LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Reynolds number: 100,000 Max Cl/Cd: 48.12 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5d-il-100000.txt Download as CSV file: xf-c5d-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4822 0.10913 0.10361 -0.0322 1.0000 0.1239
-9.750 -0.4892 0.10587 0.10040 -0.0334 1.0000 0.1282
-9.500 -0.5506 0.10192 0.09668 -0.0413 1.0000 0.1314
-9.250 -0.5239 0.09768 0.09242 -0.0374 1.0000 0.1333
-9.000 -0.5071 0.09507 0.08980 -0.0346 1.0000 0.1359
-8.750 -0.5080 0.09219 0.08697 -0.0337 1.0000 0.1392
-8.500 -0.5285 0.08879 0.08367 -0.0344 1.0000 0.1434
-8.250 -0.5945 0.08531 0.08030 -0.0356 1.0000 0.1458
-8.000 -0.6275 0.08122 0.07620 -0.0347 1.0000 0.1477
-7.750 -0.5995 0.07817 0.07325 -0.0319 1.0000 0.1502
-7.500 -0.6000 0.07550 0.07060 -0.0298 1.0000 0.1533
-7.250 -0.6539 0.07258 0.06734 -0.0294 1.0000 0.1624
-7.000 -0.6346 0.06843 0.06338 -0.0275 1.0000 0.1645
-6.750 -0.6271 0.06571 0.06070 -0.0254 1.0000 0.1680
-6.500 -0.6631 0.04554 0.03814 -0.0257 1.0000 0.0764
-6.250 -0.6488 0.04229 0.03472 -0.0243 1.0000 0.0751
-6.000 -0.6347 0.03917 0.03126 -0.0228 1.0000 0.0747
-5.750 -0.6184 0.03632 0.02804 -0.0214 1.0000 0.0746
-5.500 -0.5997 0.03368 0.02500 -0.0201 1.0000 0.0744
-5.250 -0.5789 0.03127 0.02220 -0.0190 1.0000 0.0745
-5.000 -0.5562 0.02931 0.01982 -0.0180 1.0000 0.0753
-4.750 -0.5325 0.02724 0.01755 -0.0174 1.0000 0.0781
-4.500 -0.5096 0.02618 0.01646 -0.0168 1.0000 0.0832
-4.250 -0.4850 0.02503 0.01504 -0.0159 1.0000 0.0880
-4.000 -0.4613 0.02384 0.01393 -0.0154 1.0000 0.0950
-3.750 -0.4369 0.02301 0.01292 -0.0146 1.0000 0.1029
-3.500 -0.4134 0.02210 0.01212 -0.0140 1.0000 0.1140
-3.250 -0.3895 0.02117 0.01130 -0.0134 1.0000 0.1279
-3.000 -0.3658 0.02022 0.01053 -0.0129 1.0000 0.1512
-2.750 -0.3414 0.01895 0.00975 -0.0127 1.0000 0.2127
-2.500 -0.3193 0.01645 0.00953 -0.0120 1.0000 0.6063
-2.250 -0.3074 0.01643 0.01002 -0.0070 1.0000 0.7726
-2.000 -0.2954 0.01662 0.01029 -0.0024 1.0000 0.8431
-1.750 -0.2813 0.01689 0.01060 0.0019 1.0000 0.9060
-1.500 -0.2145 0.01778 0.01130 -0.0039 1.0000 0.9781
-1.250 -0.1388 0.01834 0.01158 -0.0138 1.0000 1.0000
-1.000 -0.1421 0.01800 0.01118 -0.0098 1.0000 1.0000
-0.750 -0.1406 0.01778 0.01088 -0.0065 1.0000 1.0000
-0.500 -0.1301 0.01777 0.01075 -0.0047 1.0000 1.0000
-0.250 -0.1139 0.01791 0.01078 -0.0038 1.0000 1.0000
0.000 -0.0953 0.01815 0.01091 -0.0033 1.0000 1.0000
