AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 A AIRFOIL (ah79100a-il) Reynolds number: 100,000 Max Cl/Cd: 62.18 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100a-il-100000-n5.txt Download as CSV file: xf-ah79100a-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3788 0.09368 0.08857 -0.0415 1.0000 0.0293
-9.000 -0.3840 0.08948 0.08446 -0.0426 1.0000 0.0287
-8.750 -0.3912 0.08533 0.08040 -0.0436 1.0000 0.0286
-8.250 -0.4397 0.07275 0.06808 -0.0464 1.0000 0.0268
-8.000 -0.4570 0.06874 0.06417 -0.0464 1.0000 0.0267
-7.750 -0.4717 0.06394 0.05943 -0.0485 1.0000 0.0265
-7.500 -0.4836 0.05791 0.05336 -0.0539 1.0000 0.0262
-7.250 -0.4804 0.04865 0.04361 -0.0651 0.9966 0.0263
-7.000 -0.4531 0.04106 0.03532 -0.0752 0.9904 0.0274
-6.750 -0.4240 0.03913 0.03328 -0.0784 0.9859 0.0292
-6.500 -0.3922 0.03480 0.02837 -0.0833 0.9814 0.0306
-6.250 -0.3599 0.03101 0.02393 -0.0868 0.9772 0.0319
-6.000 -0.3269 0.02825 0.02045 -0.0893 0.9727 0.0343
-5.750 -0.2934 0.02632 0.01834 -0.0917 0.9692 0.0372
-5.500 -0.2617 0.02477 0.01654 -0.0931 0.9647 0.0398
-5.250 -0.2293 0.02346 0.01491 -0.0944 0.9598 0.0437
-5.000 -0.1947 0.02209 0.01343 -0.0962 0.9562 0.0476
-4.750 -0.1620 0.02108 0.01233 -0.0975 0.9516 0.0514
-4.500 -0.1303 0.02024 0.01137 -0.0984 0.9459 0.0578
-4.250 -0.0943 0.01938 0.01047 -0.1004 0.9418 0.0650
-4.000 -0.0609 0.01863 0.00965 -0.1018 0.9367 0.0756
-3.750 -0.0285 0.01796 0.00897 -0.1029 0.9307 0.0932
-3.500 0.0083 0.01716 0.00831 -0.1052 0.9269 0.1303
-3.250 0.0401 0.01638 0.00787 -0.1065 0.9214 0.2123
-3.000 0.0711 0.01592 0.00770 -0.1074 0.9153 0.3043
-2.750 0.1065 0.01569 0.00761 -0.1089 0.9111 0.3779
-2.500 0.1345 0.01564 0.00759 -0.1088 0.9035 0.4238
-2.250 0.1674 0.01556 0.00750 -0.1096 0.8979 0.4609
-2.000 0.1978 0.01551 0.00745 -0.1098 0.8913 0.4931
-1.750 0.2280 0.01545 0.00735 -0.1100 0.8842 0.5192
-1.500 0.2601 0.01534 0.00722 -0.1105 0.8783 0.5412
-1.250 0.2883 0.01529 0.00713 -0.1104 0.8700 0.5610
-1.000 0.3204 0.01515 0.00697 -0.1108 0.8641 0.5792
-0.750 0.3473 0.01509 0.00691 -0.1104 0.8550 0.5968
-0.500 0.3779 0.01497 0.00678 -0.1106 0.8477 0.6149
-0.250 0.4067 0.01487 0.00668 -0.1104 0.8387 0.6322
0.000 0.4351 0.01478 0.00660 -0.1102 0.8295 0.6507
0.250 0.4653 0.01463 0.00647 -0.1102 0.8216 0.6703
0.500 0.4916 0.01456 0.00646 -0.1097 0.8110 0.6914
0.750 0.5198 0.01444 0.00639 -0.1093 0.8018 0.7148
1.000 0.5477 0.01428 0.00630 -0.1089 0.7918 0.7426
1.250 0.5726 0.01413 0.00627 -0.1079 0.7799 0.7782
1.500 0.5979 0.01387 0.00621 -0.1068 0.7683 0.8401
1.750 0.6309 0.01368 0.00608 -0.1074 0.7569 1.0000
2.000 0.6607 0.01372 0.00605 -0.1076 0.7457 1.0000
2.250 0.6888 0.01381 0.00609 -0.1075 0.7324 1.0000
2.500 0.7166 0.01390 0.00615 -0.1073 0.7183 1.0000
2.750 0.7443 0.01400 0.00622 -0.1070 0.7038 1.0000
