LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 100,000 Max Cl/Cd: 42.64 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5b-il-100000-n5.txt Download as CSV file: xf-c5b-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7324 0.06422 0.05815 -0.0567 1.0000 0.0328
-10.000 -0.7551 0.06178 0.05561 -0.0523 1.0000 0.0328
-9.750 -0.7727 0.05896 0.05263 -0.0485 1.0000 0.0327
-9.500 -0.7864 0.05609 0.04955 -0.0448 1.0000 0.0327
-9.250 -0.7960 0.05318 0.04641 -0.0413 1.0000 0.0327
-9.000 -0.8019 0.05028 0.04323 -0.0379 1.0000 0.0327
-8.750 -0.8041 0.04744 0.04007 -0.0348 1.0000 0.0327
-8.500 -0.8027 0.04472 0.03700 -0.0319 1.0000 0.0327
-8.000 -0.7891 0.03969 0.03135 -0.0271 1.0000 0.0331
-7.750 -0.7777 0.03751 0.02892 -0.0252 1.0000 0.0334
-7.500 -0.7641 0.03560 0.02679 -0.0235 1.0000 0.0338
-7.250 -0.7488 0.03388 0.02486 -0.0219 1.0000 0.0343
-7.000 -0.7320 0.03231 0.02309 -0.0205 1.0000 0.0349
-6.750 -0.7141 0.03086 0.02144 -0.0191 1.0000 0.0356
-6.500 -0.6951 0.02955 0.01993 -0.0179 1.0000 0.0366
-6.250 -0.6752 0.02841 0.01861 -0.0167 1.0000 0.0382
-6.000 -0.6546 0.02740 0.01736 -0.0156 1.0000 0.0400
-5.750 -0.6342 0.02621 0.01612 -0.0146 1.0000 0.0416
-5.500 -0.6138 0.02524 0.01513 -0.0136 1.0000 0.0433
-5.250 -0.5931 0.02438 0.01423 -0.0126 1.0000 0.0453
-5.000 -0.5668 0.02364 0.01337 -0.0127 0.9986 0.0488
-4.750 -0.5381 0.02276 0.01250 -0.0135 0.9964 0.0527
-4.500 -0.5078 0.02209 0.01177 -0.0144 0.9942 0.0574
-4.250 -0.4792 0.02141 0.01109 -0.0151 0.9913 0.0646
-4.000 -0.4493 0.02080 0.01048 -0.0160 0.9885 0.0745
-3.750 -0.4182 0.02019 0.01001 -0.0172 0.9860 0.0976
-3.500 -0.3885 0.01951 0.00959 -0.0182 0.9833 0.1486
-3.250 -0.3603 0.01871 0.00924 -0.0191 0.9800 0.2339
-3.000 -0.3319 0.01772 0.00900 -0.0201 0.9772 0.3889
-2.750 -0.3047 0.01701 0.00922 -0.0200 0.9748 0.5817
-2.500 -0.2816 0.01693 0.00952 -0.0184 0.9703 0.6940
-2.250 -0.2543 0.01702 0.00968 -0.0177 0.9661 0.7467
-2.000 -0.2219 0.01715 0.00974 -0.0184 0.9629 0.7737
-1.750 -0.1964 0.01720 0.00974 -0.0178 0.9577 0.7958
-1.500 -0.1682 0.01730 0.00981 -0.0175 0.9532 0.8218
-1.250 -0.1374 0.01745 0.00994 -0.0177 0.9498 0.8496
-1.000 -0.1139 0.01757 0.01007 -0.0162 0.9442 0.8761
-0.750 -0.0840 0.01772 0.01019 -0.0161 0.9397 0.9012
-0.500 -0.0462 0.01786 0.01029 -0.0180 0.9366 0.9194
-0.250 -0.0078 0.01798 0.01035 -0.0202 0.9332 0.9337
0.000 0.0260 0.01806 0.01039 -0.0217 0.9275 0.9466
0.250 0.0683 0.01815 0.01045 -0.0250 0.9237 0.9560
0.500 0.1134 0.01821 0.01049 -0.0288 0.9208 0.9642
0.750 0.1517 0.01828 0.01055 -0.0314 0.9151 0.9740
1.000 0.1944 0.01830 0.01059 -0.0348 0.9097 0.9819
1.250 0.2423 0.01828 0.01059 -0.0392 0.9060 0.9876
1.500 0.2835 0.01827 0.01062 -0.0424 0.8992 0.9955
