AH 81-131 (ah81131-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.79 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah81131-il-1000000-n5.txt Download as CSV file: xf-ah81131-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4937 0.08517 0.08286 -0.0113 0.7198 0.0033
-9.000 -0.5038 0.07920 0.07692 -0.0158 0.7188 0.0034
-8.750 -0.5234 0.07283 0.07054 -0.0217 0.7175 0.0033
-8.500 -0.5432 0.06823 0.06588 -0.0222 0.7162 0.0033
-8.250 -0.5576 0.06381 0.06138 -0.0216 0.7150 0.0034
-8.000 -0.5655 0.05888 0.05633 -0.0212 0.7139 0.0035
-7.750 -0.5688 0.05404 0.05135 -0.0203 0.7127 0.0036
-7.500 -0.5690 0.04903 0.04615 -0.0188 0.7116 0.0037
-7.250 -0.5655 0.04417 0.04107 -0.0169 0.7104 0.0039
-7.000 -0.5588 0.03953 0.03618 -0.0148 0.7092 0.0040
-6.750 -0.5496 0.03507 0.03144 -0.0125 0.7080 0.0041
-6.500 -0.5391 0.03059 0.02663 -0.0100 0.7068 0.0041
-6.250 -0.5238 0.02682 0.02254 -0.0077 0.7056 0.0043
-6.000 -0.5072 0.02358 0.01895 -0.0057 0.7044 0.0044
-5.750 -0.4899 0.02049 0.01546 -0.0037 0.7033 0.0043
-5.500 -0.4688 0.01826 0.01288 -0.0024 0.7022 0.0043
-5.250 -0.4452 0.01660 0.01097 -0.0016 0.7011 0.0043
-5.000 -0.4203 0.01531 0.00950 -0.0010 0.7000 0.0043
-4.750 -0.3949 0.01430 0.00835 -0.0006 0.6986 0.0044
-4.500 -0.3692 0.01346 0.00741 -0.0002 0.6971 0.0045
-4.250 -0.3433 0.01281 0.00667 0.0001 0.6955 0.0045
-4.000 -0.3170 0.01229 0.00608 0.0004 0.6941 0.0046
-3.750 -0.2950 0.01112 0.00476 0.0015 0.6928 0.0051
-3.500 -0.2691 0.01069 0.00428 0.0018 0.6915 0.0054
-3.250 -0.2425 0.01037 0.00394 0.0019 0.6902 0.0058
-3.000 -0.2158 0.01008 0.00360 0.0021 0.6889 0.0062
-2.750 -0.1889 0.00980 0.00329 0.0021 0.6874 0.0065
-2.500 -0.1616 0.00955 0.00302 0.0022 0.6858 0.0068
-2.250 -0.1342 0.00932 0.00276 0.0021 0.6841 0.0070
-2.000 -0.1065 0.00915 0.00257 0.0021 0.6825 0.0075
-1.750 -0.0788 0.00898 0.00238 0.0020 0.6808 0.0078
-1.500 -0.0512 0.00879 0.00215 0.0019 0.6791 0.0080
-1.250 -0.0233 0.00863 0.00194 0.0019 0.6774 0.0089
-1.000 0.0045 0.00849 0.00179 0.0018 0.6755 0.0125
-0.750 0.0308 0.00814 0.00167 0.0019 0.6731 0.0758
-0.500 0.0514 0.00724 0.00150 0.0028 0.6702 0.3029
-0.250 0.0690 0.00628 0.00135 0.0044 0.6670 0.5393
0.000 0.0831 0.00550 0.00124 0.0072 0.6643 0.7329
0.250 0.1193 0.00498 0.00139 0.0056 0.6621 0.9219
0.500 0.1521 0.00502 0.00141 0.0044 0.6597 0.9316
0.750 0.1863 0.00507 0.00145 0.0029 0.6570 0.9396
1.000 0.2203 0.00513 0.00148 0.0015 0.6539 0.9472
1.250 0.2539 0.00519 0.00152 0.0001 0.6511 0.9527
1.500 0.2796 0.00524 0.00153 0.0005 0.6486 0.9581
1.750 0.3145 0.00528 0.00157 -0.0013 0.6454 0.9592
2.000 0.3486 0.00532 0.00161 -0.0028 0.6418 0.9605
2.250 0.3820 0.00537 0.00165 -0.0043 0.6385 0.9619
2.500 0.4153 0.00544 0.00170 -0.0056 0.6353 0.9638
2.750 0.4475 0.00550 0.00177 -0.0068 0.6293 0.9663
3.000 0.4753 0.00558 0.00180 -0.0070 0.6211 0.9697
3.250 0.5057 0.00565 0.00188 -0.0077 0.6130 0.9719
3.500 0.5404 0.00575 0.00194 -0.0095 0.5989 0.9727
3.750 0.5741 0.00587 0.00202 -0.0111 0.5840 0.9736
4.000 0.6068 0.00597 0.00210 -0.0125 0.5742 0.9744
4.250 0.6393 0.00611 0.00222 -0.0139 0.5593 0.9754
4.500 0.6717 0.00641 0.00241 -0.0155 0.5252 0.9765
