LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 50,000 Max Cl/Cd: 31.65 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5c-il-50000.txt Download as CSV file: xf-c5c-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4687 0.09239 0.08528 -0.0069 1.0000 0.4064
-7.250 -0.4745 0.09002 0.08299 -0.0043 1.0000 0.4215
-7.000 -0.6659 0.06767 0.06015 -0.0292 1.0000 0.1685
-6.750 -0.6591 0.06154 0.05379 -0.0287 1.0000 0.1518
-6.500 -0.6524 0.05730 0.04940 -0.0275 1.0000 0.1470
-6.250 -0.6526 0.05212 0.04333 -0.0262 1.0000 0.1380
-6.000 -0.6405 0.04858 0.03948 -0.0249 1.0000 0.1373
-5.750 -0.6263 0.04521 0.03572 -0.0236 1.0000 0.1365
-5.500 -0.6095 0.04200 0.03209 -0.0224 1.0000 0.1355
-5.250 -0.5906 0.03918 0.02876 -0.0212 1.0000 0.1363
-5.000 -0.5701 0.03670 0.02577 -0.0201 1.0000 0.1399
-4.750 -0.5478 0.03462 0.02363 -0.0193 1.0000 0.1453
-4.500 -0.5233 0.03263 0.02124 -0.0184 1.0000 0.1501
-4.250 -0.4989 0.03089 0.01936 -0.0176 1.0000 0.1594
-4.000 -0.4732 0.02934 0.01766 -0.0169 1.0000 0.1720
-3.750 -0.4467 0.02781 0.01614 -0.0161 1.0000 0.1892
-3.500 -0.4208 0.02632 0.01484 -0.0153 1.0000 0.2225
-3.250 -0.3960 0.02405 0.01331 -0.0145 1.0000 0.3150
-3.000 -0.3929 0.02144 0.01340 -0.0065 1.0000 0.7006
-2.750 -0.1534 0.02516 0.01592 -0.0336 1.0000 1.0000
-2.500 -0.1543 0.02457 0.01519 -0.0305 1.0000 1.0000
-2.250 -0.1546 0.02405 0.01455 -0.0272 1.0000 1.0000
-2.000 -0.1545 0.02358 0.01396 -0.0238 1.0000 1.0000
-1.750 -0.1538 0.02317 0.01344 -0.0204 1.0000 1.0000
-1.500 -0.1521 0.02282 0.01297 -0.0170 1.0000 1.0000
-1.250 -0.1486 0.02253 0.01256 -0.0138 1.0000 1.0000
-1.000 -0.1427 0.02232 0.01222 -0.0109 1.0000 1.0000
-0.750 -0.1335 0.02222 0.01197 -0.0085 1.0000 1.0000
-0.500 -0.1210 0.02221 0.01180 -0.0067 1.0000 1.0000
-0.250 -0.1060 0.02228 0.01174 -0.0053 1.0000 1.0000
0.000 -0.0894 0.02243 0.01176 -0.0042 1.0000 1.0000
0.250 -0.0716 0.02263 0.01185 -0.0032 1.0000 1.0000
0.500 -0.0531 0.02289 0.01200 -0.0025 1.0000 1.0000
0.750 -0.0342 0.02320 0.01222 -0.0018 1.0000 1.0000
1.000 -0.0150 0.02355 0.01250 -0.0012 1.0000 1.0000
1.250 0.0044 0.02394 0.01283 -0.0007 1.0000 1.0000
1.500 0.0239 0.02439 0.01323 -0.0003 1.0000 1.0000
1.750 0.0434 0.02487 0.01369 0.0001 1.0000 1.0000
2.000 0.0627 0.02541 0.01421 0.0004 1.0000 1.0000
2.250 0.0820 0.02599 0.01479 0.0007 1.0000 1.0000
2.500 0.1011 0.02662 0.01543 0.0010 1.0000 1.0000
2.750 0.1199 0.02731 0.01614 0.0011 1.0000 1.0000
3.000 0.1384 0.02806 0.01693 0.0013 1.0000 1.0000
3.250 0.1565 0.02886 0.01779 0.0014 1.0000 1.0000
3.500 0.1743 0.02974 0.01873 0.0014 1.0000 1.0000
3.750 0.1915 0.03070 0.01976 0.0013 1.0000 1.0000
4.000 0.2082 0.03174 0.02090 0.0012 1.0000 1.0000
4.250 0.2842 0.03403 0.02343 -0.0099 0.9701 1.0000
4.500 0.3551 0.03546 0.02516 -0.0188 0.9348 1.0000
4.750 0.4425 0.03547 0.02555 -0.0281 0.8886 1.0000
5.000 0.5232 0.03380 0.02433 -0.0340 0.8434 1.0000
5.250 0.5750 0.03221 0.02315 -0.0351 0.8052 1.0000
5.500 0.6571 0.02717 0.01874 -0.0359 0.7514 1.0000
5.750 0.7201 0.02275 0.01321 -0.0297 0.4526 1.0000
6.000 0.7279 0.02557 0.01444 -0.0256 0.3131 1.0000
6.250 0.7642 0.02793 0.01617 -0.0268 0.2516 1.0000
6.500 0.8029 0.02989 0.01796 -0.0283 0.2187 1.0000
6.750 0.8418 0.03198 0.02007 -0.0298 0.2013 1.0000
7.000 0.8739 0.03409 0.02221 -0.0304 0.1886 1.0000
7.250 0.9018 0.03617 0.02439 -0.0302 0.1784 1.0000
7.500 0.9263 0.03867 0.02727 -0.0294 0.1730 1.0000
7.750 0.9469 0.04095 0.02988 -0.0281 0.1665 1.0000
8.000 0.9691 0.04377 0.03278 -0.0274 0.1607 1.0000
8.250 0.9812 0.04664 0.03622 -0.0248 0.1586 1.0000
8.500 0.9900 0.04962 0.03970 -0.0221 0.1557 1.0000
8.750 0.9979 0.05268 0.04317 -0.0195 0.1526 1.0000
9.000 1.0018 0.05630 0.04721 -0.0167 0.1521 1.0000
9.250 0.9982 0.06036 0.05172 -0.0135 0.1530 1.0000
9.500 0.9892 0.06465 0.05640 -0.0102 0.1543 1.0000
9.750 0.9764 0.06914 0.06121 -0.0072 0.1560 1.0000
10.000 0.9622 0.07378 0.06609 -0.0046 0.1579 1.0000
10.250 0.9507 0.07860 0.07105 -0.0028 0.1597 1.0000
10.500 0.8791 0.08602 0.07868 -0.0008 0.1723 1.0000
10.750 0.8769 0.09193 0.08466 -0.0014 0.1776 1.0000
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Polar data table (+)
Polar graphs
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