AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 A AIRFOIL (ah79100a-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.44 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100a-il-1000000-n5.txt Download as CSV file: xf-ah79100a-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6173 0.09003 0.08815 -0.0439 1.0000 0.0058
-12.750 -0.8053 0.05231 0.05013 -0.0665 1.0000 0.0053
-12.500 -0.8582 0.04171 0.03938 -0.0726 1.0000 0.0052
-12.000 -0.8504 0.02745 0.02455 -0.0950 0.9952 0.0053
-11.750 -0.8254 0.02518 0.02209 -0.0986 0.9905 0.0054
-11.500 -0.8000 0.02315 0.01984 -0.1015 0.9859 0.0055
-11.250 -0.7722 0.02153 0.01804 -0.1038 0.9824 0.0056
-11.000 -0.7424 0.02005 0.01639 -0.1063 0.9802 0.0057
-10.750 -0.7138 0.01890 0.01509 -0.1079 0.9765 0.0058
-10.500 -0.6844 0.01782 0.01387 -0.1095 0.9725 0.0059
-10.250 -0.6537 0.01690 0.01281 -0.1111 0.9691 0.0060
-10.000 -0.6246 0.01605 0.01183 -0.1123 0.9643 0.0061
-9.750 -0.5961 0.01507 0.01071 -0.1133 0.9584 0.0062
-9.500 -0.5674 0.01421 0.00972 -0.1143 0.9530 0.0065
-9.250 -0.5405 0.01356 0.00898 -0.1146 0.9457 0.0067
-9.000 -0.5129 0.01300 0.00833 -0.1149 0.9391 0.0069
-8.750 -0.4863 0.01252 0.00776 -0.1150 0.9315 0.0072
-8.500 -0.4594 0.01209 0.00724 -0.1151 0.9246 0.0075
-8.250 -0.4326 0.01167 0.00674 -0.1151 0.9175 0.0078
-8.000 -0.4057 0.01128 0.00626 -0.1151 0.9109 0.0082
-7.750 -0.3787 0.01092 0.00583 -0.1151 0.9043 0.0085
-7.500 -0.3518 0.01054 0.00536 -0.1150 0.8967 0.0091
-7.250 -0.3248 0.01025 0.00503 -0.1149 0.8880 0.0101
-7.000 -0.2978 0.01001 0.00472 -0.1148 0.8790 0.0110
-6.750 -0.2704 0.00977 0.00442 -0.1147 0.8706 0.0117
-6.500 -0.2430 0.00949 0.00410 -0.1147 0.8645 0.0130
-6.250 -0.2152 0.00927 0.00384 -0.1147 0.8588 0.0141
-6.000 -0.1875 0.00908 0.00359 -0.1147 0.8528 0.0151
-5.750 -0.1597 0.00888 0.00333 -0.1147 0.8471 0.0159
-5.500 -0.1319 0.00864 0.00306 -0.1147 0.8410 0.0174
-5.250 -0.1042 0.00847 0.00284 -0.1147 0.8348 0.0188
-5.000 -0.0762 0.00831 0.00264 -0.1147 0.8277 0.0200
-4.750 -0.0484 0.00815 0.00243 -0.1146 0.8209 0.0218
-4.500 -0.0204 0.00797 0.00224 -0.1147 0.8146 0.0245
-4.250 0.0076 0.00783 0.00207 -0.1146 0.8080 0.0266
-4.000 0.0356 0.00767 0.00190 -0.1146 0.8017 0.0315
-3.750 0.0637 0.00755 0.00175 -0.1146 0.7944 0.0361
-3.500 0.0916 0.00741 0.00161 -0.1146 0.7867 0.0432
-3.250 0.1194 0.00729 0.00148 -0.1145 0.7773 0.0527
-3.000 0.1474 0.00715 0.00136 -0.1145 0.7684 0.0673
-2.750 0.1752 0.00704 0.00125 -0.1145 0.7599 0.0835
-2.500 0.2031 0.00688 0.00115 -0.1145 0.7509 0.1079
-2.250 0.2308 0.00673 0.00106 -0.1145 0.7419 0.1416
-2.000 0.2582 0.00656 0.00098 -0.1144 0.7306 0.1848
-1.750 0.2855 0.00636 0.00091 -0.1143 0.7172 0.2432
-1.500 0.3129 0.00627 0.00087 -0.1143 0.7038 0.2791
-1.250 0.3405 0.00620 0.00084 -0.1142 0.6914 0.3110
-1.000 0.3681 0.00614 0.00084 -0.1141 0.6802 0.3489
-0.750 0.3956 0.00613 0.00084 -0.1139 0.6669 0.3734
-0.500 0.4228 0.00616 0.00085 -0.1138 0.6502 0.3945
-0.250 0.4499 0.00619 0.00088 -0.1135 0.6321 0.4187
0.000 0.4771 0.00627 0.00090 -0.1133 0.6150 0.4300
0.250 0.5045 0.00633 0.00093 -0.1132 0.6004 0.4426
0.750 0.5589 0.00648 0.00103 -0.1128 0.5697 0.4678
1.250 0.6129 0.00667 0.00115 -0.1123 0.5372 0.4921
1.500 0.6402 0.00676 0.00122 -0.1121 0.5241 0.5037
1.750 0.6673 0.00685 0.00129 -0.1120 0.5103 0.5152
2.000 0.6940 0.00698 0.00138 -0.1117 0.4912 0.5251
2.250 0.7205 0.00712 0.00148 -0.1114 0.4689 0.5377
2.500 0.7468 0.00729 0.00159 -0.1111 0.4473 0.5517
