LA2573A (la2573a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LA2573A (la2573a-il) Reynolds number: 100,000 Max Cl/Cd: 27.94 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-la2573a-il-100000-n5.txt Download as CSV file: xf-la2573a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LA2573A
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4726 0.09797 0.09181 0.0085 0.5342 0.0822
-8.250 -0.4875 0.09276 0.08661 0.0031 0.5329 0.0824
-7.750 -0.5203 0.07481 0.06838 -0.0030 0.5317 0.0523
-7.500 -0.5162 0.07169 0.06519 -0.0031 0.5294 0.0519
-7.250 -0.5150 0.06793 0.06130 -0.0035 0.5275 0.0515
-7.000 -0.5150 0.06361 0.05676 -0.0039 0.5260 0.0515
-6.750 -0.5122 0.05934 0.05225 -0.0040 0.5242 0.0516
-6.500 -0.5059 0.05532 0.04796 -0.0037 0.5221 0.0517
-6.250 -0.4961 0.05171 0.04408 -0.0031 0.5196 0.0515
-6.000 -0.4837 0.04838 0.04046 -0.0024 0.5171 0.0513
-5.750 -0.4697 0.04520 0.03695 -0.0016 0.5145 0.0511
-5.500 -0.4538 0.04227 0.03363 -0.0006 0.5119 0.0511
-5.250 -0.4362 0.03956 0.03050 0.0005 0.5095 0.0513
-5.000 -0.4174 0.03703 0.02745 0.0016 0.5074 0.0519
-4.750 -0.3962 0.03518 0.02521 0.0025 0.5054 0.0529
-4.500 -0.3719 0.03407 0.02405 0.0028 0.5030 0.0538
-4.250 -0.3475 0.03273 0.02252 0.0033 0.5006 0.0546
-4.000 -0.3225 0.03133 0.02088 0.0038 0.4979 0.0551
-3.750 -0.2968 0.03006 0.01937 0.0044 0.4952 0.0558
-3.500 -0.2705 0.02890 0.01797 0.0049 0.4926 0.0566
-3.250 -0.2437 0.02788 0.01668 0.0054 0.4902 0.0578
-3.000 -0.2169 0.02706 0.01567 0.0058 0.4880 0.0594
-2.750 -0.1901 0.02645 0.01501 0.0061 0.4862 0.0610
-2.500 -0.1625 0.02582 0.01431 0.0063 0.4843 0.0625
-2.250 -0.1344 0.02518 0.01365 0.0064 0.4818 0.0639
-2.000 -0.1064 0.02462 0.01303 0.0066 0.4791 0.0654
-1.750 -0.0794 0.02413 0.01263 0.0068 0.4764 0.0675
-1.500 -0.0525 0.02377 0.01229 0.0071 0.4738 0.0705
-1.250 -0.0257 0.02342 0.01188 0.0075 0.4716 0.0735
-1.000 0.0001 0.02302 0.01157 0.0080 0.4697 0.0761
-0.750 0.0260 0.02276 0.01130 0.0085 0.4680 0.0799
-0.500 0.0518 0.02254 0.01105 0.0091 0.4662 0.0850
-0.250 0.0780 0.02241 0.01095 0.0095 0.4641 0.0916
0.000 0.1044 0.02230 0.01097 0.0097 0.4612 0.1002
0.250 0.1309 0.02221 0.01100 0.0099 0.4585 0.1164
0.500 0.1568 0.02196 0.01105 0.0102 0.4561 0.1631
1.000 0.3594 0.02054 0.01188 -0.0138 0.4492 1.0000
1.250 0.3832 0.02070 0.01191 -0.0131 0.4475 1.0000
1.500 0.4070 0.02091 0.01200 -0.0124 0.4459 1.0000
1.750 0.4314 0.02135 0.01247 -0.0123 0.4433 1.0000
2.000 0.4556 0.02179 0.01296 -0.0121 0.4402 1.0000
