LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.2 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5e-il-1000000.txt Download as CSV file: xf-c5e-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL1256 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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.2436 0.04112 0.03813 -0.0548 1.0000 0.0157
-15.000 -1.2535 0.03764 0.03447 -0.0550 1.0000 0.0158
-14.750 -1.2572 0.03508 0.03174 -0.0543 1.0000 0.0159
-14.500 -1.2578 0.03300 0.02952 -0.0530 1.0000 0.0161
-14.250 -1.2542 0.03133 0.02769 -0.0514 1.0000 0.0163
-14.000 -1.2442 0.02980 0.02603 -0.0503 1.0000 0.0165
-13.750 -1.2310 0.02849 0.02458 -0.0494 1.0000 0.0166
-13.500 -1.2151 0.02739 0.02335 -0.0485 1.0000 0.0168
-13.250 -1.2062 0.02541 0.02119 -0.0473 1.0000 0.0172
-13.000 -1.1887 0.02440 0.02012 -0.0465 1.0000 0.0176
-12.750 -1.1682 0.02373 0.01941 -0.0459 1.0000 0.0180
-12.500 -1.1465 0.02318 0.01882 -0.0454 1.0000 0.0183
-12.250 -1.1246 0.02264 0.01823 -0.0448 1.0000 0.0187
-12.000 -1.1027 0.02206 0.01759 -0.0443 1.0000 0.0192
-11.750 -1.0807 0.02148 0.01693 -0.0437 1.0000 0.0196
-11.500 -1.0583 0.02094 0.01631 -0.0432 1.0000 0.0200
-11.250 -1.0353 0.02049 0.01579 -0.0426 1.0000 0.0203
-11.000 -1.0169 0.01932 0.01449 -0.0416 1.0000 0.0209
-10.750 -0.9955 0.01871 0.01385 -0.0409 1.0000 0.0214
-10.500 -0.9726 0.01837 0.01349 -0.0402 1.0000 0.0218
-10.250 -0.9497 0.01805 0.01316 -0.0395 1.0000 0.0223
-10.000 -0.9270 0.01770 0.01277 -0.0387 1.0000 0.0227
-9.750 -0.9046 0.01732 0.01234 -0.0379 1.0000 0.0231
-9.500 -0.8823 0.01691 0.01188 -0.0370 1.0000 0.0236
-9.250 -0.8600 0.01653 0.01145 -0.0361 1.0000 0.0240
-9.000 -0.8378 0.01619 0.01105 -0.0351 1.0000 0.0243
-8.750 -0.8155 0.01590 0.01071 -0.0341 1.0000 0.0245
-8.500 -0.7964 0.01493 0.00965 -0.0329 1.0000 0.0251
-8.250 -0.7735 0.01441 0.00911 -0.0322 0.9998 0.0256
-8.000 -0.7382 0.01402 0.00871 -0.0340 0.9980 0.0261
-7.750 -0.7032 0.01367 0.00835 -0.0357 0.9961 0.0266
-7.500 -0.6681 0.01331 0.00797 -0.0375 0.9943 0.0272
-7.250 -0.6341 0.01293 0.00755 -0.0389 0.9919 0.0277
-7.000 -0.6004 0.01256 0.00715 -0.0403 0.9886 0.0283
-6.750 -0.5653 0.01219 0.00676 -0.0420 0.9856 0.0287
-6.500 -0.5305 0.01187 0.00641 -0.0436 0.9822 0.0291
-6.250 -0.5001 0.01139 0.00589 -0.0442 0.9743 0.0296
-6.000 -0.4697 0.01079 0.00528 -0.0450 0.9654 0.0305
-5.750 -0.4395 0.01048 0.00496 -0.0455 0.9533 0.0312
-5.500 -0.4113 0.01025 0.00471 -0.0455 0.9364 0.0319
-5.250 -0.3843 0.01009 0.00450 -0.0452 0.9167 0.0329
