AH 81-131 (ah81131-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 500,000 Max Cl/Cd: 95.75 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81131-il-500000-n5.txt Download as CSV file: xf-ah81131-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-131
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4655 0.09788 0.09502 -0.0077 0.7390 0.0074
-9.500 -0.4670 0.09349 0.09065 -0.0101 0.7380 0.0071
-9.250 -0.4686 0.08913 0.08632 -0.0126 0.7368 0.0068
-9.000 -0.4747 0.08357 0.08079 -0.0163 0.7356 0.0068
-8.750 -0.4836 0.07802 0.07526 -0.0211 0.7342 0.0067
-8.500 -0.5002 0.07235 0.06956 -0.0254 0.7328 0.0066
-8.250 -0.5160 0.06811 0.06525 -0.0256 0.7316 0.0066
-8.000 -0.5268 0.06379 0.06083 -0.0252 0.7305 0.0065
-7.750 -0.5318 0.05941 0.05630 -0.0248 0.7295 0.0065
-7.500 -0.5333 0.05491 0.05163 -0.0239 0.7283 0.0065
-7.250 -0.5306 0.05053 0.04707 -0.0228 0.7269 0.0065
-7.000 -0.5248 0.04626 0.04258 -0.0213 0.7254 0.0065
-6.750 -0.5150 0.04209 0.03815 -0.0195 0.7240 0.0070
-6.500 -0.5022 0.03838 0.03416 -0.0177 0.7227 0.0073
-6.250 -0.4886 0.03496 0.03043 -0.0158 0.7214 0.0074
-6.000 -0.4760 0.03149 0.02663 -0.0138 0.7201 0.0071
-5.750 -0.4604 0.02831 0.02311 -0.0119 0.7189 0.0069
-5.500 -0.4424 0.02532 0.01974 -0.0100 0.7177 0.0067
-5.250 -0.4220 0.02266 0.01670 -0.0084 0.7167 0.0066
-5.000 -0.3991 0.02045 0.01416 -0.0072 0.7157 0.0065
-4.750 -0.3742 0.01869 0.01212 -0.0065 0.7146 0.0065
-4.500 -0.3481 0.01728 0.01052 -0.0060 0.7131 0.0066
-4.250 -0.3219 0.01615 0.00924 -0.0057 0.7115 0.0068
-4.000 -0.2959 0.01524 0.00822 -0.0053 0.7099 0.0071
-3.750 -0.2703 0.01451 0.00737 -0.0049 0.7083 0.0074
-3.500 -0.2447 0.01392 0.00670 -0.0045 0.7068 0.0076
-3.250 -0.2199 0.01328 0.00599 -0.0040 0.7056 0.0080
-3.000 -0.1957 0.01263 0.00526 -0.0033 0.7044 0.0085
-2.750 -0.1700 0.01224 0.00485 -0.0030 0.7033 0.0095
-2.500 -0.1437 0.01196 0.00450 -0.0028 0.7022 0.0104
-2.250 -0.1170 0.01165 0.00415 -0.0027 0.7005 0.0108
-2.000 -0.0897 0.01139 0.00385 -0.0027 0.6986 0.0112
-1.750 -0.0623 0.01118 0.00359 -0.0027 0.6967 0.0119
-1.500 -0.0350 0.01098 0.00336 -0.0026 0.6951 0.0148
-1.250 -0.0088 0.01066 0.00316 -0.0025 0.6935 0.0507
-1.000 0.0084 0.00940 0.00287 -0.0011 0.6919 0.3288
-0.750 0.0200 0.00818 0.00268 0.0018 0.6904 0.6076
-0.500 0.0785 0.00737 0.00302 -0.0041 0.6896 0.9179
-0.250 0.1093 0.00744 0.00300 -0.0047 0.6885 0.9302
0.000 0.1467 0.00755 0.00308 -0.0069 0.6859 0.9358
0.250 0.1768 0.00764 0.00314 -0.0074 0.6828 0.9452
0.500 0.2139 0.00770 0.00314 -0.0094 0.6798 0.9490
0.750 0.2457 0.00771 0.00311 -0.0103 0.6775 0.9530
1.000 0.2728 0.00773 0.00307 -0.0102 0.6756 0.9582
1.250 0.3084 0.00778 0.00311 -0.0121 0.6730 0.9597
1.500 0.3438 0.00783 0.00316 -0.0140 0.6698 0.9619
1.750 0.3782 0.00787 0.00319 -0.0156 0.6669 0.9649
2.000 0.4090 0.00790 0.00320 -0.0164 0.6643 0.9689
2.250 0.4393 0.00791 0.00319 -0.0171 0.6621 0.9720
2.500 0.4754 0.00796 0.00327 -0.0191 0.6591 0.9736
2.750 0.5105 0.00800 0.00333 -0.0210 0.6557 0.9754
3.000 0.5440 0.00801 0.00337 -0.0225 0.6524 0.9775
3.250 0.5755 0.00799 0.00332 -0.0234 0.6482 0.9797
3.500 0.6065 0.00802 0.00339 -0.0244 0.6402 0.9821
3.750 0.6361 0.00803 0.00340 -0.0250 0.6321 0.9845
4.000 0.6708 0.00801 0.00338 -0.0267 0.6209 0.9857
