AH 81-131 (ah81131-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.82 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah81131-il-1000000.txt Download as CSV file: xf-ah81131-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4638 0.08539 0.08318 -0.0143 0.7414 0.0077
-8.750 -0.4691 0.07994 0.07777 -0.0187 0.7403 0.0077
-8.500 -0.4836 0.07378 0.07160 -0.0245 0.7389 0.0077
-8.250 -0.4974 0.06948 0.06725 -0.0252 0.7375 0.0077
-8.000 -0.5092 0.06572 0.06343 -0.0242 0.7361 0.0077
-7.750 -0.5134 0.06159 0.05919 -0.0238 0.7349 0.0077
-6.750 -0.5296 0.03975 0.03642 -0.0163 0.7303 0.0083
-6.500 -0.5173 0.03738 0.03388 -0.0150 0.7290 0.0086
-6.250 -0.5015 0.03547 0.03183 -0.0142 0.7279 0.0088
-6.000 -0.4846 0.03345 0.02966 -0.0131 0.7268 0.0092
-5.750 -0.4664 0.03137 0.02741 -0.0120 0.7255 0.0098
-5.500 -0.4472 0.02911 0.02495 -0.0106 0.7241 0.0104
-5.250 -0.4235 0.02758 0.02322 -0.0095 0.7227 0.0117
-5.000 -0.3954 0.02776 0.02325 -0.0089 0.7213 0.0124
-4.750 -0.3750 0.02592 0.02115 -0.0075 0.7200 0.0125
-4.500 -0.3634 0.02030 0.01504 -0.0048 0.7189 0.0137
-4.250 -0.3390 0.01909 0.01373 -0.0044 0.7178 0.0144
-4.000 -0.3138 0.01808 0.01259 -0.0040 0.7167 0.0152
-3.750 -0.2877 0.01716 0.01154 -0.0036 0.7153 0.0163
-3.500 -0.2599 0.01293 0.00689 -0.0015 0.7142 0.0090
-3.250 -0.2350 0.01195 0.00583 -0.0008 0.7127 0.0089
-3.000 -0.2098 0.01132 0.00516 -0.0003 0.7111 0.0094
-2.750 -0.1839 0.01087 0.00468 0.0001 0.7096 0.0101
-2.500 -0.1576 0.01049 0.00425 0.0003 0.7082 0.0108
-2.250 -0.1313 0.01014 0.00384 0.0006 0.7068 0.0112
-2.000 -0.1046 0.00983 0.00348 0.0008 0.7054 0.0116
-1.750 -0.0774 0.00962 0.00322 0.0009 0.7041 0.0123
-1.500 -0.0503 0.00939 0.00294 0.0011 0.7027 0.0127
-1.250 -0.0229 0.00919 0.00265 0.0011 0.7011 0.0141
-1.000 0.0015 0.00857 0.00242 0.0017 0.6993 0.1235
-0.750 0.0133 0.00695 0.00214 0.0041 0.6969 0.5116
-0.500 0.0282 0.00614 0.00199 0.0067 0.6945 0.7011
-0.250 0.0564 0.00542 0.00205 0.0070 0.6924 0.9112
0.000 0.1059 0.00574 0.00237 0.0027 0.6909 0.9557
0.250 0.1524 0.00595 0.00252 -0.0012 0.6894 0.9605
0.500 0.1899 0.00604 0.00256 -0.0035 0.6875 0.9622
0.750 0.2280 0.00611 0.00262 -0.0058 0.6852 0.9648
1.000 0.2557 0.00622 0.00271 -0.0058 0.6828 0.9713
1.250 0.2966 0.00626 0.00273 -0.0088 0.6808 0.9724
1.500 0.3340 0.00627 0.00271 -0.0110 0.6787 0.9735
1.750 0.3699 0.00628 0.00269 -0.0130 0.6766 0.9747
2.000 0.4051 0.00632 0.00271 -0.0147 0.6744 0.9762
2.250 0.4399 0.00634 0.00276 -0.0165 0.6718 0.9780
2.500 0.4741 0.00635 0.00278 -0.0181 0.6684 0.9804
2.750 0.5032 0.00639 0.00279 -0.0185 0.6642 0.9840
3.000 0.5400 0.00635 0.00276 -0.0207 0.6596 0.9852
3.250 0.5772 0.00629 0.00272 -0.0229 0.6530 0.9864
3.500 0.6133 0.00626 0.00267 -0.0250 0.6465 0.9877
3.750 0.6486 0.00625 0.00270 -0.0269 0.6415 0.9893
