AH 81-131 (ah81131-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 81-131 (ah81131-il) Reynolds number: 500,000 Max Cl/Cd: 110 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah81131-il-500000.txt Download as CSV file: xf-ah81131-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3769 0.08564 0.08327 -0.0160 0.7622 0.0140
-9.000 -0.3796 0.08086 0.07850 -0.0182 0.7613 0.0143
-8.750 -0.3851 0.07563 0.07327 -0.0210 0.7605 0.0144
-8.500 -0.4765 0.07225 0.06966 -0.0334 0.7632 0.0127
-8.250 -0.4976 0.06787 0.06519 -0.0323 0.7615 0.0129
-8.000 -0.5094 0.06370 0.06092 -0.0316 0.7601 0.0131
-7.750 -0.5108 0.06053 0.05766 -0.0308 0.7589 0.0134
-7.500 -0.5087 0.05772 0.05475 -0.0300 0.7578 0.0137
-7.250 -0.5042 0.05492 0.05182 -0.0290 0.7567 0.0140
-7.000 -0.4965 0.05221 0.04897 -0.0283 0.7552 0.0146
-6.750 -0.4861 0.04918 0.04580 -0.0277 0.7531 0.0154
-6.500 -0.4745 0.04606 0.04249 -0.0266 0.7512 0.0162
-6.250 -0.4597 0.04315 0.03934 -0.0252 0.7496 0.0176
-6.000 -0.4326 0.04350 0.03937 -0.0235 0.7481 0.0194
-5.750 -0.4330 0.03728 0.03267 -0.0204 0.7467 0.0202
-5.500 -0.4202 0.03378 0.02901 -0.0191 0.7454 0.0212
-5.250 -0.4017 0.03190 0.02702 -0.0182 0.7442 0.0221
-5.000 -0.3824 0.03021 0.02515 -0.0170 0.7432 0.0232
-4.750 -0.3611 0.02863 0.02335 -0.0159 0.7419 0.0250
-4.500 -0.3349 0.02756 0.02209 -0.0155 0.7395 0.0276
-4.250 -0.3061 0.02878 0.02308 -0.0148 0.7374 0.0295
-4.000 -0.2849 0.00917 0.00352 -0.0137 0.7325 0.0326
-3.750 -0.2581 0.02001 0.01359 -0.0119 0.7343 0.0177
-3.500 -0.2304 0.01745 0.01077 -0.0111 0.7330 0.0150
-3.250 -0.2049 0.01624 0.00946 -0.0103 0.7318 0.0150
-3.000 -0.1804 0.01545 0.00859 -0.0095 0.7307 0.0156
-2.750 -0.1564 0.01481 0.00788 -0.0086 0.7297 0.0162
-2.500 -0.1318 0.01442 0.00741 -0.0080 0.7288 0.0175
-2.250 -0.1041 0.01414 0.00715 -0.0083 0.7256 0.0187
-2.000 -0.0785 0.01374 0.00669 -0.0080 0.7233 0.0191
-1.750 -0.0530 0.01336 0.00623 -0.0075 0.7215 0.0200
-1.500 -0.0273 0.01300 0.00581 -0.0070 0.7200 0.0281
-1.250 -0.0212 0.01088 0.00533 -0.0035 0.7185 0.4798
-1.000 -0.0169 0.00966 0.00519 0.0015 0.7173 0.7522
-0.750 0.0862 0.01018 0.00622 -0.0126 0.7173 0.9485
-0.500 0.1245 0.01039 0.00632 -0.0145 0.7164 0.9584
-0.250 0.1649 0.01040 0.00622 -0.0172 0.7153 0.9607
0.000 0.2078 0.01056 0.00637 -0.0207 0.7115 0.9645
0.250 0.2422 0.01064 0.00640 -0.0221 0.7088 0.9716
0.500 0.2838 0.01056 0.00627 -0.0251 0.7070 0.9739
0.750 0.3217 0.01047 0.00613 -0.0274 0.7054 0.9767
1.000 0.3571 0.01039 0.00600 -0.0291 0.7040 0.9805
1.250 0.3892 0.01033 0.00589 -0.0301 0.7028 0.9847
1.500 0.4284 0.01024 0.00578 -0.0328 0.7007 0.9868
1.750 0.4679 0.01024 0.00583 -0.0358 0.6974 0.9897
2.000 0.5052 0.01020 0.00579 -0.0381 0.6951 0.9933
2.250 0.5419 0.01005 0.00564 -0.0403 0.6931 0.9960
2.500 0.5791 0.00984 0.00543 -0.0425 0.6914 0.9987
2.750 0.6098 0.00965 0.00524 -0.0433 0.6897 1.0000
3.000 0.6352 0.00956 0.00517 -0.0431 0.6859 1.0000
3.250 0.6605 0.00939 0.00503 -0.0429 0.6809 1.0000
3.500 0.6840 0.00904 0.00464 -0.0419 0.6767 1.0000