1.750 0.3239 0.01816 0.01056 -0.0452 0.8927 1.0000
2.000 0.3484 0.01798 0.01042 -0.0448 0.8826 1.0000
2.250 0.3983 0.01741 0.00992 -0.0486 0.8735 1.0000
2.500 0.4224 0.01688 0.00943 -0.0473 0.8546 1.0000
2.750 0.4512 0.01632 0.00891 -0.0467 0.8350 1.0000
3.000 0.4820 0.01582 0.00847 -0.0466 0.8156 1.0000
3.250 0.5054 0.01551 0.00821 -0.0452 0.7932 1.0000
3.500 0.5355 0.01514 0.00786 -0.0450 0.7651 1.0000
3.750 0.5713 0.01477 0.00747 -0.0457 0.7229 1.0000
4.000 0.6192 0.01452 0.00685 -0.0484 0.6269 1.0000
4.250 0.6408 0.01505 0.00673 -0.0467 0.5023 1.0000
4.500 0.6492 0.01591 0.00696 -0.0429 0.3886 1.0000
4.750 0.6587 0.01679 0.00733 -0.0397 0.2986 1.0000
5.000 0.6718 0.01759 0.00777 -0.0372 0.2337 1.0000
5.250 0.6867 0.01835 0.00824 -0.0351 0.1873 1.0000
5.500 0.7034 0.01904 0.00879 -0.0332 0.1564 1.0000
5.750 0.7205 0.01975 0.00935 -0.0314 0.1333 1.0000
6.000 0.7376 0.02047 0.00997 -0.0297 0.1171 1.0000
6.250 0.7557 0.02115 0.01065 -0.0281 0.1058 1.0000
6.500 0.7734 0.02191 0.01140 -0.0264 0.0980 1.0000
6.750 0.7920 0.02263 0.01214 -0.0249 0.0913 1.0000
7.000 0.8104 0.02343 0.01292 -0.0234 0.0861 1.0000
7.250 0.8304 0.02417 0.01374 -0.0221 0.0811 1.0000
7.500 0.8500 0.02499 0.01459 -0.0209 0.0775 1.0000
7.750 0.8701 0.02595 0.01554 -0.0198 0.0742 1.0000
8.000 0.8918 0.02681 0.01653 -0.0189 0.0702 1.0000
8.250 0.9125 0.02769 0.01745 -0.0180 0.0668 1.0000
8.500 0.9327 0.02880 0.01851 -0.0171 0.0638 1.0000
8.750 0.9549 0.02985 0.01979 -0.0163 0.0606 1.0000
9.000 0.9756 0.03094 0.02101 -0.0154 0.0575 1.0000
9.250 0.9950 0.03203 0.02213 -0.0145 0.0549 1.0000
9.500 1.0167 0.03367 0.02382 -0.0140 0.0528 1.0000
9.750 1.0370 0.03534 0.02582 -0.0130 0.0509 1.0000
10.000 1.0544 0.03702 0.02777 -0.0117 0.0487 1.0000
10.250 1.0694 0.03849 0.02944 -0.0102 0.0466 1.0000
10.500 1.0839 0.03996 0.03098 -0.0088 0.0449 1.0000
10.750 1.0990 0.04227 0.03339 -0.0077 0.0435 1.0000
11.000 1.1040 0.04464 0.03623 -0.0048 0.0425 1.0000
11.250 1.1042 0.04725 0.03928 -0.0016 0.0415 1.0000
11.500 1.0996 0.04993 0.04233 0.0021 0.0406 1.0000
11.750 1.0923 0.05258 0.04531 0.0056 0.0397 1.0000
12.000 1.0845 0.05512 0.04811 0.0088 0.0387 1.0000
12.250 1.0791 0.05739 0.05055 0.0112 0.0377 1.0000
12.500 1.0742 0.05961 0.05291 0.0133 0.0368 1.0000
12.750 1.0719 0.06174 0.05510 0.0148 0.0360 1.0000
13.000 1.0677 0.06449 0.05789 0.0159 0.0353 1.0000
13.250 1.0421 0.06920 0.06292 0.0170 0.0351 1.0000
13.500 1.0154 0.07469 0.06869 0.0166 0.0351 1.0000
13.750 0.9878 0.08111 0.07535 0.0145 0.0351 1.0000
14.000 0.9599 0.08863 0.08307 0.0107 0.0352 1.0000
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Polar data table (+)
Polar graphs
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