0.250 -0.0755 0.01846 0.01113 -0.0030 1.0000 1.0000
0.500 -0.0376 0.01904 0.01161 -0.0061 0.9952 1.0000
0.750 0.0061 0.01965 0.01215 -0.0103 0.9872 1.0000
1.000 0.0487 0.02023 0.01267 -0.0141 0.9783 1.0000
1.250 0.0908 0.02076 0.01316 -0.0177 0.9687 1.0000
1.500 0.1340 0.02129 0.01366 -0.0215 0.9598 1.0000
1.750 0.1742 0.02172 0.01409 -0.0246 0.9501 1.0000
2.000 0.2092 0.02208 0.01447 -0.0267 0.9392 1.0000
2.250 0.2505 0.02239 0.01481 -0.0297 0.9281 1.0000
2.500 0.2986 0.02246 0.01494 -0.0335 0.9149 1.0000
2.750 0.3498 0.02231 0.01487 -0.0376 0.9020 1.0000
3.000 0.4013 0.02191 0.01457 -0.0414 0.8885 1.0000
3.250 0.4456 0.02124 0.01402 -0.0434 0.8705 1.0000
3.500 0.4948 0.02026 0.01317 -0.0458 0.8531 1.0000
3.750 0.5479 0.01889 0.01198 -0.0483 0.8352 1.0000
4.000 0.5987 0.01734 0.01059 -0.0501 0.8143 1.0000
4.250 0.6332 0.01631 0.00967 -0.0493 0.7855 1.0000
4.500 0.6665 0.01544 0.00887 -0.0483 0.7435 1.0000
4.750 0.7043 0.01481 0.00813 -0.0482 0.6739 1.0000
5.000 0.7280 0.01513 0.00776 -0.0457 0.5223 1.0000
5.250 0.7241 0.01703 0.00825 -0.0395 0.3069 1.0000
5.500 0.7284 0.01888 0.00924 -0.0355 0.2084 1.0000
5.750 0.7411 0.02032 0.01027 -0.0329 0.1727 1.0000
6.000 0.7600 0.02162 0.01133 -0.0313 0.1538 1.0000
6.250 0.7833 0.02268 0.01231 -0.0304 0.1419 1.0000
6.500 0.8091 0.02379 0.01343 -0.0300 0.1330 1.0000
6.750 0.8371 0.02520 0.01466 -0.0302 0.1256 1.0000
7.000 0.8647 0.02640 0.01602 -0.0300 0.1203 1.0000
7.250 0.8927 0.02778 0.01743 -0.0300 0.1154 1.0000
7.500 0.9214 0.02965 0.01932 -0.0303 0.1107 1.0000
7.750 0.9457 0.03113 0.02110 -0.0295 0.1071 1.0000
8.000 0.9699 0.03270 0.02283 -0.0289 0.1031 1.0000
8.250 0.9953 0.03509 0.02520 -0.0290 0.0988 1.0000
8.500 1.0122 0.03700 0.02759 -0.0270 0.0964 1.0000
8.750 1.0274 0.03901 0.03004 -0.0249 0.0931 1.0000
9.000 1.0430 0.04130 0.03264 -0.0230 0.0902 1.0000
9.250 1.0631 0.04351 0.03486 -0.0224 0.0868 1.0000
9.500 1.0716 0.04722 0.03889 -0.0202 0.0844 1.0000
9.750 1.0734 0.05030 0.04252 -0.0166 0.0834 1.0000
10.000 1.0722 0.05397 0.04665 -0.0131 0.0828 1.0000
10.250 1.0661 0.05778 0.05090 -0.0094 0.0823 1.0000
10.500 1.0551 0.06176 0.05526 -0.0056 0.0820 1.0000
10.750 1.0400 0.06592 0.05972 -0.0020 0.0822 1.0000
11.000 1.0221 0.07004 0.06408 0.0015 0.0828 1.0000
11.250 1.0079 0.07450 0.06868 0.0040 0.0837 1.0000
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Polar data table (+)
Polar graphs
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