2.250 0.4793 0.02218 0.01335 -0.0117 0.4371 1.0000
2.500 0.5028 0.02252 0.01368 -0.0112 0.4344 1.0000
2.750 0.5261 0.02285 0.01397 -0.0106 0.4323 1.0000
3.000 0.5492 0.02314 0.01421 -0.0098 0.4303 1.0000
3.250 0.5723 0.02337 0.01438 -0.0090 0.4285 1.0000
3.500 0.5953 0.02360 0.01454 -0.0080 0.4269 1.0000
3.750 0.6171 0.02448 0.01557 -0.0080 0.4230 1.0000
4.000 0.6386 0.02527 0.01647 -0.0077 0.4193 1.0000
4.250 0.6601 0.02582 0.01706 -0.0071 0.4162 1.0000
4.500 0.6818 0.02619 0.01744 -0.0063 0.4136 1.0000
4.750 0.7037 0.02649 0.01772 -0.0053 0.4116 1.0000
5.000 0.7258 0.02672 0.01792 -0.0042 0.4099 1.0000
5.250 0.7481 0.02691 0.01807 -0.0030 0.4084 1.0000
5.500 0.7612 0.02885 0.02031 -0.0032 0.4016 1.0000
5.750 0.7793 0.02961 0.02114 -0.0023 0.3980 1.0000
6.000 0.7993 0.02998 0.02153 -0.0012 0.3954 1.0000
6.250 0.8205 0.03014 0.02169 0.0001 0.3934 1.0000
6.500 0.8428 0.03017 0.02169 0.0014 0.3918 1.0000
7.000 0.8601 0.03364 0.02551 0.0029 0.3801 1.0000
7.250 0.8805 0.03379 0.02568 0.0043 0.3778 1.0000
7.500 0.9035 0.03367 0.02556 0.0056 0.3761 1.0000
7.750 0.9234 0.03393 0.02584 0.0069 0.3736 1.0000
8.250 0.9295 0.03776 0.02993 0.0087 0.3610 1.0000
8.500 0.9391 0.03894 0.03118 0.0097 0.3567 1.0000
9.500 0.9154 0.04960 0.04200 0.0107 0.3284 1.0000
10.000 0.8668 0.05961 0.05203 0.0089 0.3049 1.0000
10.250 0.8929 0.05891 0.05139 0.0100 0.3023 1.0000
10.500 0.9123 0.05889 0.05141 0.0109 0.2981 1.0000
11.000 0.9204 0.06251 0.05509 0.0109 0.2819 1.0000
11.500 0.9727 0.06046 0.05314 0.0130 0.2717 1.0000
11.750 0.9576 0.06489 0.05760 0.0119 0.2599 1.0000
12.000 0.9591 0.06723 0.05997 0.0115 0.2506 1.0000
12.250 0.9857 0.06617 0.05894 0.0125 0.2443 1.0000
12.500 0.9809 0.06943 0.06225 0.0118 0.2335 1.0000
12.750 0.9928 0.07044 0.06328 0.0120 0.2242 1.0000
13.000 1.0163 0.06981 0.06262 0.0128 0.2148 1.0000
13.250 1.0169 0.07254 0.06536 0.0122 0.2029 1.0000
13.500 1.0228 0.07455 0.06736 0.0118 0.1906 1.0000
13.750 1.0292 0.07649 0.06925 0.0116 0.1777 1.0000
14.000 1.0339 0.07869 0.07137 0.0111 0.1644 1.0000
14.250 1.0365 0.08124 0.07384 0.0106 0.1514 1.0000
14.500 1.0367 0.08423 0.07674 0.0098 0.1389 1.0000
14.750 1.0359 0.08742 0.07986 0.0088 0.1278 1.0000
15.000 1.0347 0.09077 0.08315 0.0078 0.1178 1.0000
15.250 1.0340 0.09411 0.08642 0.0068 0.1093 1.0000
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Polar data table (+)
Polar graphs
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