AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 C AIRFOIL (ah79100c-il) Reynolds number: 1,000,000 Max Cl/Cd: 183.02 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100c-il-1000000.txt Download as CSV file: xf-ah79100c-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0536 0.08863 0.08686 -0.1182 0.9662 0.0122
-10.250 0.0614 0.08403 0.08226 -0.1214 0.9658 0.0128
-9.000 -0.1612 0.02102 0.01832 -0.1896 0.9340 0.0083
-8.750 -0.1291 0.01817 0.01514 -0.1938 0.9320 0.0085
-8.500 -0.0950 0.01595 0.01260 -0.1974 0.9306 0.0087
-8.250 -0.0592 0.01444 0.01085 -0.2004 0.9294 0.0089
-8.000 -0.0213 0.01335 0.00956 -0.2035 0.9285 0.0091
-7.750 -0.0022 0.01255 0.00861 -0.2021 0.9211 0.0093
-7.500 0.0337 0.01170 0.00758 -0.2044 0.9186 0.0097
-7.250 0.0732 0.01100 0.00673 -0.2074 0.9168 0.0101
-7.000 0.1132 0.01038 0.00603 -0.2105 0.9149 0.0110
-6.750 0.1386 0.01014 0.00574 -0.2101 0.9079 0.0120
-6.500 0.1750 0.00971 0.00522 -0.2122 0.9041 0.0136
-6.250 0.2105 0.00976 0.00525 -0.2138 0.8998 0.0160
-6.000 0.2387 0.00959 0.00505 -0.2140 0.8928 0.0181
-5.750 0.2728 0.00954 0.00492 -0.2155 0.8877 0.0196
-5.500 0.3004 0.00955 0.00488 -0.2154 0.8805 0.0204
-5.250 0.3311 0.00897 0.00418 -0.2164 0.8741 0.0219
-5.000 0.3590 0.00883 0.00401 -0.2165 0.8670 0.0230
-4.750 0.3879 0.00867 0.00378 -0.2169 0.8602 0.0239
-4.500 0.4158 0.00849 0.00352 -0.2170 0.8535 0.0247
-4.250 0.4436 0.00839 0.00335 -0.2170 0.8463 0.0253
-4.000 0.4717 0.00801 0.00291 -0.2173 0.8399 0.0271
-3.750 0.4987 0.00794 0.00281 -0.2172 0.8329 0.0286
-3.500 0.5269 0.00782 0.00261 -0.2173 0.8267 0.0298
-3.250 0.5536 0.00766 0.00242 -0.2171 0.8200 0.0306
-3.000 0.5816 0.00754 0.00220 -0.2172 0.8138 0.0315
-2.750 0.6086 0.00734 0.00198 -0.2171 0.8075 0.0341
-2.500 0.6357 0.00727 0.00187 -0.2170 0.8009 0.0372
-2.250 0.6630 0.00716 0.00175 -0.2169 0.7948 0.0457
-2.000 0.6897 0.00708 0.00167 -0.2167 0.7883 0.0561
-1.750 0.7171 0.00705 0.00161 -0.2167 0.7822 0.0675
-1.500 0.7433 0.00697 0.00158 -0.2164 0.7758 0.0849
-1.250 0.7701 0.00690 0.00155 -0.2162 0.7694 0.1153
-1.000 0.7969 0.00682 0.00156 -0.2162 0.7637 0.1603
-0.500 0.8505 0.00674 0.00161 -0.2159 0.7518 0.2418
-0.250 0.8767 0.00664 0.00165 -0.2157 0.7457 0.2978
0.000 0.9031 0.00659 0.00170 -0.2156 0.7396 0.3590
0.250 0.9297 0.00654 0.00177 -0.2154 0.7341 0.4234
0.500 0.9560 0.00644 0.00184 -0.2153 0.7279 0.5085
0.750 0.9820 0.00627 0.00199 -0.2151 0.7218 0.6671
1.000 1.0036 0.00599 0.00215 -0.2137 0.7159 0.8522
1.250 1.0244 0.00586 0.00216 -0.2120 0.7094 1.0000
1.500 1.0504 0.00595 0.00221 -0.2117 0.7035 1.0000
1.750 1.0760 0.00603 0.00226 -0.2112 0.6970 1.0000
2.000 1.1008 0.00615 0.00232 -0.2106 0.6897 1.0000
2.250 1.1253 0.00623 0.00239 -0.2100 0.6813 1.0000
2.500 1.1493 0.00635 0.00246 -0.2092 0.6732 1.0000
2.750 1.1734 0.00644 0.00254 -0.2084 0.6653 1.0000
3.000 1.1966 0.00656 0.00262 -0.2075 0.6572 1.0000
3.250 1.2193 0.00668 0.00272 -0.2065 0.6481 1.0000
3.500 1.2427 0.00679 0.00282 -0.2056 0.6399 1.0000
3.750 1.2644 0.00695 0.00294 -0.2043 0.6302 1.0000
4.000 1.2866 0.00709 0.00307 -0.2032 0.6188 1.0000
4.250 1.3063 0.00729 0.00321 -0.2015 0.6034 1.0000