3.750 0.7098 0.00890 0.00456 -0.0417 0.6707 1.0000
4.000 0.7352 0.00875 0.00444 -0.0414 0.6657 1.0000
4.250 0.7600 0.00858 0.00425 -0.0408 0.6616 1.0000
4.500 0.7868 0.00853 0.00428 -0.0410 0.6537 1.0000
4.750 0.8122 0.00840 0.00418 -0.0406 0.6471 1.0000
5.000 0.8382 0.00826 0.00406 -0.0404 0.6348 1.0000
5.250 0.8647 0.00823 0.00406 -0.0404 0.6191 1.0000
5.500 0.8912 0.00825 0.00410 -0.0404 0.6016 1.0000
5.750 0.9174 0.00834 0.00416 -0.0404 0.5777 1.0000
6.000 0.9438 0.00858 0.00434 -0.0406 0.5423 1.0000
6.250 0.9690 0.00961 0.00492 -0.0416 0.4512 1.0000
6.500 0.9892 0.01113 0.00598 -0.0423 0.3617 1.0000
6.750 0.9980 0.01316 0.00739 -0.0416 0.2499 1.0000
7.000 1.0019 0.01482 0.00867 -0.0396 0.1800 1.0000
7.250 0.9942 0.01650 0.01001 -0.0356 0.1202 1.0000
7.500 0.9775 0.01755 0.01091 -0.0289 0.0940 1.0000
7.750 0.9696 0.01854 0.01177 -0.0238 0.0741 1.0000
8.000 0.9722 0.01931 0.01251 -0.0203 0.0651 1.0000
8.250 0.9786 0.02001 0.01324 -0.0175 0.0589 1.0000
8.500 0.9861 0.02072 0.01396 -0.0150 0.0545 1.0000
8.750 0.9937 0.02149 0.01473 -0.0126 0.0488 1.0000
9.000 1.0055 0.02209 0.01536 -0.0107 0.0445 1.0000
9.250 1.0133 0.02295 0.01618 -0.0085 0.0379 1.0000
9.500 1.0250 0.02362 0.01681 -0.0069 0.0269 1.0000
9.750 1.0270 0.02495 0.01797 -0.0042 0.0111 1.0000
10.000 1.0334 0.02607 0.01911 -0.0020 0.0089 1.0000
10.250 1.0405 0.02719 0.02031 0.0000 0.0078 1.0000
10.500 1.0473 0.02840 0.02161 0.0019 0.0073 1.0000
10.750 1.0550 0.02958 0.02291 0.0037 0.0066 1.0000
11.000 1.0621 0.03084 0.02426 0.0053 0.0065 1.0000
11.250 1.0690 0.03217 0.02567 0.0070 0.0061 1.0000
11.500 1.0737 0.03371 0.02730 0.0086 0.0058 1.0000
11.750 1.0794 0.03526 0.02894 0.0101 0.0056 1.0000
12.000 1.0842 0.03694 0.03071 0.0116 0.0055 1.0000
12.250 1.0871 0.03883 0.03269 0.0131 0.0053 1.0000
12.500 1.0899 0.04081 0.03477 0.0145 0.0051 1.0000
12.750 1.0967 0.04246 0.03652 0.0156 0.0052 1.0000
13.000 1.0983 0.04466 0.03883 0.0170 0.0051 1.0000
13.250 1.1021 0.04670 0.04100 0.0181 0.0051 1.0000
13.500 1.1056 0.04884 0.04325 0.0192 0.0051 1.0000
13.750 1.1080 0.05117 0.04573 0.0204 0.0050 1.0000
14.000 1.1107 0.05353 0.04824 0.0213 0.0051 1.0000
14.250 1.1121 0.05612 0.05103 0.0221 0.0051 1.0000
14.500 1.1106 0.05914 0.05423 0.0230 0.0051 1.0000
14.750 1.1079 0.06244 0.05777 0.0237 0.0053 1.0000
15.000 1.1022 0.06623 0.06179 0.0241 0.0054 1.0000
15.250 1.0912 0.07085 0.06666 0.0242 0.0055 1.0000
15.500 1.0754 0.07641 0.07250 0.0238 0.0057 1.0000
15.750 1.0571 0.08258 0.07893 0.0227 0.0059 1.0000
16.000 1.0364 0.08946 0.08604 0.0208 0.0060 1.0000
16.250 1.0155 0.09679 0.09360 0.0181 0.0061 1.0000
16.500 0.9927 0.10498 0.10199 0.0146 0.0062 1.0000
16.750 0.9695 0.11377 0.11096 0.0104 0.0063 1.0000
17.000 0.9530 0.12163 0.11895 0.0063 0.0064 1.0000
17.250 0.9309 0.13144 0.12891 0.0010 0.0064 1.0000
17.500 0.9084 0.14209 0.13967 -0.0049 0.0065 1.0000
17.750 0.8845 0.15427 0.15197 -0.0115 0.0065 1.0000
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Polar data table (+)
Polar graphs
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