4.750 0.7033 0.00708 0.00280 -0.0173 0.4593 0.9780
5.000 0.7338 0.00789 0.00332 -0.0191 0.3978 0.9801
5.250 0.7598 0.00867 0.00386 -0.0199 0.3384 0.9834
5.500 0.7890 0.00952 0.00441 -0.0216 0.2763 0.9851
5.750 0.8186 0.01037 0.00500 -0.0235 0.2211 0.9861
6.000 0.8438 0.01162 0.00584 -0.0251 0.1410 0.9877
6.500 0.8920 0.01364 0.00746 -0.0274 0.0553 0.9919
6.750 0.9165 0.01423 0.00801 -0.0281 0.0469 0.9937
7.000 0.9407 0.01478 0.00855 -0.0286 0.0422 0.9951
7.250 0.9660 0.01530 0.00907 -0.0295 0.0367 0.9964
7.500 0.9888 0.01584 0.00960 -0.0299 0.0310 0.9981
7.750 1.0098 0.01644 0.01019 -0.0300 0.0244 0.9996
8.000 1.0072 0.01748 0.01109 -0.0261 0.0077 1.0000
8.250 1.0084 0.01825 0.01185 -0.0223 0.0036 1.0000
8.500 1.0160 0.01884 0.01246 -0.0196 0.0032 1.0000
8.750 1.0239 0.01948 0.01314 -0.0170 0.0026 1.0000
9.000 1.0338 0.02009 0.01377 -0.0148 0.0025 1.0000
9.250 1.0441 0.02071 0.01443 -0.0127 0.0024 1.0000
9.500 1.0547 0.02137 0.01513 -0.0107 0.0023 1.0000
9.750 1.0652 0.02207 0.01588 -0.0088 0.0022 1.0000
10.000 1.0756 0.02283 0.01668 -0.0070 0.0021 1.0000
10.250 1.0867 0.02357 0.01749 -0.0053 0.0020 1.0000
10.500 1.0968 0.02444 0.01840 -0.0036 0.0019 1.0000
10.750 1.1063 0.02535 0.01937 -0.0019 0.0017 1.0000
11.000 1.1171 0.02623 0.02029 -0.0004 0.0017 1.0000
11.250 1.1263 0.02724 0.02135 0.0012 0.0016 1.0000
11.500 1.1339 0.02840 0.02258 0.0029 0.0014 1.0000
11.750 1.1416 0.02961 0.02386 0.0045 0.0014 1.0000
12.000 1.1498 0.03082 0.02514 0.0059 0.0014 1.0000
12.250 1.1515 0.03261 0.02705 0.0077 0.0012 1.0000
12.500 1.1535 0.03447 0.02902 0.0094 0.0012 1.0000
12.750 1.1680 0.03533 0.02990 0.0100 0.0012 1.0000
13.000 1.1646 0.03776 0.03248 0.0118 0.0012 1.0000
13.250 1.1709 0.03943 0.03422 0.0128 0.0012 1.0000
13.500 1.1758 0.04126 0.03617 0.0138 0.0012 1.0000
13.750 1.1803 0.04319 0.03819 0.0147 0.0012 1.0000
14.000 1.1837 0.04526 0.04036 0.0155 0.0012 1.0000
14.250 1.1880 0.04732 0.04251 0.0161 0.0011 1.0000
14.500 1.1898 0.04972 0.04502 0.0167 0.0011 1.0000
14.750 1.1893 0.05239 0.04780 0.0173 0.0011 1.0000
15.000 1.1903 0.05500 0.05052 0.0176 0.0011 1.0000
15.250 1.1908 0.05776 0.05339 0.0178 0.0011 1.0000
15.500 1.1885 0.06093 0.05669 0.0179 0.0011 1.0000
15.750 1.1863 0.06416 0.06003 0.0178 0.0011 1.0000
16.000 1.1805 0.06800 0.06401 0.0175 0.0011 1.0000
16.250 1.1759 0.07181 0.06795 0.0169 0.0011 1.0000
16.500 1.1678 0.07622 0.07250 0.0161 0.0011 1.0000
16.750 1.1582 0.08105 0.07747 0.0150 0.0011 1.0000
17.000 1.1512 0.08564 0.08218 0.0136 0.0011 1.0000
17.250 1.1396 0.09115 0.08783 0.0119 0.0011 1.0000
17.500 1.1271 0.09696 0.09378 0.0098 0.0011 1.0000
17.750 1.1154 0.10286 0.09981 0.0075 0.0011 1.0000
18.000 1.1001 0.10958 0.10668 0.0047 0.0011 1.0000
18.250 1.0852 0.11642 0.11364 0.0017 0.0011 1.0000
18.500 1.0696 0.12367 0.12102 -0.0017 0.0011 1.0000
18.750 1.0552 0.13093 0.12841 -0.0052 0.0011 1.0000
19.000 1.0351 0.13975 0.13737 -0.0096 0.0011 1.0000
19.250 1.0178 0.14820 0.14594 -0.0138 0.0011 1.0000
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Polar data table (+)
Polar graphs
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