4.500 1.3245 0.00755 0.00339 -0.1996 0.5845 1.0000
4.750 1.3406 0.00788 0.00360 -0.1972 0.5565 1.0000
5.000 1.3564 0.00826 0.00386 -0.1948 0.5280 1.0000
5.250 1.3696 0.00878 0.00420 -0.1920 0.4919 1.0000
5.500 1.3838 0.00931 0.00456 -0.1894 0.4571 1.0000
5.750 1.3983 0.00984 0.00494 -0.1869 0.4250 1.0000
6.000 1.4130 0.01040 0.00534 -0.1846 0.3936 1.0000
6.250 1.4268 0.01102 0.00579 -0.1820 0.3592 1.0000
6.500 1.4405 0.01164 0.00625 -0.1796 0.3278 1.0000
6.750 1.4551 0.01222 0.00671 -0.1773 0.3017 1.0000
7.000 1.4663 0.01299 0.00729 -0.1744 0.2662 1.0000
7.250 1.4766 0.01383 0.00794 -0.1715 0.2299 1.0000
7.500 1.4858 0.01473 0.00864 -0.1684 0.1947 1.0000
7.750 1.4929 0.01580 0.00948 -0.1650 0.1556 1.0000
8.000 1.4979 0.01700 0.01044 -0.1614 0.1157 1.0000
8.250 1.4979 0.01856 0.01171 -0.1571 0.0691 1.0000
8.500 1.4980 0.02021 0.01311 -0.1530 0.0287 1.0000
8.750 1.5051 0.02146 0.01428 -0.1500 0.0141 1.0000
9.000 1.5181 0.02232 0.01516 -0.1479 0.0118 1.0000
9.250 1.5323 0.02311 0.01599 -0.1461 0.0110 1.0000
9.500 1.5453 0.02399 0.01690 -0.1441 0.0103 1.0000
9.750 1.5575 0.02495 0.01792 -0.1422 0.0097 1.0000
10.000 1.5678 0.02609 0.01912 -0.1400 0.0093 1.0000
10.250 1.5803 0.02707 0.02016 -0.1381 0.0092 1.0000
10.500 1.5916 0.02816 0.02132 -0.1362 0.0089 1.0000
10.750 1.6023 0.02933 0.02255 -0.1343 0.0088 1.0000
11.000 1.6121 0.03060 0.02389 -0.1324 0.0085 1.0000
11.250 1.6210 0.03198 0.02534 -0.1304 0.0083 1.0000
11.500 1.6297 0.03340 0.02684 -0.1286 0.0082 1.0000
11.750 1.6377 0.03492 0.02842 -0.1267 0.0079 1.0000
12.000 1.6444 0.03660 0.03017 -0.1248 0.0077 1.0000
12.250 1.6503 0.03841 0.03206 -0.1230 0.0076 1.0000
12.500 1.6541 0.04047 0.03421 -0.1211 0.0075 1.0000
12.750 1.6565 0.04274 0.03656 -0.1192 0.0074 1.0000
13.000 1.6567 0.04529 0.03922 -0.1173 0.0072 1.0000
13.250 1.6548 0.04818 0.04222 -0.1155 0.0071 1.0000
13.500 1.6514 0.05135 0.04549 -0.1138 0.0071 1.0000
13.750 1.6472 0.05472 0.04897 -0.1123 0.0070 1.0000
14.000 1.6412 0.05842 0.05279 -0.1108 0.0069 1.0000
14.250 1.6423 0.06135 0.05581 -0.1099 0.0069 1.0000
14.500 1.6440 0.06428 0.05884 -0.1091 0.0069 1.0000
14.750 1.6450 0.06736 0.06201 -0.1085 0.0069 1.0000
15.000 1.6460 0.07051 0.06526 -0.1079 0.0068 1.0000
15.250 1.6468 0.07374 0.06859 -0.1075 0.0068 1.0000
15.500 1.6470 0.07713 0.07208 -0.1072 0.0067 1.0000
15.750 1.6466 0.08067 0.07572 -0.1070 0.0067 1.0000
16.000 1.6463 0.08424 0.07940 -0.1070 0.0066 1.0000
16.250 1.6456 0.08792 0.08318 -0.1071 0.0066 1.0000
16.500 1.6450 0.09163 0.08701 -0.1073 0.0065 1.0000
16.750 1.6441 0.09547 0.09095 -0.1078 0.0064 1.0000
17.000 1.6426 0.09945 0.09504 -0.1083 0.0063 1.0000
17.250 1.6410 0.10350 0.09921 -0.1091 0.0062 1.0000
17.500 1.6388 0.10764 0.10347 -0.1100 0.0062 1.0000
17.750 1.6362 0.11191 0.10785 -0.1110 0.0061 1.0000
18.000 1.6332 0.11625 0.11231 -0.1122 0.0060 1.0000
18.250 1.6299 0.12069 0.11687 -0.1136 0.0060 1.0000
18.500 1.6264 0.12523 0.12152 -0.1152 0.0059 1.0000
18.750 1.6221 0.12991 0.12633 -0.1169 0.0059 1.0000
19.000 1.6177 0.13467 0.13120 -0.1190 0.0058 1.0000
19.250 1.6128 0.13953 0.13619 -0.1212 0.0058 1.0000
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