2.750 0.7734 0.00742 0.00170 -0.1108 0.4303 0.5655
3.000 0.7999 0.00757 0.00182 -0.1105 0.4122 0.5782
3.250 0.8260 0.00774 0.00196 -0.1102 0.3919 0.5911
3.500 0.8520 0.00793 0.00211 -0.1098 0.3717 0.6038
3.750 0.8775 0.00817 0.00228 -0.1094 0.3460 0.6178
4.000 0.9026 0.00843 0.00247 -0.1090 0.3186 0.6336
4.250 0.9270 0.00876 0.00270 -0.1084 0.2854 0.6518
4.500 0.9513 0.00906 0.00294 -0.1078 0.2560 0.6765
4.750 0.9760 0.00928 0.00317 -0.1072 0.2336 0.7092
5.000 0.9992 0.00958 0.00346 -0.1065 0.2040 0.7551
5.250 1.0164 0.00979 0.00381 -0.1044 0.1606 0.8977
5.500 1.0458 0.01029 0.00418 -0.1051 0.1229 1.0000
5.750 1.0693 0.01076 0.00451 -0.1045 0.0989 1.0000
6.000 1.0925 0.01123 0.00486 -0.1037 0.0765 1.0000
6.250 1.1162 0.01165 0.00520 -0.1031 0.0607 1.0000
6.500 1.1398 0.01207 0.00555 -0.1024 0.0477 1.0000
6.750 1.1633 0.01248 0.00591 -0.1017 0.0376 1.0000
7.000 1.1864 0.01292 0.00630 -0.1010 0.0284 1.0000
7.250 1.2088 0.01342 0.00673 -0.1001 0.0195 1.0000
7.500 1.2314 0.01388 0.00717 -0.0993 0.0144 1.0000
7.750 1.2543 0.01429 0.00758 -0.0985 0.0121 1.0000
8.000 1.2765 0.01475 0.00805 -0.0976 0.0103 1.0000
8.250 1.2992 0.01514 0.00847 -0.0969 0.0095 1.0000
8.500 1.3212 0.01558 0.00893 -0.0959 0.0088 1.0000
8.750 1.3425 0.01606 0.00943 -0.0949 0.0081 1.0000
9.000 1.3628 0.01662 0.01002 -0.0938 0.0075 1.0000
9.250 1.3834 0.01710 0.01056 -0.0927 0.0073 1.0000
9.500 1.4035 0.01760 0.01110 -0.0915 0.0070 1.0000
9.750 1.4227 0.01814 0.01168 -0.0902 0.0068 1.0000
10.000 1.4413 0.01869 0.01228 -0.0888 0.0066 1.0000
10.250 1.4584 0.01926 0.01290 -0.0872 0.0063 1.0000
10.500 1.4733 0.01986 0.01355 -0.0852 0.0061 1.0000
10.750 1.4871 0.02049 0.01424 -0.0830 0.0059 1.0000
11.000 1.5000 0.02118 0.01498 -0.0808 0.0058 1.0000
11.250 1.5116 0.02196 0.01582 -0.0785 0.0055 1.0000
11.500 1.5206 0.02294 0.01687 -0.0760 0.0053 1.0000
11.750 1.5284 0.02403 0.01804 -0.0735 0.0051 1.0000
12.000 1.5397 0.02490 0.01898 -0.0715 0.0051 1.0000
12.250 1.5493 0.02592 0.02008 -0.0695 0.0050 1.0000
12.500 1.5584 0.02701 0.02125 -0.0676 0.0049 1.0000
12.750 1.5669 0.02820 0.02252 -0.0657 0.0048 1.0000
13.000 1.5744 0.02951 0.02393 -0.0638 0.0047 1.0000
13.250 1.5812 0.03093 0.02544 -0.0621 0.0046 1.0000
13.500 1.5870 0.03248 0.02708 -0.0605 0.0046 1.0000
13.750 1.5915 0.03423 0.02892 -0.0589 0.0045 1.0000
14.000 1.5948 0.03616 0.03095 -0.0575 0.0044 1.0000
14.250 1.5986 0.03811 0.03299 -0.0563 0.0043 1.0000
14.500 1.6003 0.04037 0.03536 -0.0553 0.0043 1.0000
14.750 1.6009 0.04284 0.03793 -0.0544 0.0042 1.0000
15.000 1.6005 0.04553 0.04072 -0.0537 0.0042 1.0000
15.250 1.6010 0.04824 0.04353 -0.0533 0.0041 1.0000
15.500 1.5996 0.05129 0.04669 -0.0532 0.0040 1.0000
15.750 1.5960 0.05478 0.05031 -0.0533 0.0040 1.0000
16.000 1.5927 0.05841 0.05405 -0.0537 0.0039 1.0000
16.250 1.5896 0.06217 0.05791 -0.0544 0.0038 1.0000
16.500 1.5817 0.06680 0.06266 -0.0555 0.0038 1.0000
16.750 1.5743 0.07156 0.06754 -0.0569 0.0038 1.0000
17.000 1.5654 0.07674 0.07285 -0.0587 0.0037 1.0000
17.250 1.5561 0.08217 0.07840 -0.0608 0.0037 1.0000
17.500 1.5425 0.08853 0.08490 -0.0634 0.0037 1.0000
17.750 1.5300 0.09492 0.09141 -0.0662 0.0036 1.0000
18.000 1.5141 0.10216 0.09879 -0.0697 0.0036 1.0000
18.250 1.4973 0.10977 0.10654 -0.0734 0.0036 1.0000
18.500 1.4803 0.11763 0.11454 -0.0775 0.0036 1.0000
18.750 1.4626 0.12584 0.12289 -0.0820 0.0036 1.0000
19.000 1.4455 0.13408 0.13126 -0.0866 0.0036 1.0000
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