LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.51 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5b-il-1000000.txt Download as CSV file: xf-c5b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL488.2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7241 0.07079 0.06879 -0.0604 1.0000 0.0165
-12.500 -0.7674 0.06025 0.05809 -0.0675 1.0000 0.0163
-12.250 -0.8021 0.05426 0.05197 -0.0691 1.0000 0.0162
-12.000 -0.8355 0.05015 0.04774 -0.0675 1.0000 0.0161
-11.750 -0.8682 0.04728 0.04475 -0.0635 1.0000 0.0160
-11.500 -0.8985 0.04419 0.04150 -0.0597 0.9992 0.0159
-11.250 -0.9160 0.03883 0.03575 -0.0591 0.9957 0.0158
-11.000 -0.9348 0.03122 0.02745 -0.0575 0.9920 0.0152
-10.750 -0.9264 0.02785 0.02371 -0.0565 0.9895 0.0151
-10.500 -0.9081 0.02569 0.02131 -0.0565 0.9880 0.0152
-10.250 -0.8858 0.02398 0.01939 -0.0568 0.9868 0.0153
-10.000 -0.8613 0.02256 0.01780 -0.0573 0.9860 0.0154
-9.750 -0.8355 0.02131 0.01641 -0.0579 0.9853 0.0156
-9.500 -0.8123 0.02026 0.01525 -0.0578 0.9838 0.0158
-9.250 -0.7919 0.01935 0.01423 -0.0569 0.9810 0.0160
-9.000 -0.7665 0.01844 0.01322 -0.0570 0.9794 0.0161
-8.750 -0.7395 0.01760 0.01230 -0.0575 0.9782 0.0163
-8.500 -0.7118 0.01681 0.01143 -0.0580 0.9773 0.0164
-8.250 -0.6832 0.01609 0.01064 -0.0588 0.9765 0.0166
-8.000 -0.6537 0.01542 0.00990 -0.0596 0.9758 0.0167
-7.750 -0.6232 0.01481 0.00924 -0.0607 0.9753 0.0169
-7.500 -0.5922 0.01424 0.00863 -0.0618 0.9748 0.0170
-7.250 -0.5622 0.01346 0.00778 -0.0628 0.9744 0.0172
-7.000 -0.5490 0.01286 0.00713 -0.0600 0.9691 0.0176
-6.750 -0.5204 0.01230 0.00654 -0.0605 0.9677 0.0181
-6.500 -0.4900 0.01190 0.00611 -0.0614 0.9667 0.0187
-6.250 -0.4593 0.01155 0.00576 -0.0623 0.9657 0.0195
-6.000 -0.4281 0.01123 0.00542 -0.0632 0.9648 0.0206
-5.750 -0.3975 0.01084 0.00500 -0.0640 0.9639 0.0218
-5.500 -0.3670 0.01044 0.00461 -0.0648 0.9630 0.0245
-5.250 -0.3399 0.01026 0.00442 -0.0648 0.9609 0.0264
-5.000 -0.3176 0.00994 0.00411 -0.0638 0.9572 0.0299
-4.750 -0.2890 0.00973 0.00390 -0.0640 0.9551 0.0324
-4.500 -0.2598 0.00941 0.00359 -0.0644 0.9531 0.0369
-4.250 -0.2291 0.00915 0.00333 -0.0651 0.9513 0.0415
-4.000 -0.1993 0.00880 0.00305 -0.0657 0.9495 0.0545
-3.750 -0.1777 0.00838 0.00287 -0.0646 0.9456 0.1021
-3.500 -0.1518 0.00814 0.00271 -0.0643 0.9424 0.1302
-3.250 -0.1245 0.00782 0.00254 -0.0643 0.9398 0.1643
-3.000 -0.0971 0.00744 0.00235 -0.0645 0.9375 0.2164
-2.750 -0.0707 0.00693 0.00217 -0.0645 0.9352 0.3070
-2.500 -0.0490 0.00641 0.00203 -0.0635 0.9314 0.4149
-2.250 -0.0253 0.00595 0.00192 -0.0628 0.9275 0.5130
-2.000 0.0013 0.00564 0.00182 -0.0626 0.9241 0.5796
-1.750 0.0291 0.00541 0.00173 -0.0626 0.9209 0.6286
-1.500 0.0554 0.00527 0.00172 -0.0622 0.9168 0.6724
-1.250 0.0818 0.00515 0.00167 -0.0618 0.9109 0.7013
-1.000 0.1110 0.00504 0.00157 -0.0619 0.9051 0.7164
-0.750 0.1375 0.00498 0.00152 -0.0615 0.8979 0.7270
-0.250 0.1932 0.00487 0.00143 -0.0612 0.8839 0.7490
0.000 0.2211 0.00481 0.00135 -0.0610 0.8734 0.7574
0.250 0.2480 0.00478 0.00130 -0.0607 0.8597 0.7667
0.500 0.2747 0.00475 0.00127 -0.0603 0.8444 0.7769
0.750 0.3015 0.00476 0.00125 -0.0599 0.8279 0.7882
1.000 0.3279 0.00479 0.00126 -0.0595 0.8099 0.8000
1.250 0.3538 0.00482 0.00128 -0.0589 0.7896 0.8113
1.500 0.3786 0.00492 0.00130 -0.0581 0.7598 0.8217
1.750 0.4012 0.00511 0.00134 -0.0568 0.7170 0.8319
2.000 0.4216 0.00539 0.00144 -0.0551 0.6606 0.8415
2.250 0.4420 0.00572 0.00156 -0.0535 0.6026 0.8522
2.500 0.4628 0.00606 0.00170 -0.0520 0.5431 0.8635
2.750 0.4806 0.00661 0.00190 -0.0500 0.4497 0.8742