-5.000 -0.3578 0.00998 0.00431 -0.0447 0.8969 0.0338
-4.500 -0.3050 0.00960 0.00376 -0.0440 0.8625 0.0355
-4.250 -0.2784 0.00929 0.00342 -0.0437 0.8489 0.0369
-4.000 -0.2509 0.00913 0.00323 -0.0436 0.8377 0.0382
-3.750 -0.2233 0.00900 0.00305 -0.0435 0.8275 0.0396
-3.500 -0.1954 0.00885 0.00288 -0.0434 0.8176 0.0408
-3.250 -0.1678 0.00863 0.00260 -0.0433 0.8088 0.0425
-3.000 -0.1399 0.00842 0.00239 -0.0433 0.8000 0.0450
-2.750 -0.1118 0.00830 0.00224 -0.0433 0.7919 0.0472
-2.500 -0.0838 0.00818 0.00209 -0.0432 0.7817 0.0494
-2.250 -0.0559 0.00802 0.00193 -0.0432 0.7706 0.0540
-2.000 -0.0279 0.00794 0.00181 -0.0431 0.7610 0.0579
-1.750 0.0006 0.00778 0.00170 -0.0432 0.7527 0.0667
-1.500 0.0287 0.00765 0.00161 -0.0432 0.7449 0.0847
-1.250 0.0573 0.00752 0.00156 -0.0433 0.7367 0.1034
-1.000 0.0856 0.00745 0.00151 -0.0433 0.7275 0.1194
-0.750 0.1141 0.00735 0.00145 -0.0434 0.7167 0.1348
-0.500 0.1425 0.00727 0.00140 -0.0434 0.7044 0.1530
-0.250 0.1708 0.00716 0.00136 -0.0435 0.6926 0.1834
0.000 0.1988 0.00686 0.00128 -0.0436 0.6805 0.2687
0.250 0.2247 0.00574 0.00116 -0.0440 0.6677 0.6034
0.500 0.2527 0.00568 0.00117 -0.0439 0.6499 0.6495
0.750 0.2806 0.00569 0.00118 -0.0438 0.6301 0.6763
1.000 0.3086 0.00570 0.00121 -0.0437 0.6115 0.7021
1.250 0.3365 0.00573 0.00125 -0.0436 0.5908 0.7239
1.500 0.3639 0.00584 0.00130 -0.0434 0.5615 0.7430
1.750 0.3913 0.00598 0.00138 -0.0432 0.5314 0.7623
2.000 0.4186 0.00614 0.00146 -0.0430 0.4955 0.7768
2.250 0.4448 0.00645 0.00158 -0.0427 0.4371 0.7917
2.500 0.4692 0.00700 0.00179 -0.0421 0.3477 0.8055
2.750 0.4917 0.00782 0.00212 -0.0414 0.2210 0.8186
3.000 0.5168 0.00830 0.00235 -0.0410 0.1590 0.8311
3.250 0.5429 0.00858 0.00254 -0.0407 0.1308 0.8437
3.500 0.5696 0.00877 0.00271 -0.0403 0.1169 0.8548
3.750 0.5959 0.00902 0.00287 -0.0400 0.0940 0.8663
4.000 0.6221 0.00927 0.00306 -0.0397 0.0807 0.8762
4.250 0.6486 0.00948 0.00326 -0.0393 0.0692 0.8844
4.500 0.6749 0.00971 0.00343 -0.0390 0.0596 0.8932
4.750 0.7009 0.00992 0.00362 -0.0386 0.0555 0.9016
5.000 0.7268 0.01016 0.00385 -0.0382 0.0518 0.9111
5.250 0.7521 0.01032 0.00406 -0.0376 0.0505 0.9211
5.500 0.7770 0.01050 0.00428 -0.0369 0.0493 0.9324
5.750 0.8009 0.01070 0.00450 -0.0360 0.0481 0.9465
6.000 0.8249 0.01091 0.00476 -0.0351 0.0469 0.9670
6.250 0.8550 0.01125 0.00510 -0.0358 0.0452 1.0000
6.500 0.8814 0.01163 0.00549 -0.0357 0.0439 1.0000
6.750 0.9085 0.01188 0.00576 -0.0356 0.0434 1.0000
7.000 0.9352 0.01216 0.00605 -0.0355 0.0426 1.0000
7.250 0.9615 0.01247 0.00637 -0.0354 0.0417 1.0000
