LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 200,000 Max Cl/Cd: 64.91 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5b-il-200000.txt Download as CSV file: xf-c5b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL488.2 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4460 0.09132 0.08781 -0.0379 1.0000 0.0774
-9.750 -0.5882 0.08380 0.08015 -0.0479 1.0000 0.0741
-9.500 -0.6084 0.07942 0.07578 -0.0486 1.0000 0.0746
-9.250 -0.6472 0.07549 0.07186 -0.0471 1.0000 0.0745
-9.000 -0.6775 0.07298 0.06933 -0.0430 1.0000 0.0747
-8.750 -0.6912 0.07037 0.06670 -0.0401 1.0000 0.0755
-8.500 -0.7037 0.06766 0.06394 -0.0373 1.0000 0.0766
-8.250 -0.7155 0.06478 0.06098 -0.0346 1.0000 0.0782
-8.000 -0.7290 0.06163 0.05764 -0.0317 1.0000 0.0809
-7.250 -0.7658 0.03918 0.03309 -0.0201 1.0000 0.0484
-7.000 -0.7547 0.03565 0.02929 -0.0183 1.0000 0.0468
-6.750 -0.7406 0.03280 0.02608 -0.0164 1.0000 0.0460
-6.500 -0.7234 0.03016 0.02303 -0.0149 1.0000 0.0450
-6.250 -0.7032 0.02766 0.02009 -0.0135 1.0000 0.0438
-6.000 -0.6815 0.02584 0.01794 -0.0124 1.0000 0.0434
-5.750 -0.6591 0.02444 0.01635 -0.0115 1.0000 0.0436
-5.500 -0.6366 0.02326 0.01503 -0.0106 1.0000 0.0442
-5.250 -0.6139 0.02224 0.01391 -0.0098 1.0000 0.0452
-5.000 -0.5912 0.02134 0.01293 -0.0089 1.0000 0.0466
-4.750 -0.5685 0.02057 0.01207 -0.0080 1.0000 0.0484
-4.500 -0.5459 0.01958 0.01105 -0.0073 1.0000 0.0507
-4.250 -0.5237 0.01886 0.01039 -0.0067 1.0000 0.0548
-4.000 -0.5010 0.01844 0.00993 -0.0060 1.0000 0.0595
-3.750 -0.4749 0.01771 0.00927 -0.0062 0.9994 0.0669
-3.500 -0.4389 0.01718 0.00878 -0.0083 0.9967 0.0796
-3.250 -0.4027 0.01645 0.00838 -0.0105 0.9945 0.1309
-3.000 -0.3705 0.01498 0.00801 -0.0128 0.9924 0.3399
-2.750 -0.3396 0.01400 0.00812 -0.0141 0.9900 0.5747
-2.500 -0.3064 0.01398 0.00847 -0.0151 0.9869 0.6807
-2.250 -0.2730 0.01416 0.00875 -0.0160 0.9834 0.7385
-2.000 -0.2445 0.01430 0.00898 -0.0158 0.9785 0.7822
-1.750 -0.2125 0.01457 0.00933 -0.0161 0.9750 0.8216
-1.500 -0.1876 0.01471 0.00948 -0.0151 0.9693 0.8488
-1.250 -0.1559 0.01488 0.00963 -0.0157 0.9649 0.8671
-1.000 -0.1252 0.01506 0.00980 -0.0160 0.9606 0.8847
-0.750 -0.1003 0.01513 0.00987 -0.0151 0.9542 0.9022
-0.500 -0.0661 0.01530 0.01002 -0.0161 0.9505 0.9196
-0.250 -0.0397 0.01544 0.01016 -0.0153 0.9442 0.9419
0.000 0.0010 0.01564 0.01034 -0.0177 0.9400 0.9608
0.250 0.0524 0.01583 0.01050 -0.0226 0.9375 0.9710
0.500 0.1084 0.01599 0.01064 -0.0286 0.9357 0.9772
0.750 0.1570 0.01609 0.01073 -0.0331 0.9311 0.9843
1.000 0.2073 0.01608 0.01073 -0.0381 0.9262 0.9880
1.250 0.2657 0.01578 0.01045 -0.0442 0.9218 0.9893
1.500 0.3194 0.01526 0.00995 -0.0490 0.9124 0.9910
