AH 79-K-132/20 (ah79k132-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-K-132/20 (ah79k132-il) Reynolds number: 200,000 Max Cl/Cd: 79.24 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k132-il-200000.txt Download as CSV file: xf-ah79k132-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-132/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1236 0.09102 0.08735 -0.0912 0.8765 0.0522
-10.500 -0.1350 0.08737 0.08373 -0.0950 0.8752 0.0529
-10.250 -0.1386 0.08340 0.07977 -0.0974 0.8739 0.0531
-10.000 -0.1281 0.07799 0.07436 -0.0960 0.8728 0.0548
-9.750 -0.1173 0.07513 0.07150 -0.0956 0.8714 0.0561
-9.250 -0.1713 0.07555 0.07173 -0.1089 0.8732 0.0556
-9.000 -0.1673 0.07284 0.06904 -0.1093 0.8714 0.0570
-8.750 -0.1716 0.06938 0.06564 -0.1112 0.8692 0.0580
-8.500 -0.1826 0.06578 0.06205 -0.1130 0.8668 0.0586
-8.250 -0.1963 0.06299 0.05926 -0.1126 0.8640 0.0594
-8.000 -0.2067 0.06030 0.05651 -0.1118 0.8615 0.0605
-7.750 -0.2144 0.05745 0.05354 -0.1112 0.8593 0.0624
-7.500 -0.2337 0.05653 0.05213 -0.1087 0.8561 0.0661
-7.250 -0.2336 0.05448 0.04980 -0.1066 0.8536 0.0664
-6.750 -0.2377 0.03766 0.03227 -0.1020 0.8488 0.0399
-6.500 -0.2296 0.03438 0.02862 -0.0998 0.8465 0.0392
-6.250 -0.2181 0.03161 0.02542 -0.0976 0.8444 0.0388
-6.000 -0.2027 0.02978 0.02320 -0.0958 0.8416 0.0401
-5.750 -0.1867 0.02785 0.02085 -0.0941 0.8386 0.0419
-5.500 -0.1670 0.02586 0.01864 -0.0931 0.8359 0.0434
-5.250 -0.1442 0.02486 0.01747 -0.0923 0.8334 0.0458
-5.000 -0.1196 0.02400 0.01638 -0.0915 0.8312 0.0492
-4.750 -0.0988 0.02334 0.01552 -0.0904 0.8279 0.0544
-4.500 -0.0780 0.02281 0.01504 -0.0896 0.8242 0.0608
-4.250 -0.0547 0.02208 0.01417 -0.0887 0.8211 0.0687
-4.000 -0.0303 0.02177 0.01384 -0.0881 0.8185 0.0777
-3.750 -0.0100 0.02152 0.01359 -0.0871 0.8150 0.0871
-3.500 0.0097 0.02142 0.01343 -0.0860 0.8105 0.0952
-3.250 0.0324 0.02102 0.01309 -0.0851 0.8073 0.1043
-3.000 0.0563 0.02073 0.01281 -0.0843 0.8048 0.1162
-2.750 0.0703 0.02070 0.01286 -0.0825 0.7988 0.1277
-2.500 0.0918 0.02047 0.01268 -0.0814 0.7950 0.1494
-2.250 0.1134 0.01984 0.01247 -0.0805 0.7925 0.2305
-2.000 0.1057 0.01853 0.01283 -0.0750 0.7851 0.6161
-1.750 0.1139 0.01890 0.01384 -0.0686 0.7815 0.8359
-1.500 0.1326 0.01940 0.01423 -0.0652 0.7791 0.8775
-1.250 0.1347 0.02003 0.01486 -0.0601 0.7710 0.9017
-1.000 0.1629 0.02031 0.01503 -0.0585 0.7680 0.9268
-0.750 0.2330 0.02055 0.01511 -0.0654 0.7671 0.9473
-0.500 0.4035 0.02042 0.01473 -0.0925 0.7692 0.9746
-0.250 0.4636 0.02019 0.01437 -0.0990 0.7672 0.9851
0.000 0.5139 0.01993 0.01401 -0.1036 0.7652 0.9916
0.250 0.5452 0.02004 0.01413 -0.1056 0.7583 0.9964
0.500 0.5812 0.01987 0.01392 -0.1076 0.7546 1.0000
0.750 0.6039 0.01976 0.01375 -0.1066 0.7519 1.0000
1.000 0.6161 0.02008 0.01410 -0.1046 0.7443 1.0000
1.250 0.6371 0.01997 0.01397 -0.1034 0.7403 1.0000
1.500 0.6614 0.01974 0.01370 -0.1025 0.7379 1.0000
1.750 0.6717 0.02010 0.01410 -0.1001 0.7294 1.0000
2.000 0.6949 0.01986 0.01385 -0.0991 0.7261 1.0000
