LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Reynolds number: 200,000 Max Cl/Cd: 66.65 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5d-il-200000.txt Download as CSV file: xf-c5d-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5256 0.08754 0.08378 -0.0404 1.0000 0.0698
-9.000 -0.5415 0.08328 0.07959 -0.0415 1.0000 0.0710
-8.750 -0.5719 0.07838 0.07475 -0.0431 1.0000 0.0713
-8.500 -0.6063 0.07532 0.07170 -0.0404 1.0000 0.0714
-8.250 -0.6316 0.07167 0.06801 -0.0384 1.0000 0.0724
-8.000 -0.6892 0.06893 0.06468 -0.0344 1.0000 0.0759
-7.750 -0.6983 0.06256 0.05826 -0.0329 1.0000 0.0770
-7.500 -0.6896 0.05938 0.05517 -0.0315 1.0000 0.0779
-7.250 -0.6822 0.05700 0.05281 -0.0297 1.0000 0.0789
-7.000 -0.6760 0.05469 0.05045 -0.0279 1.0000 0.0802
-6.750 -0.7004 0.03747 0.03108 -0.0220 1.0000 0.0442
-6.500 -0.6862 0.03331 0.02677 -0.0210 1.0000 0.0427
-6.250 -0.6699 0.03043 0.02354 -0.0196 1.0000 0.0418
-6.000 -0.6503 0.02799 0.02074 -0.0184 1.0000 0.0413
-5.750 -0.6289 0.02604 0.01846 -0.0174 1.0000 0.0412
-5.500 -0.6065 0.02448 0.01661 -0.0165 1.0000 0.0417
-5.250 -0.5836 0.02322 0.01512 -0.0156 1.0000 0.0425
-5.000 -0.5605 0.02226 0.01395 -0.0148 1.0000 0.0436
-4.750 -0.5369 0.02077 0.01238 -0.0142 1.0000 0.0455
-4.500 -0.5143 0.02006 0.01171 -0.0136 1.0000 0.0487
-4.250 -0.4913 0.01956 0.01114 -0.0129 1.0000 0.0526
-4.000 -0.4650 0.01858 0.01021 -0.0130 0.9994 0.0574
-3.750 -0.4284 0.01818 0.00976 -0.0150 0.9966 0.0646
-3.500 -0.3915 0.01771 0.00935 -0.0173 0.9941 0.0750
-3.250 -0.3572 0.01713 0.00885 -0.0190 0.9905 0.0874
-3.000 -0.3207 0.01665 0.00852 -0.0212 0.9873 0.1126
-2.750 -0.2828 0.01587 0.00819 -0.0240 0.9851 0.1931
-2.500 -0.2514 0.01479 0.00795 -0.0258 0.9815 0.3584
-2.250 -0.2215 0.01377 0.00818 -0.0266 0.9785 0.6469
-2.000 -0.1873 0.01381 0.00847 -0.0274 0.9752 0.7399
-1.750 -0.1596 0.01387 0.00864 -0.0270 0.9698 0.7897
-1.500 -0.1295 0.01400 0.00883 -0.0269 0.9650 0.8321
-1.250 -0.0970 0.01420 0.00908 -0.0272 0.9616 0.8678
-1.000 -0.0774 0.01425 0.00916 -0.0249 0.9539 0.8978
-0.750 -0.0447 0.01441 0.00932 -0.0252 0.9500 0.9229
-0.500 -0.0132 0.01455 0.00944 -0.0255 0.9447 0.9466
-0.250 0.0305 0.01473 0.00958 -0.0286 0.9406 0.9650
0.000 0.0861 0.01495 0.00976 -0.0343 0.9389 0.9793
0.250 0.1454 0.01512 0.00989 -0.0410 0.9377 0.9876
0.500 0.2081 0.01513 0.00988 -0.0482 0.9360 0.9939
0.750 0.2699 0.01495 0.00969 -0.0551 0.9339 0.9963
1.000 0.3078 0.01478 0.00953 -0.0576 0.9249 1.0000
1.250 0.3635 0.01436 0.00913 -0.0630 0.9208 1.0000
1.500 0.4171 0.01359 0.00839 -0.0675 0.9105 1.0000
