LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 200,000 Max Cl/Cd: 47.9 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5e-il-200000-n5.txt Download as CSV file: xf-c5e-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5778 0.08970 0.08564 -0.0214 1.0000 0.0280
-9.750 -0.5962 0.08067 0.07664 -0.0281 1.0000 0.0282
-9.500 -0.6317 0.06911 0.06505 -0.0386 1.0000 0.0282
-9.250 -0.7522 0.04192 0.03664 -0.0439 1.0000 0.0294
-9.000 -0.7399 0.04034 0.03497 -0.0430 1.0000 0.0297
-8.750 -0.7248 0.03922 0.03378 -0.0421 1.0000 0.0301
-8.500 -0.7088 0.03824 0.03274 -0.0412 1.0000 0.0307
-8.250 -0.6933 0.03709 0.03150 -0.0402 1.0000 0.0315
-8.000 -0.6842 0.03408 0.02814 -0.0387 1.0000 0.0329
-7.750 -0.6775 0.02993 0.02327 -0.0367 1.0000 0.0344
-7.500 -0.6629 0.02779 0.02078 -0.0353 1.0000 0.0351
-7.250 -0.6450 0.02663 0.01956 -0.0341 1.0000 0.0357
-7.000 -0.6271 0.02556 0.01838 -0.0328 1.0000 0.0362
-6.750 -0.6062 0.02448 0.01717 -0.0320 0.9992 0.0368
-6.500 -0.5721 0.02334 0.01585 -0.0339 0.9945 0.0380
-6.250 -0.5383 0.02213 0.01442 -0.0356 0.9890 0.0393
-6.000 -0.5035 0.02088 0.01293 -0.0374 0.9839 0.0403
-5.750 -0.4701 0.01983 0.01168 -0.0387 0.9773 0.0411
-5.500 -0.4365 0.01875 0.01056 -0.0402 0.9715 0.0420
-5.250 -0.4051 0.01800 0.00980 -0.0412 0.9629 0.0430
-5.000 -0.3717 0.01732 0.00909 -0.0425 0.9559 0.0442
-4.750 -0.3402 0.01673 0.00847 -0.0434 0.9464 0.0459
-4.500 -0.3082 0.01616 0.00783 -0.0443 0.9375 0.0477
-4.250 -0.2765 0.01553 0.00716 -0.0452 0.9283 0.0494
-4.000 -0.2465 0.01497 0.00664 -0.0457 0.9177 0.0511
-3.750 -0.2159 0.01452 0.00618 -0.0463 0.9081 0.0532
-3.500 -0.1866 0.01410 0.00573 -0.0466 0.8974 0.0556
-3.250 -0.1581 0.01371 0.00533 -0.0467 0.8869 0.0587
-3.000 -0.1294 0.01339 0.00501 -0.0468 0.8774 0.0628
-2.750 -0.1019 0.01312 0.00470 -0.0466 0.8669 0.0671
-2.500 -0.0746 0.01281 0.00445 -0.0465 0.8575 0.0729
-2.250 -0.0473 0.01257 0.00421 -0.0463 0.8480 0.0812
-2.000 -0.0200 0.01235 0.00403 -0.0462 0.8389 0.0925
-1.750 0.0073 0.01216 0.00386 -0.0460 0.8301 0.1069
-1.500 0.0345 0.01197 0.00373 -0.0459 0.8210 0.1241
-1.250 0.0619 0.01180 0.00359 -0.0457 0.8128 0.1423
-1.000 0.0892 0.01163 0.00349 -0.0456 0.8038 0.1641
-0.750 0.1164 0.01142 0.00336 -0.0454 0.7955 0.1986
-0.500 0.1385 0.01006 0.00318 -0.0451 0.7852 0.5341
-0.250 0.1626 0.00979 0.00330 -0.0440 0.7753 0.6564
0.000 0.1876 0.00972 0.00338 -0.0429 0.7639 0.7083
0.250 0.2134 0.00972 0.00343 -0.0421 0.7520 0.7361
0.500 0.2396 0.00975 0.00348 -0.0413 0.7413 0.7597
0.750 0.2661 0.00979 0.00352 -0.0406 0.7300 0.7793
1.000 0.2924 0.00982 0.00357 -0.0400 0.7181 0.7970
1.250 0.3185 0.00986 0.00363 -0.0392 0.7071 0.8134
1.500 0.3437 0.00990 0.00368 -0.0382 0.6952 0.8309
1.750 0.3686 0.00993 0.00372 -0.0372 0.6793 0.8469
2.000 0.3928 0.00996 0.00374 -0.0360 0.6573 0.8627