3.000 0.7718 0.01412 0.00631 -0.1067 0.6892 1.0000
3.250 0.7992 0.01426 0.00644 -0.1064 0.6742 1.0000
3.500 0.8263 0.01440 0.00656 -0.1060 0.6582 1.0000
3.750 0.8529 0.01457 0.00670 -0.1055 0.6410 1.0000
4.000 0.8791 0.01477 0.00690 -0.1050 0.6233 1.0000
4.250 0.9049 0.01499 0.00713 -0.1044 0.6042 1.0000
4.500 0.9305 0.01522 0.00731 -0.1036 0.5836 1.0000
4.750 0.9549 0.01550 0.00757 -0.1028 0.5598 1.0000
5.000 0.9795 0.01581 0.00783 -0.1020 0.5375 1.0000
5.250 1.0035 0.01615 0.00820 -0.1011 0.5144 1.0000
5.500 1.0272 0.01652 0.00856 -0.1002 0.4915 1.0000
5.750 1.0499 0.01693 0.00895 -0.0992 0.4650 1.0000
6.000 1.0719 0.01737 0.00939 -0.0980 0.4360 1.0000
6.250 1.0928 0.01789 0.00985 -0.0968 0.4036 1.0000
6.500 1.1127 0.01848 0.01036 -0.0954 0.3676 1.0000
6.750 1.1312 0.01919 0.01094 -0.0939 0.3290 1.0000
7.000 1.1489 0.01998 0.01162 -0.0923 0.2889 1.0000
7.250 1.1652 0.02092 0.01241 -0.0907 0.2469 1.0000
7.500 1.1799 0.02201 0.01329 -0.0889 0.2036 1.0000
7.750 1.1929 0.02327 0.01430 -0.0870 0.1603 1.0000
8.000 1.2057 0.02458 0.01539 -0.0851 0.1249 1.0000
8.250 1.2184 0.02587 0.01655 -0.0833 0.0973 1.0000
8.500 1.2299 0.02725 0.01783 -0.0812 0.0758 1.0000
8.750 1.2408 0.02863 0.01919 -0.0791 0.0604 1.0000
9.000 1.2482 0.03012 0.02066 -0.0765 0.0502 1.0000
9.250 1.2552 0.03162 0.02219 -0.0739 0.0432 1.0000
9.500 1.2613 0.03320 0.02387 -0.0713 0.0385 1.0000
9.750 1.2671 0.03484 0.02562 -0.0689 0.0353 1.0000
10.000 1.2700 0.03675 0.02760 -0.0664 0.0331 1.0000
10.250 1.2744 0.03869 0.02967 -0.0642 0.0313 1.0000
10.500 1.2809 0.04054 0.03173 -0.0623 0.0293 1.0000
10.750 1.2866 0.04247 0.03378 -0.0606 0.0275 1.0000
11.000 1.2911 0.04455 0.03595 -0.0591 0.0261 1.0000
11.250 1.2933 0.04705 0.03850 -0.0576 0.0250 1.0000
11.500 1.3001 0.04938 0.04102 -0.0562 0.0242 1.0000
11.750 1.3068 0.05184 0.04370 -0.0549 0.0235 1.0000
12.000 1.3126 0.05450 0.04658 -0.0537 0.0229 1.0000
12.250 1.3167 0.05738 0.04969 -0.0526 0.0223 1.0000
12.500 1.3189 0.06048 0.05302 -0.0517 0.0218 1.0000
12.750 1.3186 0.06386 0.05664 -0.0510 0.0214 1.0000
13.000 1.3156 0.06749 0.06053 -0.0507 0.0209 1.0000
13.250 1.3105 0.07134 0.06461 -0.0507 0.0205 1.0000
13.500 1.3038 0.07553 0.06901 -0.0511 0.0202 1.0000
13.750 1.2958 0.07994 0.07361 -0.0519 0.0199 1.0000
14.000 1.2863 0.08473 0.07859 -0.0532 0.0196 1.0000
14.250 1.2758 0.08989 0.08393 -0.0549 0.0193 1.0000
14.500 1.2634 0.09561 0.08984 -0.0572 0.0191 1.0000
14.750 1.2490 0.10201 0.09645 -0.0602 0.0190 1.0000
15.000 1.2325 0.10923 0.10390 -0.0640 0.0190 1.0000
15.250 1.2131 0.11758 0.11249 -0.0691 0.0191 1.0000
15.500 1.1778 0.13101 0.12631 -0.0782 0.0197 1.0000
15.750 1.0903 0.16531 0.16096 -0.1010 0.0225 1.0000
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