AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 200,000 Max Cl/Cd: 74.42 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k135-il-200000-n5.txt Download as CSV file: xf-ah79k135-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-135/20 B
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2135 0.10840 0.10423 -0.0677 0.8093 0.0314
-11.750 -0.2126 0.10067 0.09646 -0.0681 0.8087 0.0182
-11.500 -0.2754 0.10303 0.09846 -0.0759 0.8140 0.0181
-11.250 -0.2710 0.09986 0.09530 -0.0771 0.8131 0.0175
-11.000 -0.2698 0.09586 0.09134 -0.0787 0.8122 0.0170
-10.750 -0.2702 0.09162 0.08713 -0.0807 0.8111 0.0165
-10.500 -0.2743 0.08661 0.08216 -0.0830 0.8100 0.0159
-10.250 -0.3080 0.07243 0.06808 -0.0904 0.8085 0.0139
-10.000 -0.3153 0.06643 0.06211 -0.0949 0.8068 0.0137
-9.750 -0.3348 0.05957 0.05517 -0.0994 0.8051 0.0136
-9.500 -0.3549 0.05490 0.05040 -0.1004 0.8036 0.0135
-9.250 -0.3733 0.05132 0.04668 -0.0991 0.8020 0.0134
-9.000 -0.3909 0.04854 0.04377 -0.0961 0.8004 0.0132
-8.750 -0.4033 0.04524 0.04027 -0.0933 0.7984 0.0131
-8.500 -0.4104 0.04193 0.03670 -0.0907 0.7964 0.0130
-8.250 -0.4134 0.03856 0.03299 -0.0880 0.7947 0.0129
-8.000 -0.4111 0.03545 0.02951 -0.0855 0.7931 0.0127
-7.750 -0.4042 0.03259 0.02621 -0.0832 0.7915 0.0127
-7.500 -0.3927 0.03006 0.02326 -0.0813 0.7899 0.0127
-7.250 -0.3769 0.02796 0.02075 -0.0797 0.7887 0.0127
-7.000 -0.3583 0.02617 0.01861 -0.0785 0.7874 0.0128
-6.750 -0.3377 0.02468 0.01687 -0.0775 0.7856 0.0130
-6.500 -0.3159 0.02344 0.01543 -0.0767 0.7837 0.0132
-6.250 -0.2934 0.02236 0.01417 -0.0759 0.7819 0.0135
-6.000 -0.2707 0.02147 0.01312 -0.0752 0.7802 0.0139
-5.750 -0.2495 0.02048 0.01206 -0.0743 0.7785 0.0145
-5.500 -0.2274 0.01978 0.01130 -0.0735 0.7769 0.0152
-5.250 -0.2043 0.01928 0.01073 -0.0729 0.7755 0.0168
-5.000 -0.1810 0.01883 0.01017 -0.0722 0.7741 0.0184
-4.750 -0.1596 0.01826 0.00960 -0.0714 0.7717 0.0204
-4.500 -0.1368 0.01784 0.00913 -0.0706 0.7694 0.0228
-4.250 -0.1139 0.01740 0.00870 -0.0699 0.7671 0.0282
-4.000 -0.0905 0.01701 0.00830 -0.0692 0.7651 0.0433
-3.750 -0.0668 0.01666 0.00802 -0.0687 0.7633 0.0653
-3.500 -0.0436 0.01623 0.00775 -0.0682 0.7616 0.1007
-3.250 -0.0218 0.01567 0.00750 -0.0674 0.7601 0.1721
-3.000 -0.0018 0.01522 0.00738 -0.0666 0.7568 0.2519
-2.750 0.0169 0.01459 0.00721 -0.0654 0.7538 0.3715
-2.500 0.0339 0.01388 0.00707 -0.0637 0.7513 0.5202
-2.250 0.0526 0.01342 0.00713 -0.0616 0.7492 0.6582
-2.000 0.0762 0.01339 0.00731 -0.0600 0.7475 0.7375
-1.750 0.1016 0.01349 0.00740 -0.0590 0.7460 0.7791
-1.500 0.1220 0.01379 0.00773 -0.0572 0.7417 0.8142
-1.250 0.1442 0.01403 0.00796 -0.0555 0.7385 0.8399
-1.000 0.1661 0.01422 0.00810 -0.0538 0.7360 0.8611
-0.750 0.1895 0.01436 0.00817 -0.0523 0.7340 0.8764
-0.500 0.2153 0.01441 0.00815 -0.0513 0.7324 0.8871
-0.250 0.2372 0.01456 0.00830 -0.0501 0.7278 0.8957
0.000 0.2595 0.01458 0.00828 -0.0491 0.7240 0.9041
0.250 0.2877 0.01451 0.00816 -0.0490 0.7214 0.9085
0.500 0.3158 0.01440 0.00799 -0.0490 0.7193 0.9132
0.750 0.3403 0.01430 0.00784 -0.0483 0.7167 0.9193
1.000 0.3654 0.01437 0.00794 -0.0481 0.7111 0.9233
1.250 0.3930 0.01426 0.00780 -0.0481 0.7077 0.9273
1.500 0.4190 0.01410 0.00760 -0.0478 0.7053 0.9319
1.750 0.4475 0.01400 0.00751 -0.0480 0.7019 0.9350
2.000 0.4736 0.01404 0.00757 -0.0480 0.6961 0.9386
2.250 0.5020 0.01389 0.00743 -0.0482 0.6927 0.9421
2.500 0.5294 0.01368 0.00720 -0.0481 0.6900 0.9460
2.750 0.5559 0.01376 0.00735 -0.0483 0.6831 0.9493