4.000 0.6821 0.00625 0.00270 -0.0284 0.6360 0.9910
4.250 0.7149 0.00625 0.00273 -0.0298 0.6264 0.9926
4.500 0.7468 0.00629 0.00277 -0.0309 0.6160 0.9942
4.750 0.7805 0.00634 0.00278 -0.0326 0.5975 0.9953
5.000 0.8154 0.00645 0.00284 -0.0346 0.5705 0.9964
5.250 0.8497 0.00670 0.00297 -0.0365 0.5338 0.9976
5.500 0.8831 0.00773 0.00354 -0.0392 0.4343 0.9983
5.750 0.9154 0.00887 0.00424 -0.0419 0.3427 0.9992
6.000 0.9453 0.01017 0.00505 -0.0444 0.2446 1.0000
6.250 0.9656 0.01121 0.00576 -0.0445 0.1806 1.0000
6.500 0.9800 0.01254 0.00670 -0.0439 0.1055 1.0000
6.750 0.9926 0.01362 0.00754 -0.0426 0.0640 1.0000
7.000 1.0088 0.01427 0.00816 -0.0416 0.0536 1.0000
7.250 1.0237 0.01487 0.00876 -0.0404 0.0474 1.0000
7.500 1.0340 0.01552 0.00941 -0.0384 0.0424 1.0000
7.750 1.0333 0.01614 0.01003 -0.0341 0.0376 1.0000
8.000 1.0324 0.01664 0.01055 -0.0297 0.0341 1.0000
8.250 1.0305 0.01739 0.01122 -0.0254 0.0231 1.0000
8.500 1.0295 0.01826 0.01200 -0.0214 0.0117 1.0000
8.750 1.0297 0.01922 0.01292 -0.0177 0.0057 1.0000
9.000 1.0380 0.01989 0.01362 -0.0152 0.0050 1.0000
9.250 1.0465 0.02061 0.01440 -0.0128 0.0044 1.0000
9.500 1.0561 0.02132 0.01515 -0.0107 0.0042 1.0000
9.750 1.0654 0.02210 0.01599 -0.0086 0.0040 1.0000
10.000 1.0747 0.02292 0.01687 -0.0066 0.0039 1.0000
10.250 1.0841 0.02378 0.01778 -0.0048 0.0036 1.0000
10.500 1.0923 0.02477 0.01885 -0.0028 0.0034 1.0000
10.750 1.0967 0.02606 0.02021 -0.0005 0.0030 1.0000
11.000 1.1063 0.02704 0.02125 0.0011 0.0031 1.0000
11.250 1.1104 0.02845 0.02274 0.0031 0.0029 1.0000
11.500 1.1132 0.03002 0.02441 0.0052 0.0028 1.0000
11.750 1.1176 0.03153 0.02601 0.0070 0.0028 1.0000
12.000 1.1238 0.03298 0.02754 0.0085 0.0028 1.0000
12.250 1.1247 0.03493 0.02960 0.0103 0.0027 1.0000
12.500 1.1283 0.03673 0.03149 0.0118 0.0027 1.0000
12.750 1.1388 0.03797 0.03279 0.0126 0.0028 1.0000
13.000 1.1396 0.04013 0.03507 0.0142 0.0027 1.0000
13.250 1.1441 0.04201 0.03703 0.0153 0.0027 1.0000
13.500 1.1483 0.04396 0.03909 0.0163 0.0028 1.0000
13.750 1.1508 0.04616 0.04141 0.0174 0.0028 1.0000
14.000 1.1542 0.04831 0.04368 0.0182 0.0028 1.0000
14.250 1.1562 0.05067 0.04616 0.0190 0.0028 1.0000
14.500 1.1562 0.05333 0.04895 0.0198 0.0029 1.0000
14.750 1.1576 0.05593 0.05170 0.0203 0.0029 1.0000
15.000 1.1566 0.05887 0.05478 0.0207 0.0030 1.0000
15.250 1.1471 0.06298 0.05914 0.0215 0.0031 1.0000
15.500 1.1303 0.06830 0.06476 0.0220 0.0034 1.0000
15.750 1.1189 0.07303 0.06968 0.0216 0.0035 1.0000
16.000 1.0934 0.08018 0.07712 0.0206 0.0038 1.0000
16.250 1.0848 0.08502 0.08208 0.0190 0.0037 1.0000
16.500 1.0549 0.09366 0.09098 0.0164 0.0040 1.0000
16.750 1.0300 0.10205 0.09956 0.0131 0.0041 1.0000
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Polar data table (+)
Polar graphs
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