1.750 0.3802 0.01459 0.00932 -0.0551 0.9071 0.9905
2.000 0.4330 0.01389 0.00868 -0.0595 0.8982 0.9920
2.250 0.4895 0.01288 0.00771 -0.0642 0.8897 0.9920
2.500 0.5340 0.01223 0.00713 -0.0670 0.8755 0.9955
2.750 0.5784 0.01166 0.00663 -0.0699 0.8597 0.9992
3.000 0.6009 0.01127 0.00627 -0.0686 0.8360 1.0000
3.250 0.6275 0.01087 0.00587 -0.0679 0.8088 1.0000
3.500 0.6543 0.01058 0.00551 -0.0672 0.7701 1.0000
3.750 0.6803 0.01048 0.00519 -0.0663 0.7066 1.0000
4.000 0.6962 0.01078 0.00506 -0.0635 0.6167 1.0000
4.250 0.7003 0.01140 0.00515 -0.0588 0.5124 1.0000
4.500 0.6972 0.01224 0.00539 -0.0529 0.4001 1.0000
4.750 0.6954 0.01319 0.00575 -0.0474 0.2939 1.0000
5.000 0.6995 0.01411 0.00617 -0.0432 0.2084 1.0000
5.250 0.7082 0.01499 0.00669 -0.0397 0.1600 1.0000
5.500 0.7203 0.01582 0.00730 -0.0369 0.1293 1.0000
5.750 0.7353 0.01659 0.00796 -0.0346 0.1133 1.0000
6.000 0.7528 0.01726 0.00857 -0.0327 0.1038 1.0000
6.250 0.7718 0.01797 0.00928 -0.0312 0.0978 1.0000
6.500 0.7924 0.01858 0.00990 -0.0299 0.0926 1.0000
6.750 0.8126 0.01960 0.01081 -0.0287 0.0877 1.0000
7.000 0.8352 0.02008 0.01140 -0.0278 0.0837 1.0000
7.250 0.8570 0.02065 0.01197 -0.0268 0.0792 1.0000
7.500 0.8806 0.02184 0.01309 -0.0264 0.0750 1.0000
7.750 0.9036 0.02246 0.01385 -0.0256 0.0719 1.0000
8.000 0.9271 0.02328 0.01473 -0.0249 0.0687 1.0000
8.250 0.9508 0.02425 0.01569 -0.0245 0.0656 1.0000
8.500 0.9772 0.02587 0.01741 -0.0245 0.0625 1.0000
8.750 0.9995 0.02686 0.01858 -0.0236 0.0596 1.0000
9.000 1.0221 0.02803 0.01985 -0.0229 0.0571 1.0000
9.250 1.0456 0.02950 0.02137 -0.0225 0.0549 1.0000
9.500 1.0697 0.03274 0.02483 -0.0225 0.0530 1.0000
9.750 1.0855 0.03438 0.02682 -0.0205 0.0520 1.0000
10.000 1.0989 0.03610 0.02889 -0.0182 0.0502 1.0000
10.250 1.1125 0.03746 0.03045 -0.0163 0.0479 1.0000
10.500 1.1288 0.03843 0.03144 -0.0150 0.0458 1.0000
10.750 1.1417 0.04147 0.03455 -0.0139 0.0440 1.0000
11.000 1.1394 0.04398 0.03750 -0.0099 0.0428 1.0000
11.250 1.1363 0.04604 0.03997 -0.0058 0.0416 1.0000
11.500 1.1284 0.04873 0.04301 -0.0015 0.0407 1.0000
11.750 1.1154 0.05157 0.04616 0.0032 0.0400 1.0000
12.000 1.0997 0.05462 0.04949 0.0074 0.0394 1.0000
12.250 1.0816 0.05791 0.05304 0.0110 0.0389 1.0000
12.500 1.0591 0.06183 0.05720 0.0139 0.0387 1.0000
12.750 1.0261 0.06727 0.06293 0.0157 0.0390 1.0000
13.000 0.9841 0.07469 0.07063 0.0152 0.0399 1.0000
13.250 0.9446 0.08319 0.07934 0.0117 0.0408 1.0000
13.500 0.9078 0.09317 0.08947 0.0057 0.0419 1.0000
13.750 0.8759 0.10431 0.10066 -0.0014 0.0428 1.0000
14.000 0.8585 0.11297 0.10931 -0.0051 0.0435 1.0000
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Polar data table (+)
Polar graphs
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