LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Reynolds number: 100,000 Max Cl/Cd: 41.51 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5a-il-100000.txt Download as CSV file: xf-c5a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL0 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 -0.5812 0.09676 0.09154 -0.0318 1.0000 0.1838
-9.750 -0.6088 0.09145 0.08634 -0.0337 1.0000 0.1937
-9.500 -0.6090 0.08777 0.08269 -0.0330 1.0000 0.1967
-9.250 -0.6433 0.08260 0.07765 -0.0342 1.0000 0.2086
-9.000 -0.8604 0.05969 0.05346 -0.0293 1.0000 0.0947
-8.750 -0.8721 0.05356 0.04658 -0.0243 1.0000 0.0773
-8.500 -0.8689 0.04996 0.04276 -0.0215 1.0000 0.0754
-8.250 -0.8658 0.04630 0.03874 -0.0184 1.0000 0.0727
-8.000 -0.8659 0.04306 0.03451 -0.0136 1.0000 0.0677
-7.750 -0.8501 0.04059 0.03177 -0.0117 1.0000 0.0665
-7.500 -0.8340 0.03771 0.02862 -0.0100 1.0000 0.0658
-7.250 -0.8162 0.03531 0.02594 -0.0083 1.0000 0.0654
-7.000 -0.7965 0.03323 0.02360 -0.0069 1.0000 0.0654
-6.750 -0.7753 0.03143 0.02156 -0.0055 1.0000 0.0657
-6.500 -0.7534 0.02998 0.01989 -0.0042 1.0000 0.0667
-6.250 -0.7302 0.02806 0.01800 -0.0035 1.0000 0.0693
-6.000 -0.7090 0.02683 0.01681 -0.0024 1.0000 0.0726
-5.750 -0.6878 0.02570 0.01566 -0.0011 1.0000 0.0757
-5.500 -0.6677 0.02471 0.01460 0.0004 1.0000 0.0790
-5.250 -0.6510 0.02345 0.01349 0.0021 1.0000 0.0846
-5.000 -0.6335 0.02253 0.01260 0.0037 1.0000 0.0939
-4.750 -0.6159 0.02153 0.01172 0.0053 1.0000 0.1093
-4.500 -0.6034 0.01892 0.01015 0.0068 1.0000 0.2291
-4.250 -0.5973 0.01706 0.01039 0.0112 1.0000 0.6045
-4.000 -0.5799 0.01748 0.01085 0.0143 1.0000 0.6661
-3.750 -0.5628 0.01801 0.01136 0.0175 1.0000 0.7051
-3.500 -0.5480 0.01873 0.01209 0.0217 1.0000 0.7379
-3.250 -0.5362 0.01965 0.01304 0.0270 1.0000 0.7668
-3.000 -0.5236 0.02032 0.01369 0.0317 1.0000 0.7914
-2.750 -0.5089 0.02075 0.01406 0.0355 1.0000 0.8094
-2.500 -0.4916 0.02087 0.01409 0.0379 1.0000 0.8242
-2.250 -0.4740 0.02091 0.01403 0.0400 1.0000 0.8386
-2.000 -0.4573 0.02099 0.01404 0.0424 1.0000 0.8537
-1.750 -0.4416 0.02111 0.01411 0.0452 1.0000 0.8697
-1.500 -0.4246 0.02119 0.01414 0.0477 1.0000 0.8854
-1.250 -0.4042 0.02124 0.01411 0.0491 1.0000 0.8988
-1.000 -0.3800 0.02129 0.01410 0.0496 1.0000 0.9109
-0.750 -0.3534 0.02135 0.01410 0.0493 1.0000 0.9230
-0.500 -0.3248 0.02142 0.01410 0.0483 1.0000 0.9350
-0.250 -0.2924 0.02157 0.01420 0.0464 1.0000 0.9459