3.000 0.4999 0.00715 0.00211 -0.0484 0.3640 0.8851
3.250 0.5198 0.00767 0.00234 -0.0470 0.2857 0.8969
3.500 0.5405 0.00811 0.00255 -0.0456 0.2224 0.9089
3.750 0.5616 0.00852 0.00277 -0.0443 0.1741 0.9216
4.000 0.5836 0.00883 0.00297 -0.0431 0.1385 0.9353
4.250 0.6061 0.00910 0.00316 -0.0420 0.1163 0.9498
4.500 0.6308 0.00936 0.00336 -0.0414 0.0965 0.9637
4.750 0.6578 0.00976 0.00360 -0.0414 0.0678 0.9754
5.000 0.6884 0.01007 0.00384 -0.0422 0.0587 0.9846
5.250 0.7217 0.01040 0.00414 -0.0436 0.0536 0.9902
5.500 0.7555 0.01065 0.00439 -0.0451 0.0520 0.9949
5.750 0.7903 0.01092 0.00467 -0.0469 0.0498 0.9978
6.000 0.8193 0.01121 0.00496 -0.0474 0.0479 1.0000
6.250 0.8370 0.01147 0.00521 -0.0454 0.0462 1.0000
6.500 0.8559 0.01181 0.00557 -0.0437 0.0443 1.0000
6.750 0.8771 0.01211 0.00590 -0.0425 0.0433 1.0000
7.000 0.9002 0.01232 0.00613 -0.0416 0.0426 1.0000
7.250 0.9234 0.01256 0.00639 -0.0408 0.0415 1.0000
7.500 0.9464 0.01282 0.00667 -0.0400 0.0402 1.0000
7.750 0.9694 0.01311 0.00696 -0.0392 0.0388 1.0000
8.000 0.9912 0.01349 0.00734 -0.0382 0.0368 1.0000
8.250 1.0122 0.01394 0.00782 -0.0371 0.0350 1.0000
8.500 1.0369 0.01408 0.00798 -0.0366 0.0338 1.0000
8.750 1.0611 0.01426 0.00817 -0.0361 0.0321 1.0000
9.000 1.0842 0.01452 0.00839 -0.0354 0.0301 1.0000
9.250 1.1053 0.01494 0.00883 -0.0343 0.0283 1.0000
9.500 1.1280 0.01519 0.00910 -0.0335 0.0271 1.0000
9.750 1.1496 0.01549 0.00941 -0.0325 0.0257 1.0000
10.000 1.1699 0.01587 0.00978 -0.0313 0.0244 1.0000
10.250 1.1886 0.01636 0.01030 -0.0298 0.0232 1.0000
10.500 1.2091 0.01671 0.01069 -0.0287 0.0224 1.0000
10.750 1.2294 0.01707 0.01107 -0.0276 0.0214 1.0000
11.000 1.2489 0.01750 0.01151 -0.0263 0.0204 1.0000
11.250 1.2658 0.01812 0.01215 -0.0247 0.0193 1.0000
11.500 1.2842 0.01861 0.01269 -0.0233 0.0187 1.0000
11.750 1.3027 0.01908 0.01322 -0.0220 0.0181 1.0000
12.000 1.3206 0.01959 0.01377 -0.0206 0.0174 1.0000
12.250 1.3376 0.02016 0.01438 -0.0191 0.0166 1.0000
12.500 1.3516 0.02096 0.01521 -0.0172 0.0157 1.0000
12.750 1.3670 0.02163 0.01596 -0.0156 0.0151 1.0000
13.000 1.3834 0.02223 0.01663 -0.0142 0.0144 1.0000
13.250 1.3984 0.02291 0.01736 -0.0126 0.0136 1.0000
13.500 1.4103 0.02385 0.01834 -0.0107 0.0128 1.0000
13.750 1.4202 0.02491 0.01949 -0.0085 0.0120 1.0000
14.000 1.4341 0.02569 0.02036 -0.0070 0.0114 1.0000
14.250 1.4462 0.02660 0.02134 -0.0053 0.0109 1.0000
14.500 1.4567 0.02763 0.02242 -0.0035 0.0103 1.0000
14.750 1.4629 0.02901 0.02387 -0.0014 0.0098 1.0000
15.000 1.4687 0.03043 0.02539 0.0006 0.0094 1.0000
15.250 1.4783 0.03157 0.02662 0.0022 0.0091 1.0000
15.500 1.4861 0.03289 0.02803 0.0038 0.0088 1.0000
15.750 1.4929 0.03431 0.02954 0.0053 0.0085 1.0000
16.000 1.4984 0.03589 0.03121 0.0067 0.0082 1.0000
16.250 1.5023 0.03766 0.03306 0.0081 0.0080 1.0000
16.500 1.5039 0.03971 0.03521 0.0093 0.0078 1.0000
16.750 1.5022 0.04216 0.03776 0.0105 0.0076 1.0000
17.000 1.4966 0.04514 0.04086 0.0114 0.0075 1.0000
17.500 1.4787 0.05254 0.04854 0.0117 0.0072 1.0000
17.750 1.4704 0.05657 0.05271 0.0111 0.0072 1.0000
18.000 1.4597 0.06123 0.05751 0.0099 0.0071 1.0000
18.250 1.4447 0.06682 0.06326 0.0079 0.0071 1.0000
18.500 1.4259 0.07337 0.06997 0.0051 0.0070 1.0000
18.750 1.4006 0.08155 0.07833 0.0010 0.0071 1.0000
19.000 1.3653 0.09205 0.08904 -0.0047 0.0071 1.0000
19.250 1.3140 0.10617 0.10338 -0.0124 0.0072 1.0000
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Polar data table (+)
Polar graphs
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