AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 100,000 Max Cl/Cd: 65.85 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100b-il-100000.txt Download as CSV file: xf-ah79100b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 B 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2506 0.10586 0.10166 -0.0462 0.9680 0.0690
-6.500 -0.2547 0.10470 0.10053 -0.0477 0.9596 0.0708
-6.250 -0.2532 0.10403 0.09991 -0.0587 0.9489 0.0724
-6.000 -0.2408 0.09877 0.09468 -0.0599 0.9442 0.0736
-5.750 -0.2206 0.09465 0.09053 -0.0565 0.9421 0.0768
-5.500 -0.2166 0.09237 0.08827 -0.0566 0.9345 0.0796
-5.250 -0.1947 0.08879 0.08466 -0.0643 0.9285 0.0847
-5.000 -0.1676 0.08410 0.07991 -0.0837 0.9182 0.0881
-4.750 -0.1632 0.08124 0.07711 -0.0753 0.9152 0.0903
-4.500 -0.1506 0.07879 0.07464 -0.0751 0.9100 0.0942
-4.250 -0.1046 0.07251 0.06822 -0.0946 0.9028 0.1041
-4.000 -0.0893 0.07028 0.06602 -0.0910 0.8995 0.1083
-3.750 -0.0582 0.06596 0.06158 -0.1011 0.8926 0.1208
-3.500 -0.0215 0.06218 0.05771 -0.1080 0.8880 0.1364
-3.250 0.0370 0.05802 0.05332 -0.1197 0.8851 0.1632
-3.000 0.0631 0.05507 0.05029 -0.1232 0.8786 0.1816
-2.500 0.2586 0.03967 0.03287 -0.1599 0.8763 0.1169
-2.250 0.3231 0.03576 0.02817 -0.1673 0.8741 0.0995
-2.000 0.3773 0.03357 0.02547 -0.1723 0.8716 0.0974
-1.750 0.4299 0.03217 0.02361 -0.1766 0.8695 0.1014
-1.500 0.4481 0.03208 0.02333 -0.1754 0.8607 0.1026
-1.250 0.4920 0.03075 0.02201 -0.1783 0.8575 0.1084
-1.000 0.5387 0.02976 0.02105 -0.1815 0.8551 0.1240
-0.750 0.5556 0.03000 0.02136 -0.1802 0.8462 0.1371
-0.500 0.6125 0.02798 0.02099 -0.1858 0.8438 0.5959
-0.250 0.6458 0.02745 0.02069 -0.1849 0.8406 0.7395
0.000 0.6513 0.02792 0.02128 -0.1806 0.8302 0.8074
0.250 0.6748 0.02699 0.02045 -0.1781 0.8260 1.0000
0.500 0.6981 0.02783 0.02109 -0.1786 0.8161 1.0000
0.750 0.7451 0.02760 0.02063 -0.1820 0.8127 1.0000
1.000 0.7957 0.02715 0.01998 -0.1857 0.8107 1.0000
1.250 0.8076 0.02829 0.02102 -0.1839 0.7993 1.0000
1.500 0.8561 0.02778 0.02038 -0.1871 0.7967 1.0000
1.750 0.8713 0.02873 0.02128 -0.1855 0.7862 1.0000
2.000 0.9181 0.02820 0.02066 -0.1883 0.7828 1.0000
2.250 0.9691 0.02741 0.01980 -0.1915 0.7807 1.0000
2.500 0.9827 0.02832 0.02070 -0.1895 0.7690 1.0000
2.750 1.0313 0.02755 0.01989 -0.1923 0.7664 1.0000
3.000 1.0441 0.02855 0.02090 -0.1902 0.7549 1.0000
3.250 1.0902 0.02787 0.02023 -0.1926 0.7519 1.0000
3.500 1.1042 0.02881 0.02121 -0.1907 0.7407 1.0000
3.750 1.1498 0.02806 0.02047 -0.1929 0.7372 1.0000
4.000 1.1661 0.02886 0.02132 -0.1912 0.7263 1.0000
4.250 1.2118 0.02800 0.02051 -0.1933 0.7222 1.0000
