AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 C AIRFOIL (ah79100c-il) Reynolds number: 500,000 Max Cl/Cd: 137.65 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100c-il-500000-n5.txt Download as CSV file: xf-ah79100c-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0515 0.09668 0.09407 -0.1087 0.9557 0.0080
-9.500 -0.0418 0.09218 0.08957 -0.1121 0.9541 0.0078
-8.000 -0.0779 0.01949 0.01561 -0.1868 0.9012 0.0087
-7.750 -0.0511 0.01749 0.01327 -0.1886 0.8954 0.0090
-7.500 -0.0163 0.01585 0.01130 -0.1915 0.8921 0.0096
-7.250 0.0213 0.01456 0.00974 -0.1946 0.8895 0.0101
-7.000 0.0603 0.01397 0.00905 -0.1974 0.8873 0.0109
-6.750 0.0905 0.01339 0.00831 -0.1984 0.8822 0.0123
-6.500 0.1250 0.01288 0.00767 -0.2002 0.8776 0.0136
-6.250 0.1626 0.01253 0.00718 -0.2025 0.8739 0.0153
-6.000 0.1947 0.01211 0.00660 -0.2037 0.8689 0.0167
-5.750 0.2256 0.01182 0.00624 -0.2046 0.8633 0.0178
-5.500 0.2599 0.01153 0.00584 -0.2062 0.8586 0.0191
-5.250 0.2889 0.01126 0.00544 -0.2067 0.8524 0.0202
-5.000 0.3195 0.01094 0.00504 -0.2075 0.8465 0.0216
-4.750 0.3506 0.01087 0.00493 -0.2083 0.8414 0.0236
-4.500 0.3782 0.01068 0.00465 -0.2084 0.8350 0.0249
-4.250 0.4088 0.01033 0.00419 -0.2092 0.8293 0.0258
-4.000 0.4372 0.01002 0.00382 -0.2095 0.8234 0.0266
-3.750 0.4657 0.00981 0.00355 -0.2097 0.8175 0.0275
-3.500 0.4956 0.00963 0.00328 -0.2103 0.8122 0.0285
-3.250 0.5226 0.00946 0.00307 -0.2102 0.8061 0.0297
-3.000 0.5511 0.00933 0.00287 -0.2104 0.8004 0.0311
-2.750 0.5795 0.00918 0.00268 -0.2106 0.7952 0.0339
-2.500 0.6066 0.00909 0.00256 -0.2105 0.7892 0.0379
-2.250 0.6351 0.00899 0.00244 -0.2107 0.7838 0.0444
-2.000 0.6622 0.00892 0.00235 -0.2106 0.7782 0.0511
-1.750 0.6893 0.00887 0.00228 -0.2105 0.7722 0.0588
-1.500 0.7173 0.00883 0.00222 -0.2107 0.7666 0.0703
-1.250 0.7436 0.00876 0.00219 -0.2104 0.7603 0.0876
-1.000 0.7709 0.00868 0.00217 -0.2104 0.7544 0.1190
-0.750 0.7979 0.00859 0.00219 -0.2104 0.7485 0.1690
-0.500 0.8242 0.00856 0.00221 -0.2102 0.7418 0.2028
-0.250 0.8512 0.00854 0.00223 -0.2101 0.7357 0.2358
0.000 0.8772 0.00851 0.00227 -0.2098 0.7294 0.2730
0.250 0.9040 0.00848 0.00233 -0.2098 0.7236 0.3256
0.500 0.9304 0.00838 0.00243 -0.2097 0.7172 0.4148
0.750 0.9564 0.00823 0.00256 -0.2095 0.7100 0.5363
1.000 0.9819 0.00810 0.00270 -0.2091 0.7037 0.6624
1.250 1.0055 0.00800 0.00283 -0.2082 0.6971 0.7629
1.500 1.0223 0.00785 0.00291 -0.2056 0.6905 0.8902
1.750 1.0472 0.00783 0.00292 -0.2049 0.6826 1.0000
2.000 1.0720 0.00796 0.00299 -0.2043 0.6749 1.0000
2.250 1.0966 0.00807 0.00308 -0.2037 0.6666 1.0000
2.500 1.1212 0.00821 0.00317 -0.2031 0.6594 1.0000
2.750 1.1449 0.00833 0.00327 -0.2023 0.6500 1.0000
3.000 1.1673 0.00848 0.00337 -0.2012 0.6395 1.0000
3.250 1.1884 0.00865 0.00350 -0.1998 0.6277 1.0000
3.500 1.2088 0.00884 0.00363 -0.1983 0.6148 1.0000
3.750 1.2294 0.00903 0.00378 -0.1968 0.6011 1.0000