3.000 0.5867 0.01362 0.00722 -0.0490 0.6788 0.9519
3.250 0.6179 0.01341 0.00702 -0.0497 0.6753 0.9547
3.500 0.6401 0.01347 0.00717 -0.0490 0.6673 0.9596
3.750 0.6732 0.01326 0.00698 -0.0501 0.6627 0.9616
4.000 0.7035 0.01329 0.00709 -0.0510 0.6544 0.9642
4.250 0.7367 0.01306 0.00689 -0.0521 0.6482 0.9665
4.500 0.7651 0.01304 0.00694 -0.0525 0.6378 0.9699
4.750 0.7940 0.01294 0.00688 -0.0529 0.6283 0.9732
5.000 0.8277 0.01281 0.00677 -0.0541 0.6185 0.9751
5.250 0.8599 0.01276 0.00677 -0.0552 0.6067 0.9775
5.500 0.8908 0.01272 0.00675 -0.0560 0.5922 0.9803
5.750 0.9194 0.01274 0.00677 -0.0564 0.5735 0.9834
6.000 0.9484 0.01284 0.00680 -0.0569 0.5479 0.9862
6.250 0.9757 0.01311 0.00696 -0.0572 0.5138 0.9896
6.500 0.9977 0.01356 0.00724 -0.0567 0.4741 0.9950
6.750 1.0095 0.01405 0.00761 -0.0542 0.4417 1.0000
7.000 1.0058 0.01450 0.00795 -0.0487 0.4128 1.0000
7.250 1.0028 0.01510 0.00838 -0.0436 0.3784 1.0000
7.500 0.9989 0.01584 0.00894 -0.0386 0.3423 1.0000
7.750 0.9932 0.01690 0.00973 -0.0339 0.2971 1.0000
8.000 0.9890 0.01824 0.01080 -0.0301 0.2497 1.0000
8.250 0.9831 0.02000 0.01220 -0.0268 0.1933 1.0000
8.500 0.9829 0.02159 0.01350 -0.0242 0.1460 1.0000
8.750 0.9834 0.02321 0.01484 -0.0218 0.1014 1.0000
9.000 0.9818 0.02504 0.01635 -0.0193 0.0549 1.0000
9.250 0.9866 0.02651 0.01773 -0.0174 0.0338 1.0000
9.500 0.9935 0.02789 0.01904 -0.0157 0.0221 1.0000
9.750 1.0021 0.02918 0.02035 -0.0142 0.0187 1.0000
10.000 1.0123 0.03037 0.02165 -0.0130 0.0172 1.0000
10.250 1.0216 0.03166 0.02303 -0.0117 0.0161 1.0000
10.500 1.0297 0.03305 0.02452 -0.0104 0.0154 1.0000
10.750 1.0349 0.03471 0.02627 -0.0090 0.0145 1.0000
11.000 1.0415 0.03629 0.02797 -0.0078 0.0137 1.0000
11.250 1.0481 0.03790 0.02970 -0.0067 0.0134 1.0000
11.500 1.0552 0.03950 0.03140 -0.0057 0.0126 1.0000
11.750 1.0599 0.04135 0.03335 -0.0046 0.0122 1.0000
12.000 1.0643 0.04329 0.03539 -0.0037 0.0119 1.0000
12.250 1.0684 0.04533 0.03753 -0.0028 0.0117 1.0000
12.500 1.0726 0.04745 0.03974 -0.0020 0.0115 1.0000
12.750 1.0766 0.04964 0.04201 -0.0014 0.0112 1.0000
13.000 1.0804 0.05191 0.04439 -0.0008 0.0110 1.0000
13.250 1.0848 0.05417 0.04673 -0.0003 0.0109 1.0000
13.500 1.0889 0.05651 0.04914 0.0003 0.0107 1.0000
13.750 1.0940 0.05883 0.05152 0.0010 0.0104 1.0000
14.000 1.1015 0.06095 0.05376 0.0014 0.0103 1.0000
14.250 1.1088 0.06313 0.05607 0.0018 0.0103 1.0000
14.500 1.1155 0.06546 0.05856 0.0022 0.0102 1.0000
14.750 1.1215 0.06793 0.06118 0.0024 0.0101 1.0000
15.000 1.1258 0.07069 0.06412 0.0025 0.0100 1.0000
15.250 1.1285 0.07371 0.06733 0.0025 0.0099 1.0000
15.500 1.1282 0.07714 0.07096 0.0021 0.0097 1.0000
15.750 1.1263 0.08086 0.07492 0.0015 0.0096 1.0000
16.000 1.1223 0.08495 0.07922 0.0005 0.0095 1.0000
16.250 1.1168 0.08939 0.08388 -0.0006 0.0094 1.0000
16.500 1.1101 0.09403 0.08870 -0.0024 0.0091 1.0000
16.750 1.1012 0.09929 0.09418 -0.0043 0.0092 1.0000
17.000 1.0920 0.10472 0.09981 -0.0066 0.0090 1.0000
17.250 1.0799 0.11089 0.10619 -0.0095 0.0090 1.0000
17.500 1.0690 0.11699 0.11247 -0.0127 0.0088 1.0000
17.750 1.0542 0.12418 0.11987 -0.0166 0.0089 1.0000
18.000 1.0385 0.13193 0.12782 -0.0210 0.0089 1.0000
18.250 1.0198 0.14080 0.13690 -0.0263 0.0090 1.0000
18.500 1.0021 0.14996 0.14623 -0.0320 0.0091 1.0000
18.750 0.9800 0.16098 0.15743 -0.0389 0.0092 1.0000
19.000 0.9519 0.17502 0.17160 -0.0473 0.0095 1.0000
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Polar data table (+)
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