AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 C AIRFOIL (ah79100c-il) Reynolds number: 1,000,000 Max Cl/Cd: 161.43 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100c-il-1000000-n5.txt Download as CSV file: xf-ah79100c-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0291 0.09753 0.09557 -0.1202 0.9668 0.0051
-10.250 -0.0193 0.09327 0.09131 -0.1235 0.9660 0.0051
-9.750 -0.2309 0.02135 0.01848 -0.1896 0.9189 0.0054
-9.500 -0.1957 0.01810 0.01486 -0.1953 0.9163 0.0054
-9.250 -0.1609 0.01628 0.01278 -0.1989 0.9131 0.0054
-9.000 -0.1281 0.01508 0.01139 -0.2012 0.9084 0.0055
-8.750 -0.0904 0.01388 0.00997 -0.2046 0.9047 0.0056
-8.250 -0.0228 0.01208 0.00782 -0.2088 0.8948 0.0059
-8.000 0.0099 0.01143 0.00701 -0.2105 0.8891 0.0062
-7.750 0.0404 0.01088 0.00633 -0.2115 0.8829 0.0065
-7.500 0.0701 0.01041 0.00573 -0.2123 0.8755 0.0069
-7.250 0.0995 0.01002 0.00523 -0.2129 0.8687 0.0072
-7.000 0.1278 0.00968 0.00478 -0.2132 0.8614 0.0076
-6.750 0.1562 0.00936 0.00441 -0.2136 0.8548 0.0092
-6.500 0.1836 0.00918 0.00419 -0.2137 0.8473 0.0111
-6.250 0.2114 0.00904 0.00397 -0.2138 0.8404 0.0130
-6.000 0.2385 0.00894 0.00384 -0.2137 0.8330 0.0143
-5.750 0.2658 0.00882 0.00364 -0.2137 0.8265 0.0153
-5.500 0.2929 0.00872 0.00348 -0.2136 0.8199 0.0161
-5.000 0.3471 0.00840 0.00303 -0.2135 0.8070 0.0174
-4.750 0.3740 0.00829 0.00286 -0.2134 0.8006 0.0183
-4.500 0.4011 0.00818 0.00271 -0.2133 0.7950 0.0191
-4.250 0.4281 0.00808 0.00255 -0.2132 0.7888 0.0198
-3.750 0.4822 0.00785 0.00223 -0.2131 0.7774 0.0219
-3.500 0.5091 0.00776 0.00210 -0.2129 0.7715 0.0230
-3.250 0.5360 0.00768 0.00198 -0.2128 0.7661 0.0238
-3.000 0.5632 0.00760 0.00186 -0.2127 0.7605 0.0246
-2.750 0.5898 0.00755 0.00176 -0.2125 0.7546 0.0257
-2.500 0.6167 0.00748 0.00168 -0.2123 0.7490 0.0284
-2.250 0.6434 0.00743 0.00162 -0.2121 0.7427 0.0329
-2.000 0.6695 0.00741 0.00157 -0.2118 0.7366 0.0383
-1.750 0.6965 0.00736 0.00153 -0.2117 0.7308 0.0451
-1.500 0.7225 0.00735 0.00150 -0.2114 0.7241 0.0519
-1.250 0.7488 0.00733 0.00148 -0.2111 0.7177 0.0596
-0.750 0.8012 0.00729 0.00148 -0.2105 0.7058 0.0910
-0.500 0.8280 0.00724 0.00149 -0.2104 0.6997 0.1179
-0.250 0.8535 0.00721 0.00152 -0.2100 0.6924 0.1588
0.000 0.8799 0.00719 0.00155 -0.2098 0.6861 0.1890
0.250 0.9056 0.00718 0.00160 -0.2095 0.6794 0.2195
0.500 0.9312 0.00719 0.00165 -0.2091 0.6729 0.2498
1.000 0.9816 0.00715 0.00180 -0.2082 0.6581 0.3617
1.250 1.0068 0.00708 0.00191 -0.2078 0.6496 0.4509
1.500 1.0313 0.00705 0.00201 -0.2073 0.6419 0.5263
1.750 1.0558 0.00703 0.00213 -0.2067 0.6333 0.6038
2.000 1.0793 0.00702 0.00226 -0.2059 0.6230 0.6824
2.250 1.1007 0.00702 0.00243 -0.2046 0.6101 0.7813
2.500 1.1140 0.00692 0.00258 -0.2013 0.5953 0.9324
2.750 1.1381 0.00705 0.00267 -0.2006 0.5820 1.0000
3.000 1.1603 0.00724 0.00279 -0.1995 0.5676 1.0000
3.250 1.1818 0.00746 0.00295 -0.1983 0.5501 1.0000
3.500 1.2032 0.00770 0.00311 -0.1970 0.5333 1.0000
3.750 1.2245 0.00794 0.00328 -0.1958 0.5170 1.0000
4.000 1.2447 0.00824 0.00348 -0.1943 0.4975 1.0000
