AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 A AIRFOIL (ah79100a-il) Reynolds number: 50,000 Max Cl/Cd: 39.81 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100a-il-50000.txt Download as CSV file: xf-ah79100a-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2779 0.11407 0.10752 -0.0321 1.0000 0.2145
-9.750 -0.2579 0.10888 0.10232 -0.0308 1.0000 0.2253
-9.500 -0.2796 0.10891 0.10249 -0.0313 1.0000 0.2295
-9.250 -0.2569 0.10347 0.09702 -0.0297 1.0000 0.2407
-9.000 -0.2674 0.10162 0.09528 -0.0295 1.0000 0.2458
-8.750 -0.2565 0.09794 0.09162 -0.0282 1.0000 0.2556
-8.500 -0.2675 0.09604 0.08983 -0.0275 1.0000 0.2610
-8.250 -0.2594 0.09271 0.08653 -0.0260 1.0000 0.2709
-8.000 -0.2652 0.09026 0.08417 -0.0248 1.0000 0.2773
-7.750 -0.2722 0.08856 0.08257 -0.0230 1.0000 0.2878
-7.500 -0.2646 0.08513 0.07917 -0.0211 1.0000 0.2984
-7.250 -0.2961 0.08548 0.07971 -0.0186 1.0000 0.3041
-7.000 -0.2830 0.08156 0.07580 -0.0166 1.0000 0.3175
-6.750 -0.2807 0.07841 0.07271 -0.0147 1.0000 0.3250
-6.500 -0.3073 0.07836 0.07282 -0.0114 1.0000 0.3337
-6.250 -0.3666 0.08619 0.08011 -0.0103 1.0000 0.3389
-6.000 -0.3971 0.08671 0.08081 -0.0071 1.0000 0.3490
-5.750 -0.3813 0.08264 0.07675 -0.0044 1.0000 0.3590
-5.500 -0.3929 0.08089 0.07512 -0.0022 1.0000 0.3678
-5.250 -0.4095 0.07990 0.07425 -0.0008 1.0000 0.3801
-5.000 -0.3688 0.04756 0.04062 -0.0615 1.0000 0.1438
-4.750 -0.3351 0.04127 0.03348 -0.0678 1.0000 0.1380
-4.500 -0.3035 0.03687 0.02841 -0.0711 1.0000 0.1374
-4.250 -0.2739 0.03379 0.02481 -0.0730 1.0000 0.1435
-4.000 -0.2456 0.03149 0.02216 -0.0738 1.0000 0.1501
-3.750 -0.2157 0.02929 0.01948 -0.0746 1.0000 0.1583
-3.500 -0.1896 0.02783 0.01790 -0.0747 1.0000 0.1742
-3.250 -0.1636 0.02644 0.01641 -0.0745 1.0000 0.1937
-3.000 -0.1380 0.02528 0.01528 -0.0743 1.0000 0.2280
-2.750 -0.1128 0.02424 0.01466 -0.0740 1.0000 0.2930
-2.500 -0.0923 0.02392 0.01512 -0.0719 1.0000 0.4285
-2.250 -0.0800 0.02434 0.01585 -0.0679 1.0000 0.5214
-2.000 -0.0681 0.02464 0.01626 -0.0641 1.0000 0.5836
-1.750 -0.0545 0.02476 0.01638 -0.0610 1.0000 0.6371
-1.500 -0.0424 0.02475 0.01639 -0.0576 1.0000 0.6835
-1.250 -0.0297 0.02463 0.01629 -0.0546 1.0000 0.7281
-1.000 -0.0162 0.02445 0.01607 -0.0520 1.0000 0.7713
-0.750 -0.0027 0.02418 0.01582 -0.0496 1.0000 0.8149
-0.500 0.0101 0.02379 0.01552 -0.0472 1.0000 0.8671
-0.250 0.0281 0.02325 0.01511 -0.0478 1.0000 1.0000
0.000 0.0698 0.02396 0.01543 -0.0541 1.0000 1.0000
0.250 0.1045 0.02474 0.01588 -0.0584 1.0000 1.0000
0.500 0.1335 0.02558 0.01644 -0.0613 1.0000 1.0000
0.750 0.1740 0.02676 0.01734 -0.0660 0.9929 1.0000
1.000 0.2272 0.02821 0.01851 -0.0726 0.9795 1.0000