2.250 0.4162 0.01002 0.00372 -0.0345 0.6281 0.8771
2.500 0.4400 0.01010 0.00370 -0.0333 0.5947 0.8883
2.750 0.4650 0.01022 0.00372 -0.0325 0.5653 0.8984
3.000 0.4891 0.01039 0.00376 -0.0315 0.5276 0.9091
3.250 0.5120 0.01069 0.00380 -0.0303 0.4650 0.9198
3.500 0.5328 0.01130 0.00396 -0.0290 0.3685 0.9320
3.750 0.5527 0.01232 0.00434 -0.0281 0.2352 0.9462
4.000 0.5791 0.01303 0.00472 -0.0283 0.1704 0.9610
4.250 0.6098 0.01353 0.00506 -0.0292 0.1385 0.9776
4.500 0.6398 0.01397 0.00540 -0.0301 0.1196 1.0000
4.750 0.6649 0.01436 0.00573 -0.0299 0.1034 1.0000
5.000 0.6897 0.01481 0.00607 -0.0296 0.0908 1.0000
5.250 0.7141 0.01531 0.00649 -0.0292 0.0822 1.0000
5.500 0.7390 0.01575 0.00694 -0.0289 0.0762 1.0000
5.750 0.7632 0.01626 0.00741 -0.0285 0.0716 1.0000
6.000 0.7873 0.01677 0.00792 -0.0280 0.0684 1.0000
6.250 0.8116 0.01726 0.00844 -0.0276 0.0655 1.0000
6.500 0.8356 0.01776 0.00894 -0.0271 0.0629 1.0000
6.750 0.8584 0.01839 0.00951 -0.0265 0.0606 1.0000
7.000 0.8819 0.01894 0.01013 -0.0260 0.0589 1.0000
7.250 0.9050 0.01954 0.01076 -0.0253 0.0573 1.0000
7.500 0.9279 0.02015 0.01139 -0.0247 0.0556 1.0000
7.750 0.9504 0.02076 0.01200 -0.0241 0.0538 1.0000
8.000 0.9713 0.02158 0.01278 -0.0233 0.0519 1.0000
8.250 0.9940 0.02221 0.01350 -0.0227 0.0502 1.0000
8.500 1.0161 0.02288 0.01423 -0.0220 0.0484 1.0000
8.750 1.0375 0.02359 0.01497 -0.0213 0.0469 1.0000
9.000 1.0582 0.02437 0.01578 -0.0205 0.0455 1.0000
9.250 1.0776 0.02547 0.01685 -0.0197 0.0442 1.0000
9.500 1.0985 0.02634 0.01784 -0.0188 0.0432 1.0000
9.750 1.1188 0.02725 0.01888 -0.0180 0.0420 1.0000
10.000 1.1384 0.02820 0.01995 -0.0171 0.0408 1.0000
10.250 1.1571 0.02914 0.02097 -0.0162 0.0396 1.0000
10.500 1.1750 0.03008 0.02196 -0.0152 0.0386 1.0000
10.750 1.1921 0.03117 0.02306 -0.0142 0.0376 1.0000
11.000 1.2082 0.03248 0.02449 -0.0130 0.0367 1.0000
11.250 1.2223 0.03370 0.02594 -0.0116 0.0358 1.0000
11.500 1.2346 0.03506 0.02749 -0.0099 0.0349 1.0000
11.750 1.2454 0.03647 0.02907 -0.0083 0.0342 1.0000
12.000 1.2549 0.03791 0.03066 -0.0066 0.0335 1.0000
12.250 1.2633 0.03939 0.03229 -0.0050 0.0329 1.0000
12.500 1.2708 0.04092 0.03393 -0.0035 0.0324 1.0000
12.750 1.2775 0.04253 0.03564 -0.0021 0.0320 1.0000
13.000 1.2832 0.04430 0.03749 -0.0009 0.0316 1.0000
13.250 1.2876 0.04635 0.03963 0.0002 0.0313 1.0000
13.500 1.2836 0.04918 0.04273 0.0014 0.0309 1.0000
13.750 1.2758 0.05251 0.04637 0.0022 0.0306 1.0000
14.000 1.2649 0.05635 0.05050 0.0025 0.0303 1.0000
14.250 1.2507 0.06076 0.05521 0.0021 0.0301 1.0000
14.500 1.2330 0.06592 0.06064 0.0010 0.0299 1.0000
14.750 1.2108 0.07204 0.06703 -0.0012 0.0298 1.0000
15.000 1.1829 0.07960 0.07486 -0.0048 0.0297 1.0000
15.250 1.1462 0.08955 0.08510 -0.0106 0.0297 1.0000
15.500 1.0371 0.11897 0.11501 -0.0308 0.0303 1.0000
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