AH 80-136 (ah80136-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 100,000 Max Cl/Cd: 33.43 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80136-il-100000-n5.txt Download as CSV file: xf-ah80136-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-136
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5125 0.09767 0.09298 0.0097 0.6796 0.0311
-8.500 -0.5122 0.09253 0.08784 0.0060 0.6776 0.0309
-8.250 -0.5133 0.08684 0.08216 0.0008 0.6757 0.0305
-8.000 -0.5181 0.08141 0.07667 -0.0038 0.6740 0.0301
-7.750 -0.5224 0.07631 0.07146 -0.0068 0.6725 0.0297
-7.500 -0.5230 0.07112 0.06614 -0.0096 0.6705 0.0293
-7.250 -0.5206 0.06602 0.06087 -0.0118 0.6681 0.0288
-7.000 -0.5156 0.06095 0.05556 -0.0133 0.6659 0.0281
-6.750 -0.5081 0.05595 0.05021 -0.0141 0.6640 0.0274
-6.500 -0.4977 0.05117 0.04502 -0.0143 0.6621 0.0269
-6.250 -0.4841 0.04695 0.04034 -0.0140 0.6603 0.0266
-6.000 -0.4678 0.04327 0.03618 -0.0134 0.6586 0.0266
-5.750 -0.4488 0.04009 0.03251 -0.0128 0.6567 0.0268
-5.500 -0.4258 0.03730 0.02928 -0.0128 0.6537 0.0273
-5.250 -0.4016 0.03512 0.02668 -0.0126 0.6509 0.0288
-5.000 -0.3762 0.03330 0.02432 -0.0122 0.6486 0.0310
-4.750 -0.3499 0.03169 0.02223 -0.0117 0.6466 0.0321
-4.500 -0.3247 0.02947 0.01980 -0.0114 0.6448 0.0334
-4.250 -0.2989 0.02810 0.01826 -0.0111 0.6431 0.0351
-4.000 -0.2705 0.02721 0.01726 -0.0115 0.6402 0.0387
-3.750 -0.2415 0.02629 0.01613 -0.0118 0.6372 0.0417
-3.500 -0.2143 0.02510 0.01488 -0.0117 0.6347 0.0440
-3.250 -0.1884 0.02430 0.01410 -0.0117 0.6325 0.0489
-3.000 -0.1624 0.02366 0.01334 -0.0113 0.6306 0.0538
-2.750 -0.1378 0.02292 0.01250 -0.0107 0.6289 0.0584
-2.500 -0.1110 0.02252 0.01203 -0.0108 0.6264 0.0674
-2.250 -0.0829 0.02213 0.01166 -0.0113 0.6230 0.0781
-2.000 -0.0563 0.02161 0.01134 -0.0116 0.6204 0.1142
-1.750 -0.0362 0.01993 0.01103 -0.0111 0.6182 0.4189
-1.500 -0.0171 0.01891 0.01109 -0.0087 0.6162 0.6913
-1.250 0.0312 0.01893 0.01154 -0.0097 0.6145 0.9112
-1.000 0.1107 0.01929 0.01160 -0.0183 0.6128 0.9793
-0.750 0.1584 0.01963 0.01178 -0.0233 0.6089 0.9905
-0.500 0.2019 0.01977 0.01175 -0.0272 0.6058 0.9993
-0.250 0.2275 0.01987 0.01171 -0.0274 0.6032 1.0000
0.000 0.2511 0.01996 0.01165 -0.0271 0.6012 1.0000
0.250 0.2744 0.02003 0.01158 -0.0265 0.5995 1.0000
0.500 0.3005 0.02042 0.01191 -0.0272 0.5961 1.0000
0.750 0.3266 0.02086 0.01230 -0.0280 0.5920 1.0000
1.000 0.3510 0.02110 0.01247 -0.0279 0.5892 1.0000
1.250 0.3747 0.02125 0.01253 -0.0274 0.5869 1.0000
1.500 0.3981 0.02133 0.01252 -0.0267 0.5851 1.0000
1.750 0.4237 0.02190 0.01308 -0.0274 0.5809 1.0000
2.000 0.4487 0.02244 0.01362 -0.0279 0.5765 1.0000