2.250 0.7207 0.01952 0.01349 -0.0985 0.7239 1.0000
2.500 0.7298 0.01989 0.01393 -0.0958 0.7148 1.0000
2.750 0.7548 0.01954 0.01357 -0.0950 0.7120 1.0000
3.000 0.7815 0.01910 0.01311 -0.0945 0.7099 1.0000
3.250 0.7905 0.01943 0.01351 -0.0916 0.7006 1.0000
3.500 0.8171 0.01893 0.01304 -0.0910 0.6979 1.0000
3.750 0.8316 0.01896 0.01311 -0.0888 0.6907 1.0000
4.000 0.8557 0.01849 0.01268 -0.0878 0.6863 1.0000
4.250 0.8849 0.01782 0.01202 -0.0875 0.6839 1.0000
4.500 0.8975 0.01784 0.01214 -0.0849 0.6754 1.0000
4.750 0.9252 0.01722 0.01154 -0.0844 0.6718 1.0000
5.000 0.9534 0.01660 0.01096 -0.0840 0.6681 1.0000
5.250 0.9673 0.01652 0.01096 -0.0815 0.6594 1.0000
5.500 0.9998 0.01574 0.01023 -0.0817 0.6557 1.0000
5.750 1.0131 0.01557 0.01014 -0.0789 0.6450 1.0000
6.000 1.0325 0.01514 0.00976 -0.0770 0.6344 1.0000
6.250 1.0544 0.01471 0.00936 -0.0755 0.6236 1.0000
6.500 1.0749 0.01438 0.00906 -0.0738 0.6112 1.0000
6.750 1.0919 0.01422 0.00891 -0.0715 0.5966 1.0000
7.000 1.1066 0.01419 0.00891 -0.0689 0.5806 1.0000
7.250 1.1211 0.01424 0.00896 -0.0664 0.5643 1.0000
7.500 1.1368 0.01437 0.00909 -0.0641 0.5476 1.0000
7.750 1.1537 0.01456 0.00926 -0.0622 0.5299 1.0000
8.000 1.1651 0.01489 0.00960 -0.0594 0.5071 1.0000
8.250 1.1725 0.01533 0.00992 -0.0559 0.4763 1.0000
8.500 1.1733 0.01594 0.01038 -0.0515 0.4418 1.0000
8.750 1.1692 0.01675 0.01106 -0.0466 0.4066 1.0000
9.000 1.1639 0.01786 0.01198 -0.0421 0.3693 1.0000
9.250 1.1590 0.01929 0.01322 -0.0386 0.3322 1.0000
9.500 1.1521 0.02105 0.01473 -0.0352 0.2888 1.0000
9.750 1.1446 0.02297 0.01638 -0.0319 0.2423 1.0000
10.000 1.1359 0.02509 0.01819 -0.0286 0.1930 1.0000
10.250 1.1260 0.02745 0.02019 -0.0256 0.1390 1.0000
10.500 1.1072 0.03062 0.02280 -0.0220 0.0692 1.0000
10.750 1.0895 0.03398 0.02587 -0.0185 0.0396 1.0000
11.000 1.0857 0.03641 0.02832 -0.0164 0.0294 1.0000
11.250 1.0855 0.03861 0.03061 -0.0147 0.0253 1.0000
11.500 1.0899 0.04048 0.03254 -0.0135 0.0222 1.0000
11.750 1.0887 0.04292 0.03505 -0.0121 0.0208 1.0000
12.000 1.0823 0.04599 0.03819 -0.0105 0.0193 1.0000
12.250 1.0865 0.04812 0.04043 -0.0095 0.0188 1.0000
12.500 1.0921 0.05018 0.04258 -0.0085 0.0185 1.0000
12.750 1.0995 0.05214 0.04466 -0.0074 0.0179 1.0000
13.000 1.1089 0.05398 0.04658 -0.0063 0.0171 1.0000
13.250 1.1221 0.05558 0.04828 -0.0052 0.0168 1.0000
13.500 1.1381 0.05719 0.05002 -0.0040 0.0166 1.0000
13.750 1.1532 0.05906 0.05206 -0.0031 0.0164 1.0000
14.000 1.1683 0.06139 0.05462 -0.0021 0.0165 1.0000
14.250 1.1785 0.06436 0.05785 -0.0012 0.0167 1.0000
14.500 1.1816 0.06795 0.06173 -0.0005 0.0170 1.0000
14.750 1.1790 0.07194 0.06600 0.0000 0.0173 1.0000
15.000 1.1713 0.07645 0.07078 0.0002 0.0177 1.0000
15.250 1.1607 0.08121 0.07579 -0.0001 0.0180 1.0000
15.500 1.1467 0.08654 0.08137 -0.0007 0.0182 1.0000
15.750 1.1330 0.09183 0.08687 -0.0018 0.0185 1.0000
16.000 1.1153 0.09792 0.09319 -0.0036 0.0186 1.0000
16.250 1.0990 0.10415 0.09960 -0.0057 0.0189 1.0000
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