0.000 -0.2508 0.02187 0.01445 0.0426 1.0000 0.9539
0.250 -0.2118 0.02216 0.01469 0.0391 1.0000 0.9632
0.500 -0.1658 0.02257 0.01508 0.0341 1.0000 0.9707
0.750 -0.1196 0.02300 0.01549 0.0289 1.0000 0.9777
1.000 -0.0632 0.02354 0.01603 0.0217 0.9954 0.9836
1.250 -0.0004 0.02405 0.01656 0.0133 0.9873 0.9872
1.500 0.0631 0.02445 0.01701 0.0050 0.9777 0.9909
1.750 0.1238 0.02473 0.01735 -0.0028 0.9677 0.9949
2.000 0.1851 0.02489 0.01760 -0.0105 0.9572 0.9986
2.250 0.2416 0.02481 0.01761 -0.0169 0.9441 1.0000
2.500 0.3026 0.02433 0.01725 -0.0235 0.9276 1.0000
2.750 0.3656 0.02356 0.01664 -0.0300 0.9113 1.0000
3.000 0.4232 0.02270 0.01594 -0.0353 0.8960 1.0000
3.250 0.5013 0.02102 0.01449 -0.0432 0.8785 1.0000
3.500 0.5596 0.01918 0.01285 -0.0469 0.8518 1.0000
3.750 0.6003 0.01791 0.01171 -0.0478 0.8199 1.0000
4.000 0.6377 0.01690 0.01075 -0.0482 0.7712 1.0000
4.250 0.6741 0.01624 0.00990 -0.0482 0.6790 1.0000
4.500 0.6917 0.01673 0.00947 -0.0450 0.4994 1.0000
4.750 0.6843 0.01845 0.00984 -0.0387 0.2901 1.0000
5.000 0.6838 0.01986 0.01055 -0.0341 0.2075 1.0000
5.250 0.6875 0.02090 0.01128 -0.0300 0.1748 1.0000
5.500 0.6950 0.02171 0.01195 -0.0266 0.1566 1.0000
5.750 0.7055 0.02249 0.01264 -0.0237 0.1453 1.0000
6.000 0.7210 0.02353 0.01346 -0.0219 0.1371 1.0000
6.250 0.7369 0.02425 0.01429 -0.0197 0.1305 1.0000
6.500 0.7567 0.02533 0.01524 -0.0186 0.1240 1.0000
6.750 0.7754 0.02632 0.01635 -0.0170 0.1190 1.0000
7.000 0.7955 0.02739 0.01753 -0.0157 0.1148 1.0000
7.250 0.8176 0.02872 0.01880 -0.0150 0.1104 1.0000
7.500 0.8373 0.03014 0.02042 -0.0136 0.1065 1.0000
7.750 0.8571 0.03157 0.02211 -0.0121 0.1032 1.0000
8.000 0.8783 0.03298 0.02362 -0.0112 0.0993 1.0000
8.250 0.9008 0.03533 0.02597 -0.0109 0.0957 1.0000
8.500 0.9149 0.03717 0.02832 -0.0084 0.0936 1.0000
8.750 0.9278 0.03929 0.03088 -0.0060 0.0907 1.0000
9.000 0.9409 0.04157 0.03348 -0.0039 0.0882 1.0000
9.250 0.9528 0.04425 0.03646 -0.0018 0.0867 1.0000
9.500 0.9714 0.04687 0.03905 -0.0014 0.0839 1.0000
9.750 0.9738 0.05083 0.04335 0.0014 0.0825 1.0000
10.000 0.9717 0.05418 0.04716 0.0050 0.0821 1.0000
10.250 0.9709 0.05846 0.05176 0.0077 0.0824 1.0000
10.500 0.9726 0.06328 0.05681 0.0097 0.0830 1.0000
10.750 0.8897 0.06898 0.06349 0.0201 0.0916 1.0000
11.000 0.8759 0.07366 0.06828 0.0220 0.0939 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED C-5A BL0 AIRFOIL (c5a-il)