4.000 1.2494 0.00925 0.00395 -0.1952 0.5866 1.0000
4.250 1.2699 0.00947 0.00415 -0.1938 0.5727 1.0000
4.500 1.2898 0.00971 0.00435 -0.1923 0.5583 1.0000
4.750 1.3082 0.01001 0.00459 -0.1904 0.5415 1.0000
5.000 1.3250 0.01036 0.00486 -0.1883 0.5213 1.0000
5.250 1.3397 0.01081 0.00520 -0.1858 0.4952 1.0000
5.500 1.3523 0.01136 0.00561 -0.1829 0.4655 1.0000
5.750 1.3660 0.01191 0.00603 -0.1803 0.4380 1.0000
6.000 1.3764 0.01263 0.00656 -0.1772 0.4026 1.0000
6.250 1.3885 0.01330 0.00710 -0.1744 0.3724 1.0000
6.500 1.3989 0.01410 0.00771 -0.1714 0.3364 1.0000
6.750 1.4081 0.01499 0.00839 -0.1683 0.2985 1.0000
7.000 1.4167 0.01595 0.00913 -0.1652 0.2604 1.0000
7.250 1.4271 0.01685 0.00987 -0.1624 0.2284 1.0000
7.500 1.4394 0.01765 0.01058 -0.1600 0.2059 1.0000
7.750 1.4493 0.01863 0.01140 -0.1573 0.1767 1.0000
8.000 1.4567 0.01978 0.01238 -0.1543 0.1437 1.0000
8.250 1.4627 0.02107 0.01347 -0.1513 0.1097 1.0000
8.500 1.4702 0.02230 0.01456 -0.1485 0.0829 1.0000
8.750 1.4752 0.02375 0.01586 -0.1454 0.0545 1.0000
9.000 1.4782 0.02540 0.01735 -0.1422 0.0265 1.0000
9.250 1.4855 0.02679 0.01869 -0.1397 0.0162 1.0000
9.500 1.4965 0.02791 0.01984 -0.1377 0.0124 1.0000
9.750 1.5084 0.02898 0.02096 -0.1359 0.0109 1.0000
10.000 1.5199 0.03011 0.02213 -0.1341 0.0099 1.0000
10.250 1.5305 0.03133 0.02342 -0.1322 0.0093 1.0000
10.500 1.5418 0.03253 0.02469 -0.1305 0.0089 1.0000
10.750 1.5524 0.03380 0.02605 -0.1288 0.0086 1.0000
11.000 1.5624 0.03515 0.02748 -0.1272 0.0084 1.0000
11.250 1.5716 0.03661 0.02902 -0.1255 0.0081 1.0000
11.500 1.5802 0.03817 0.03067 -0.1238 0.0079 1.0000
11.750 1.5879 0.03983 0.03242 -0.1222 0.0077 1.0000
12.000 1.5947 0.04164 0.03431 -0.1206 0.0075 1.0000
12.250 1.6005 0.04358 0.03634 -0.1190 0.0074 1.0000
12.500 1.6043 0.04578 0.03863 -0.1174 0.0072 1.0000
12.750 1.6067 0.04820 0.04115 -0.1158 0.0071 1.0000
13.000 1.6074 0.05089 0.04395 -0.1143 0.0069 1.0000
13.250 1.6108 0.05332 0.04649 -0.1131 0.0069 1.0000
13.500 1.6133 0.05592 0.04919 -0.1119 0.0068 1.0000
13.750 1.6154 0.05865 0.05204 -0.1109 0.0067 1.0000
14.000 1.6171 0.06148 0.05498 -0.1100 0.0066 1.0000
14.250 1.6181 0.06449 0.05811 -0.1093 0.0065 1.0000
14.500 1.6184 0.06765 0.06138 -0.1086 0.0064 1.0000
14.750 1.6180 0.07098 0.06483 -0.1081 0.0063 1.0000
15.000 1.6170 0.07448 0.06845 -0.1078 0.0062 1.0000
15.250 1.6155 0.07814 0.07224 -0.1076 0.0061 1.0000
15.500 1.6133 0.08198 0.07619 -0.1076 0.0060 1.0000
15.750 1.6107 0.08595 0.08029 -0.1078 0.0059 1.0000
16.000 1.6078 0.09004 0.08449 -0.1081 0.0059 1.0000
16.250 1.6047 0.09424 0.08881 -0.1086 0.0058 1.0000
16.500 1.6016 0.09850 0.09320 -0.1093 0.0058 1.0000
16.750 1.5983 0.10285 0.09767 -0.1101 0.0057 1.0000
17.000 1.5950 0.10726 0.10220 -0.1111 0.0056 1.0000
17.250 1.5917 0.11171 0.10676 -0.1122 0.0056 1.0000
17.500 1.5883 0.11620 0.11137 -0.1136 0.0055 1.0000
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