1.250 0.2712 0.02938 0.01951 -0.0774 0.9648 1.0000
1.500 0.3142 0.03054 0.02052 -0.0817 0.9502 1.0000
1.750 0.3557 0.03164 0.02151 -0.0855 0.9352 1.0000
2.000 0.3959 0.03269 0.02248 -0.0889 0.9199 1.0000
2.250 0.4343 0.03367 0.02341 -0.0918 0.9044 1.0000
2.500 0.4710 0.03463 0.02435 -0.0943 0.8892 1.0000
2.750 0.5066 0.03557 0.02530 -0.0966 0.8740 1.0000
3.000 0.5417 0.03645 0.02620 -0.0985 0.8584 1.0000
3.250 0.5766 0.03729 0.02708 -0.1003 0.8424 1.0000
3.500 0.6114 0.03807 0.02791 -0.1019 0.8263 1.0000
3.750 0.6466 0.03880 0.02874 -0.1033 0.8102 1.0000
4.000 0.6818 0.03944 0.02948 -0.1046 0.7942 1.0000
4.250 0.7187 0.03995 0.03011 -0.1059 0.7781 1.0000
4.500 0.7585 0.04020 0.03054 -0.1072 0.7620 1.0000
4.750 0.7925 0.04052 0.03101 -0.1075 0.7446 1.0000
5.000 0.8176 0.04114 0.03178 -0.1069 0.7256 1.0000
5.250 0.8556 0.04103 0.03190 -0.1072 0.7076 1.0000
5.500 0.9068 0.03979 0.03092 -0.1078 0.6901 1.0000
5.750 0.9644 0.03753 0.02899 -0.1080 0.6725 1.0000
6.000 0.9918 0.03718 0.02884 -0.1061 0.6488 1.0000
6.250 1.0520 0.03409 0.02602 -0.1055 0.6269 1.0000
6.500 1.0890 0.03275 0.02491 -0.1036 0.5991 1.0000
6.750 1.1252 0.03141 0.02367 -0.1014 0.5666 1.0000
7.000 1.1524 0.03070 0.02303 -0.0986 0.5277 1.0000
7.250 1.1771 0.03014 0.02244 -0.0954 0.4825 1.0000
7.500 1.1959 0.03004 0.02215 -0.0919 0.4310 1.0000
7.750 1.2092 0.03054 0.02230 -0.0881 0.3743 1.0000
8.000 1.2167 0.03181 0.02319 -0.0842 0.3165 1.0000
8.250 1.2220 0.03364 0.02465 -0.0804 0.2627 1.0000
8.500 1.2286 0.03581 0.02638 -0.0772 0.2158 1.0000
8.750 1.2379 0.03836 0.02868 -0.0746 0.1775 1.0000
9.000 1.2531 0.04118 0.03133 -0.0727 0.1480 1.0000
9.250 1.2772 0.04451 0.03446 -0.0720 0.1272 1.0000
9.500 1.2983 0.04781 0.03784 -0.0710 0.1139 1.0000
9.750 1.3140 0.05128 0.04178 -0.0692 0.1066 1.0000
10.000 1.3309 0.05513 0.04577 -0.0681 0.1002 1.0000
10.250 1.3324 0.05876 0.04999 -0.0653 0.0967 1.0000
10.500 1.3341 0.06272 0.05439 -0.0629 0.0944 1.0000
10.750 1.3307 0.06698 0.05906 -0.0604 0.0935 1.0000
11.000 1.3196 0.07132 0.06380 -0.0577 0.0934 1.0000
11.250 1.2995 0.07554 0.06837 -0.0546 0.0938 1.0000
11.500 1.2740 0.08004 0.07317 -0.0522 0.0945 1.0000
11.750 1.2454 0.08517 0.07855 -0.0512 0.0956 1.0000
12.000 1.2152 0.09112 0.08472 -0.0517 0.0968 1.0000
12.250 1.1846 0.09802 0.09179 -0.0538 0.0981 1.0000
12.500 1.1563 0.10579 0.09967 -0.0572 0.0995 1.0000
12.750 1.1346 0.11391 0.10785 -0.0610 0.1007 1.0000
13.000 1.1234 0.12161 0.11558 -0.0640 0.1017 1.0000
13.250 1.0228 0.15403 0.14780 -0.0900 0.1304 1.0000
13.500 0.7625 0.16861 0.16288 -0.0947 0.2710 1.0000
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