4.500 1.2315 0.02847 0.02106 -0.1919 0.7113 1.0000
4.750 1.2779 0.02751 0.02014 -0.1941 0.7068 1.0000
5.250 1.3427 0.02715 0.01995 -0.1946 0.6909 1.0000
5.500 1.3612 0.02755 0.02046 -0.1929 0.6787 1.0000
5.750 1.3859 0.02763 0.02065 -0.1920 0.6678 1.0000
6.000 1.4308 0.02668 0.01979 -0.1938 0.6613 1.0000
6.250 1.4503 0.02705 0.02030 -0.1922 0.6491 1.0000
6.500 1.4750 0.02708 0.02045 -0.1912 0.6372 1.0000
6.750 1.5049 0.02657 0.02007 -0.1907 0.6240 1.0000
7.000 1.5341 0.02593 0.01950 -0.1898 0.6085 1.0000
7.250 1.5626 0.02520 0.01882 -0.1888 0.5907 1.0000
7.500 1.5913 0.02462 0.01826 -0.1879 0.5724 1.0000
7.750 1.6080 0.02481 0.01860 -0.1854 0.5537 1.0000
8.000 1.6255 0.02501 0.01893 -0.1832 0.5346 1.0000
8.250 1.6457 0.02499 0.01891 -0.1811 0.5126 1.0000
8.500 1.6534 0.02541 0.01942 -0.1772 0.4864 1.0000
8.750 1.6594 0.02593 0.01996 -0.1731 0.4578 1.0000
9.000 1.6604 0.02665 0.02068 -0.1682 0.4280 1.0000
9.250 1.6555 0.02769 0.02164 -0.1626 0.3946 1.0000
9.500 1.6456 0.02919 0.02304 -0.1568 0.3551 1.0000
9.750 1.6311 0.03129 0.02490 -0.1510 0.3070 1.0000
10.000 1.6116 0.03420 0.02746 -0.1454 0.2494 1.0000
10.250 1.5888 0.03798 0.03077 -0.1405 0.1923 1.0000
10.500 1.5671 0.04223 0.03460 -0.1364 0.1479 1.0000
10.750 1.5501 0.04644 0.03855 -0.1331 0.1181 1.0000
11.000 1.5364 0.05057 0.04254 -0.1304 0.0995 1.0000
11.250 1.5255 0.05460 0.04651 -0.1281 0.0861 1.0000
11.500 1.5170 0.05854 0.05042 -0.1259 0.0756 1.0000
11.750 1.5129 0.06217 0.05400 -0.1239 0.0676 1.0000
12.000 1.5156 0.06518 0.05693 -0.1221 0.0603 1.0000
12.250 1.5273 0.06754 0.05938 -0.1203 0.0539 1.0000
12.500 1.5692 0.06875 0.06035 -0.1187 0.0474 1.0000
12.750 1.5885 0.07112 0.06306 -0.1173 0.0453 1.0000
13.000 1.6046 0.07387 0.06609 -0.1161 0.0430 1.0000
13.250 1.6138 0.07682 0.06925 -0.1151 0.0407 1.0000
13.500 1.6281 0.08009 0.07266 -0.1143 0.0389 1.0000
13.750 1.6451 0.08457 0.07740 -0.1136 0.0380 1.0000
14.000 1.6460 0.08949 0.08269 -0.1126 0.0378 1.0000
14.250 1.6388 0.09461 0.08816 -0.1117 0.0377 1.0000
14.500 1.6265 0.09921 0.09310 -0.1110 0.0379 1.0000
14.750 1.6111 0.10424 0.09846 -0.1108 0.0380 1.0000
15.000 1.5932 0.10929 0.10385 -0.1112 0.0383 1.0000
15.250 1.5724 0.11501 0.10992 -0.1123 0.0387 1.0000
15.500 1.5483 0.12167 0.11693 -0.1145 0.0392 1.0000
15.750 1.5162 0.12983 0.12546 -0.1185 0.0397 1.0000
16.000 1.4813 0.13961 0.13558 -0.1244 0.0406 1.0000
16.250 1.4490 0.15037 0.14663 -0.1316 0.0415 1.0000
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Polar data table (+)
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