4.250 1.2640 0.00858 0.00372 -0.1927 0.4761 1.0000
4.500 1.2823 0.00897 0.00399 -0.1909 0.4498 1.0000
4.750 1.2972 0.00954 0.00436 -0.1885 0.4115 1.0000
5.000 1.3126 0.01008 0.00472 -0.1863 0.3775 1.0000
5.250 1.3265 0.01070 0.00515 -0.1837 0.3400 1.0000
5.500 1.3409 0.01132 0.00558 -0.1814 0.3044 1.0000
5.750 1.3558 0.01193 0.00602 -0.1791 0.2723 1.0000
6.000 1.3690 0.01260 0.00651 -0.1766 0.2396 1.0000
6.250 1.3840 0.01319 0.00698 -0.1744 0.2145 1.0000
6.500 1.3965 0.01394 0.00755 -0.1718 0.1821 1.0000
6.750 1.4100 0.01463 0.00811 -0.1694 0.1576 1.0000
7.000 1.4233 0.01534 0.00870 -0.1671 0.1349 1.0000
7.250 1.4336 0.01625 0.00943 -0.1643 0.1037 1.0000
7.500 1.4418 0.01729 0.01031 -0.1612 0.0727 1.0000
7.750 1.4489 0.01845 0.01128 -0.1580 0.0424 1.0000
8.000 1.4569 0.01957 0.01228 -0.1550 0.0192 1.0000
8.250 1.4699 0.02041 0.01309 -0.1528 0.0108 1.0000
8.500 1.4846 0.02111 0.01380 -0.1510 0.0086 1.0000
8.750 1.4999 0.02181 0.01453 -0.1493 0.0077 1.0000
9.000 1.5144 0.02256 0.01531 -0.1475 0.0071 1.0000
9.250 1.5293 0.02330 0.01608 -0.1458 0.0068 1.0000
9.500 1.5436 0.02409 0.01691 -0.1441 0.0066 1.0000
9.750 1.5576 0.02491 0.01778 -0.1424 0.0064 1.0000
10.000 1.5709 0.02580 0.01872 -0.1406 0.0062 1.0000
10.250 1.5839 0.02673 0.01969 -0.1389 0.0061 1.0000
10.500 1.5961 0.02774 0.02076 -0.1371 0.0059 1.0000
10.750 1.6079 0.02879 0.02186 -0.1353 0.0058 1.0000
11.000 1.6189 0.02994 0.02306 -0.1335 0.0056 1.0000
11.250 1.6291 0.03118 0.02437 -0.1317 0.0054 1.0000
11.500 1.6388 0.03249 0.02574 -0.1299 0.0054 1.0000
11.750 1.6471 0.03396 0.02728 -0.1280 0.0052 1.0000
12.000 1.6543 0.03557 0.02896 -0.1262 0.0051 1.0000
12.250 1.6600 0.03737 0.03084 -0.1242 0.0050 1.0000
12.500 1.6672 0.03906 0.03261 -0.1226 0.0049 1.0000
12.750 1.6757 0.04067 0.03428 -0.1211 0.0049 1.0000
13.000 1.6836 0.04235 0.03604 -0.1197 0.0048 1.0000
13.250 1.6898 0.04425 0.03802 -0.1183 0.0047 1.0000
13.500 1.6953 0.04628 0.04013 -0.1169 0.0046 1.0000
13.750 1.7000 0.04845 0.04239 -0.1155 0.0046 1.0000
14.000 1.7042 0.05073 0.04475 -0.1143 0.0045 1.0000
14.250 1.7074 0.05318 0.04730 -0.1131 0.0045 1.0000
14.500 1.7097 0.05578 0.05000 -0.1121 0.0044 1.0000
14.750 1.7116 0.05852 0.05283 -0.1111 0.0043 1.0000
15.000 1.7127 0.06142 0.05583 -0.1103 0.0043 1.0000
15.250 1.7134 0.06446 0.05897 -0.1095 0.0042 1.0000
15.500 1.7133 0.06767 0.06228 -0.1090 0.0042 1.0000
15.750 1.7121 0.07110 0.06581 -0.1086 0.0041 1.0000
16.000 1.7104 0.07470 0.06952 -0.1083 0.0041 1.0000
16.250 1.7082 0.07846 0.07339 -0.1082 0.0041 1.0000
16.500 1.7053 0.08242 0.07746 -0.1083 0.0040 1.0000
16.750 1.7019 0.08654 0.08169 -0.1086 0.0040 1.0000
17.000 1.6979 0.09081 0.08607 -0.1091 0.0039 1.0000
17.250 1.6935 0.09526 0.09063 -0.1098 0.0039 1.0000
17.500 1.6884 0.09990 0.09539 -0.1107 0.0039 1.0000
17.750 1.6831 0.10465 0.10025 -0.1118 0.0038 1.0000
18.000 1.6772 0.10958 0.10529 -0.1132 0.0038 1.0000
18.250 1.6708 0.11464 0.11047 -0.1147 0.0038 1.0000
18.500 1.6655 0.11955 0.11549 -0.1164 0.0038 1.0000
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