4.250 0.7048 0.00803 0.00342 -0.0284 0.6095 0.9872
4.500 0.7378 0.00808 0.00347 -0.0298 0.5965 0.9887
4.750 0.7700 0.00817 0.00353 -0.0312 0.5796 0.9904
5.000 0.8024 0.00838 0.00367 -0.0326 0.5465 0.9922
5.250 0.8337 0.00923 0.00413 -0.0347 0.4613 0.9939
5.500 0.8646 0.01025 0.00482 -0.0370 0.3943 0.9954
5.750 0.8946 0.01119 0.00549 -0.0391 0.3323 0.9969
6.000 0.9220 0.01232 0.00630 -0.0410 0.2639 0.9986
6.250 0.9460 0.01347 0.00716 -0.0422 0.2042 1.0000
6.500 0.9537 0.01486 0.00821 -0.0406 0.1398 1.0000
6.750 0.9510 0.01647 0.00949 -0.0374 0.0823 1.0000
7.000 0.9491 0.01731 0.01026 -0.0332 0.0666 1.0000
7.250 0.9446 0.01797 0.01089 -0.0283 0.0582 1.0000
7.500 0.9474 0.01858 0.01150 -0.0247 0.0526 1.0000
7.750 0.9533 0.01919 0.01211 -0.0217 0.0474 1.0000
8.000 0.9611 0.01978 0.01271 -0.0190 0.0435 1.0000
8.250 0.9688 0.02045 0.01339 -0.0165 0.0389 1.0000
8.500 0.9796 0.02102 0.01401 -0.0144 0.0371 1.0000
8.750 0.9899 0.02166 0.01466 -0.0123 0.0318 1.0000
9.000 0.9994 0.02239 0.01537 -0.0103 0.0265 1.0000
9.250 1.0071 0.02327 0.01619 -0.0081 0.0169 1.0000
9.500 1.0103 0.02447 0.01729 -0.0055 0.0067 1.0000
9.750 1.0178 0.02549 0.01833 -0.0034 0.0048 1.0000
10.000 1.0277 0.02639 0.01929 -0.0017 0.0043 1.0000
10.250 1.0383 0.02727 0.02023 -0.0002 0.0039 1.0000
10.500 1.0479 0.02826 0.02130 0.0014 0.0036 1.0000
10.750 1.0569 0.02933 0.02247 0.0030 0.0032 1.0000
11.000 1.0669 0.03037 0.02358 0.0044 0.0032 1.0000
11.250 1.0754 0.03155 0.02483 0.0059 0.0030 1.0000
11.500 1.0818 0.03294 0.02631 0.0075 0.0027 1.0000
11.750 1.0878 0.03443 0.02791 0.0089 0.0026 1.0000
12.000 1.0942 0.03594 0.02951 0.0103 0.0025 1.0000
12.250 1.1018 0.03740 0.03106 0.0114 0.0025 1.0000
12.500 1.1086 0.03897 0.03272 0.0125 0.0024 1.0000
12.750 1.1151 0.04062 0.03446 0.0135 0.0024 1.0000
13.000 1.1193 0.04253 0.03648 0.0146 0.0023 1.0000
13.250 1.1244 0.04439 0.03844 0.0155 0.0023 1.0000
13.500 1.1285 0.04641 0.04057 0.0163 0.0023 1.0000
13.750 1.1308 0.04868 0.04296 0.0172 0.0022 1.0000
14.000 1.1328 0.05102 0.04544 0.0179 0.0022 1.0000
14.250 1.1346 0.05346 0.04801 0.0184 0.0021 1.0000
14.500 1.1344 0.05620 0.05088 0.0189 0.0021 1.0000
14.750 1.1341 0.05904 0.05385 0.0193 0.0021 1.0000
15.000 1.1341 0.06190 0.05684 0.0194 0.0021 1.0000
15.250 1.1310 0.06524 0.06033 0.0195 0.0020 1.0000
15.500 1.1281 0.06868 0.06392 0.0193 0.0020 1.0000
15.750 1.1248 0.07227 0.06764 0.0189 0.0020 1.0000
16.000 1.1182 0.07644 0.07197 0.0183 0.0020 1.0000
16.250 1.1120 0.08072 0.07641 0.0174 0.0020 1.0000
16.500 1.1028 0.08562 0.08147 0.0161 0.0020 1.0000
16.750 1.0923 0.09089 0.08692 0.0146 0.0020 1.0000
17.000 1.0836 0.09604 0.09220 0.0127 0.0020 1.0000
17.250 1.0714 0.10202 0.09835 0.0105 0.0020 1.0000
17.500 1.0582 0.10838 0.10487 0.0079 0.0020 1.0000
17.750 1.0451 0.11491 0.11155 0.0050 0.0020 1.0000
18.000 1.0300 0.12208 0.11887 0.0016 0.0020 1.0000
18.250 1.0156 0.12944 0.12638 -0.0020 0.0020 1.0000
18.500 1.0000 0.13740 0.13447 -0.0060 0.0020 1.0000
18.750 0.9855 0.14532 0.14252 -0.0101 0.0021 1.0000
19.000 0.9665 0.15485 0.15219 -0.0150 0.0021 1.0000
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Polar data table (+)
Polar graphs
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