2.250 0.4725 0.02264 0.01377 -0.0275 0.5736 1.0000
2.500 0.4962 0.02272 0.01380 -0.0267 0.5715 1.0000
2.750 0.5199 0.02272 0.01374 -0.0258 0.5698 1.0000
3.000 0.5446 0.02382 0.01494 -0.0274 0.5625 1.0000
3.250 0.5685 0.02401 0.01512 -0.0269 0.5592 1.0000
3.500 0.5924 0.02401 0.01508 -0.0261 0.5570 1.0000
3.750 0.6167 0.02391 0.01496 -0.0250 0.5553 1.0000
4.000 0.6390 0.02524 0.01642 -0.0266 0.5467 1.0000
4.250 0.6632 0.02529 0.01648 -0.0259 0.5439 1.0000
4.500 0.6881 0.02519 0.01637 -0.0250 0.5419 1.0000
5.000 0.7331 0.02660 0.01797 -0.0256 0.5304 1.0000
5.250 0.7586 0.02643 0.01782 -0.0248 0.5282 1.0000
5.750 0.8023 0.02784 0.01945 -0.0252 0.5162 1.0000
6.000 0.8288 0.02755 0.01921 -0.0244 0.5140 1.0000
6.500 0.8714 0.02890 0.02079 -0.0247 0.5013 1.0000
6.750 0.8992 0.02844 0.02043 -0.0238 0.4993 1.0000
7.000 0.9132 0.03014 0.02230 -0.0248 0.4885 1.0000
7.250 0.9415 0.02959 0.02184 -0.0239 0.4860 1.0000
7.750 0.9837 0.03052 0.02306 -0.0238 0.4722 1.0000
8.250 1.0260 0.03134 0.02417 -0.0236 0.4579 1.0000
8.750 1.0687 0.03197 0.02510 -0.0233 0.4430 1.0000
9.000 1.0805 0.03325 0.02653 -0.0236 0.4301 1.0000
9.250 1.0967 0.03354 0.02692 -0.0229 0.4161 1.0000
9.500 1.1120 0.03378 0.02722 -0.0221 0.3980 1.0000
9.750 1.1230 0.03460 0.02807 -0.0213 0.3770 1.0000
10.000 1.1404 0.03474 0.02819 -0.0203 0.3552 1.0000
10.250 1.1510 0.03571 0.02912 -0.0194 0.3327 1.0000
10.500 1.1578 0.03705 0.03041 -0.0185 0.3069 1.0000
10.750 1.1597 0.03892 0.03217 -0.0176 0.2784 1.0000
11.000 1.1567 0.04134 0.03444 -0.0168 0.2467 1.0000
11.250 1.1496 0.04426 0.03715 -0.0161 0.2112 1.0000
11.500 1.1389 0.04762 0.04026 -0.0156 0.1756 1.0000
11.750 1.1269 0.05128 0.04367 -0.0152 0.1402 1.0000
12.000 1.1151 0.05517 0.04732 -0.0150 0.1090 1.0000
12.250 1.1058 0.05897 0.05093 -0.0150 0.0865 1.0000
12.500 1.0985 0.06267 0.05451 -0.0150 0.0720 1.0000
12.750 1.0939 0.06618 0.05800 -0.0152 0.0616 1.0000
13.000 1.0904 0.06963 0.06148 -0.0153 0.0539 1.0000
13.250 1.0853 0.07335 0.06519 -0.0157 0.0481 1.0000
13.500 1.0842 0.07665 0.06859 -0.0159 0.0430 1.0000
13.750 1.0815 0.08020 0.07219 -0.0163 0.0388 1.0000
14.000 1.0795 0.08364 0.07571 -0.0166 0.0354 1.0000
14.250 1.0806 0.08672 0.07891 -0.0169 0.0321 1.0000
14.500 1.0809 0.08991 0.08217 -0.0172 0.0298 1.0000
14.750 1.0813 0.09283 0.08507 -0.0173 0.0279 1.0000
15.000 1.0870 0.09521 0.08763 -0.0172 0.0258 1.0000
15.250 1.0906 0.09797 0.09049 -0.0174 0.0238 1.0000
15.500 1.0928 0.10099 0.09358 -0.0179 0.0224 1.0000
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Polar data table (+)
Polar graphs
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