0.0283 1.0000
10.000 1.1419 0.01929 0.01235 -0.0267 0.0269 1.0000
10.250 1.1616 0.01971 0.01280 -0.0255 0.0257 1.0000
10.500 1.1800 0.02024 0.01333 -0.0242 0.0244 1.0000
10.750 1.1983 0.02076 0.01393 -0.0229 0.0234 1.0000
11.000 1.2164 0.02130 0.01453 -0.0215 0.0224 1.0000
11.250 1.2344 0.02184 0.01513 -0.0202 0.0213 1.0000
11.500 1.2522 0.02239 0.01569 -0.0189 0.0202 1.0000
11.750 1.2685 0.02305 0.01641 -0.0174 0.0193 1.0000
12.000 1.2846 0.02372 0.01716 -0.0159 0.0184 1.0000
12.250 1.3001 0.02443 0.01794 -0.0144 0.0176 1.0000
12.500 1.3149 0.02519 0.01877 -0.0128 0.0170 1.0000
12.750 1.3288 0.02602 0.01965 -0.0112 0.0163 1.0000
13.000 1.3411 0.02696 0.02066 -0.0095 0.0157 1.0000
13.250 1.3536 0.02789 0.02171 -0.0078 0.0153 1.0000
13.500 1.3653 0.02888 0.02280 -0.0061 0.0147 1.0000
13.750 1.3763 0.02993 0.02395 -0.0044 0.0142 1.0000
14.000 1.3865 0.03105 0.02516 -0.0027 0.0137 1.0000
14.250 1.3954 0.03229 0.02649 -0.0011 0.0132 1.0000
14.500 1.4020 0.03373 0.02802 0.0007 0.0128 1.0000
14.750 1.4085 0.03521 0.02962 0.0023 0.0124 1.0000
15.000 1.4147 0.03675 0.03130 0.0038 0.0120 1.0000
15.250 1.4197 0.03844 0.03311 0.0053 0.0115 1.0000
15.500 1.4237 0.04027 0.03507 0.0066 0.0111 1.0000
15.750 1.4262 0.04231 0.03722 0.0077 0.0107 1.0000
16.000 1.4265 0.04462 0.03964 0.0087 0.0103 1.0000
16.250 1.4240 0.04735 0.04249 0.0095 0.0100 1.0000
16.500 1.4207 0.05033 0.04561 0.0099 0.0097 1.0000
16.750 1.4168 0.05354 0.04899 0.0100 0.0094 1.0000
17.000 1.4107 0.05725 0.05286 0.0095 0.0092 1.0000
17.250 1.4022 0.06153 0.05731 0.0086 0.0089 1.0000
17.500 1.3908 0.06651 0.06244 0.0070 0.0087 1.0000
17.750 1.3753 0.07246 0.06858 0.0045 0.0086 1.0000
18.000 1.3557 0.07957 0.07587 0.0011 0.0085 1.0000
18.250 1.3287 0.08852 0.08503 -0.0037 0.0085 1.0000
18.500 1.2904 0.10021 0.09694 -0.0103 0.0087 1.0000
18.750 1.2341 0.11611 0.11309 -0.0191 0.0091 1.0000
19.000 1.1614 0.13605 0.13323 -0.0301 0.0098 1.0000
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Polar data table (+)
Polar graphs
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