7.500 0.9874 0.01279 0.00670 -0.0352 0.0408 1.0000
7.750 1.0131 0.01313 0.00704 -0.0349 0.0399 1.0000
8.000 1.0380 0.01353 0.00744 -0.0345 0.0388 1.0000
8.250 1.0601 0.01423 0.00816 -0.0338 0.0374 1.0000
8.500 1.0852 0.01458 0.00854 -0.0334 0.0368 1.0000
8.750 1.1111 0.01481 0.00880 -0.0332 0.0361 1.0000
9.000 1.1365 0.01509 0.00910 -0.0329 0.0352 1.0000
9.250 1.1618 0.01537 0.00939 -0.0326 0.0341 1.0000
9.500 1.1869 0.01564 0.00965 -0.0323 0.0331 1.0000
9.750 1.2094 0.01617 0.01017 -0.0317 0.0317 1.0000
10.000 1.2332 0.01655 0.01058 -0.0312 0.0307 1.0000
10.250 1.2580 0.01680 0.01087 -0.0308 0.0298 1.0000
10.500 1.2822 0.01710 0.01118 -0.0304 0.0288 1.0000
10.750 1.3060 0.01742 0.01150 -0.0299 0.0278 1.0000
11.000 1.3273 0.01796 0.01203 -0.0291 0.0267 1.0000
11.250 1.3480 0.01852 0.01264 -0.0282 0.0259 1.0000
11.500 1.3697 0.01896 0.01312 -0.0274 0.0253 1.0000
11.750 1.3907 0.01943 0.01363 -0.0265 0.0246 1.0000
12.000 1.4112 0.01991 0.01415 -0.0256 0.0239 1.0000
12.250 1.4308 0.02044 0.01470 -0.0246 0.0234 1.0000
12.500 1.4479 0.02105 0.01533 -0.0232 0.0228 1.0000
12.750 1.4590 0.02196 0.01628 -0.0210 0.0221 1.0000
13.000 1.4735 0.02266 0.01704 -0.0193 0.0218 1.0000
13.250 1.4878 0.02337 0.01782 -0.0178 0.0215 1.0000
13.500 1.5009 0.02419 0.01872 -0.0161 0.0213 1.0000
13.750 1.5133 0.02508 0.01968 -0.0146 0.0210 1.0000
14.000 1.5254 0.02602 0.02069 -0.0131 0.0207 1.0000
14.250 1.5375 0.02698 0.02171 -0.0118 0.0204 1.0000
14.500 1.5490 0.02804 0.02283 -0.0106 0.0201 1.0000
14.750 1.5591 0.02924 0.02410 -0.0094 0.0198 1.0000
15.000 1.5680 0.03060 0.02553 -0.0083 0.0196 1.0000
15.250 1.5757 0.03211 0.02711 -0.0073 0.0193 1.0000
15.500 1.5813 0.03387 0.02894 -0.0063 0.0191 1.0000
15.750 1.5848 0.03590 0.03105 -0.0055 0.0189 1.0000
16.000 1.5856 0.03824 0.03349 -0.0047 0.0187 1.0000
16.250 1.5833 0.04101 0.03637 -0.0042 0.0185 1.0000
16.500 1.5804 0.04391 0.03939 -0.0038 0.0183 1.0000
16.750 1.5828 0.04635 0.04194 -0.0037 0.0182 1.0000
17.000 1.5832 0.04909 0.04479 -0.0038 0.0181 1.0000
17.250 1.5818 0.05209 0.04790 -0.0041 0.0180 1.0000
17.500 1.5791 0.05536 0.05129 -0.0046 0.0179 1.0000
17.750 1.5750 0.05896 0.05500 -0.0054 0.0178 1.0000
18.000 1.5697 0.06284 0.05900 -0.0064 0.0177 1.0000
18.250 1.5617 0.06725 0.06353 -0.0078 0.0176 1.0000
18.500 1.5527 0.07199 0.06840 -0.0096 0.0175 1.0000
18.750 1.5406 0.07737 0.07390 -0.0118 0.0174 1.0000
19.000 1.5253 0.08342 0.08009 -0.0145 0.0173 1.0000
19.250 1.5084 0.09000 0.08681 -0.0176 0.0172 1.0000
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