1.750 0.4752 0.01266 0.00749 -0.0726 0.9038 1.0000
2.000 0.5033 0.01210 0.00695 -0.0722 0.8902 1.0000
2.250 0.5324 0.01149 0.00637 -0.0718 0.8750 1.0000
2.500 0.5599 0.01098 0.00587 -0.0711 0.8584 1.0000
2.750 0.5798 0.01069 0.00559 -0.0692 0.8378 1.0000
3.000 0.6037 0.01040 0.00530 -0.0679 0.8142 1.0000
3.250 0.6256 0.01021 0.00509 -0.0664 0.7863 1.0000
3.500 0.6500 0.01007 0.00486 -0.0652 0.7502 1.0000
3.750 0.6725 0.01009 0.00468 -0.0636 0.6971 1.0000
4.000 0.6902 0.01037 0.00465 -0.0612 0.6291 1.0000
4.250 0.7003 0.01091 0.00474 -0.0574 0.5395 1.0000
4.500 0.7027 0.01179 0.00499 -0.0523 0.4207 1.0000
4.750 0.7043 0.01293 0.00544 -0.0475 0.2969 1.0000
5.000 0.7112 0.01409 0.00598 -0.0439 0.1951 1.0000
5.250 0.7236 0.01508 0.00663 -0.0412 0.1424 1.0000
5.500 0.7391 0.01592 0.00728 -0.0390 0.1182 1.0000
5.750 0.7566 0.01668 0.00795 -0.0371 0.1065 1.0000
6.250 0.7953 0.01810 0.00932 -0.0341 0.0940 1.0000
6.500 0.8164 0.01878 0.01000 -0.0330 0.0899 1.0000
6.750 0.8375 0.01978 0.01090 -0.0319 0.0860 1.0000
7.000 0.8609 0.02060 0.01177 -0.0312 0.0830 1.0000
7.250 0.8849 0.02136 0.01261 -0.0305 0.0802 1.0000
7.500 0.9088 0.02215 0.01343 -0.0299 0.0772 1.0000
7.750 0.9332 0.02314 0.01438 -0.0296 0.0741 1.0000
8.000 0.9598 0.02460 0.01592 -0.0296 0.0713 1.0000
8.250 0.9827 0.02535 0.01684 -0.0287 0.0686 1.0000
8.500 1.0056 0.02622 0.01780 -0.0280 0.0657 1.0000
8.750 1.0285 0.02719 0.01875 -0.0275 0.0629 1.0000
9.000 1.0525 0.02908 0.02079 -0.0272 0.0603 1.0000
9.250 1.0724 0.03023 0.02220 -0.0259 0.0578 1.0000
9.500 1.0918 0.03126 0.02335 -0.0247 0.0550 1.0000
9.750 1.1122 0.03252 0.02458 -0.0240 0.0524 1.0000
10.000 1.1273 0.03509 0.02748 -0.0224 0.0502 1.0000
10.250 1.1391 0.03667 0.02943 -0.0199 0.0479 1.0000
10.500 1.1528 0.03811 0.03105 -0.0181 0.0457 1.0000
10.750 1.1668 0.03961 0.03263 -0.0165 0.0440 1.0000
11.000 1.1778 0.04285 0.03598 -0.0151 0.0425 1.0000
11.250 1.1721 0.04603 0.03962 -0.0110 0.0415 1.0000
11.500 1.1643 0.04848 0.04249 -0.0066 0.0406 1.0000
11.750 1.1507 0.05123 0.04559 -0.0018 0.0398 1.0000
12.000 1.1341 0.05429 0.04896 0.0026 0.0391 1.0000
12.250 1.1144 0.05775 0.05270 0.0064 0.0387 1.0000
12.500 1.0907 0.06184 0.05707 0.0093 0.0385 1.0000
12.750 1.0619 0.06684 0.06234 0.0110 0.0386 1.0000
13.000 1.0288 0.07296 0.06871 0.0109 0.0389 1.0000
13.250 0.9930 0.08053 0.07649 0.0085 0.0396 1.0000
13.500 0.9579 0.08945 0.08558 0.0037 0.0404 1.0000
13.750 0.9261 0.09952 0.09575 -0.0025 0.0413 1.0000
14.000 0.9017 0.10941 0.10567 -0.0079 0.0419 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il)