AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 1,000,000 Max Cl/Cd: 153.73 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100b-il-1000000-n5.txt Download as CSV file: xf-ah79100b-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2314 0.14510 0.14329 -0.0603 0.9923 0.0068
-13.000 -0.2208 0.14135 0.13954 -0.0629 0.9911 0.0069
-9.500 -0.1813 0.01870 0.01537 -0.1941 0.8528 0.0061
-9.250 -0.1555 0.01659 0.01294 -0.1964 0.8414 0.0063
-9.000 -0.1284 0.01521 0.01129 -0.1978 0.8316 0.0065
-8.750 -0.1009 0.01417 0.01002 -0.1989 0.8231 0.0067
-8.500 -0.0729 0.01334 0.00899 -0.1998 0.8157 0.0069
-8.250 -0.0446 0.01259 0.00806 -0.2006 0.8095 0.0071
-8.000 -0.0159 0.01195 0.00729 -0.2014 0.8036 0.0076
-7.750 0.0124 0.01149 0.00673 -0.2019 0.7978 0.0080
-7.500 0.0411 0.01108 0.00622 -0.2024 0.7926 0.0085
-7.250 0.0699 0.01069 0.00573 -0.2029 0.7871 0.0092
-7.000 0.0983 0.01037 0.00531 -0.2033 0.7813 0.0099
-6.750 0.1267 0.01020 0.00511 -0.2036 0.7757 0.0108
-6.500 0.1550 0.01001 0.00484 -0.2038 0.7696 0.0118
-6.250 0.1834 0.00981 0.00455 -0.2041 0.7644 0.0125
-6.000 0.2122 0.00963 0.00432 -0.2044 0.7596 0.0134
-5.750 0.2404 0.00957 0.00424 -0.2046 0.7548 0.0143
-5.250 0.2974 0.00934 0.00391 -0.2050 0.7465 0.0160
-5.000 0.3261 0.00922 0.00372 -0.2053 0.7418 0.0164
-4.750 0.3555 0.00888 0.00331 -0.2058 0.7369 0.0173
-4.500 0.3843 0.00876 0.00317 -0.2061 0.7324 0.0182
-4.250 0.4130 0.00866 0.00304 -0.2064 0.7276 0.0192
-4.000 0.4418 0.00852 0.00285 -0.2067 0.7227 0.0200
-3.750 0.4709 0.00835 0.00262 -0.2070 0.7176 0.0205
-3.500 0.4997 0.00824 0.00245 -0.2073 0.7112 0.0211
-3.250 0.5284 0.00810 0.00224 -0.2076 0.7053 0.0217
-3.000 0.5581 0.00791 0.00202 -0.2081 0.7005 0.0227
-2.750 0.5872 0.00781 0.00189 -0.2084 0.6960 0.0237
-2.500 0.6159 0.00774 0.00178 -0.2086 0.6918 0.0248
-2.250 0.6448 0.00767 0.00168 -0.2089 0.6875 0.0261
-2.000 0.6735 0.00762 0.00160 -0.2091 0.6822 0.0274
-1.750 0.7020 0.00756 0.00153 -0.2093 0.6765 0.0314
-1.500 0.7307 0.00752 0.00148 -0.2095 0.6711 0.0355
-1.250 0.7590 0.00749 0.00145 -0.2097 0.6640 0.0437
-1.000 0.7874 0.00746 0.00142 -0.2098 0.6576 0.0558
-0.750 0.8160 0.00742 0.00142 -0.2101 0.6514 0.0777
-0.500 0.8444 0.00737 0.00142 -0.2103 0.6460 0.1126
-0.250 0.8744 0.00720 0.00144 -0.2110 0.6407 0.2003
0.000 0.9047 0.00696 0.00151 -0.2119 0.6345 0.3438
0.250 0.9334 0.00691 0.00157 -0.2122 0.6290 0.4112
0.500 0.9620 0.00688 0.00164 -0.2125 0.6226 0.4638
0.750 0.9897 0.00691 0.00173 -0.2126 0.6151 0.5123
1.000 1.0175 0.00694 0.00181 -0.2126 0.6059 0.5491
1.250 1.0448 0.00701 0.00189 -0.2126 0.5967 0.5706
1.750 1.0986 0.00721 0.00206 -0.2123 0.5767 0.5984
2.000 1.1253 0.00732 0.00216 -0.2121 0.5658 0.6140
2.250 1.1510 0.00749 0.00228 -0.2118 0.5483 0.6275
2.500 1.1759 0.00772 0.00244 -0.2113 0.5257 0.6438
2.750 1.2012 0.00793 0.00260 -0.2108 0.5070 0.6620
3.000 1.2271 0.00809 0.00276 -0.2106 0.4938 0.6814
3.250 1.2530 0.00826 0.00292 -0.2103 0.4811 0.7028
3.500 1.2788 0.00842 0.00310 -0.2100 0.4682 0.7272
3.750 1.3043 0.00860 0.00329 -0.2096 0.4546 0.7559
4.250 1.3516 0.00906 0.00378 -0.2082 0.4141 0.8458
4.500 1.3679 0.00922 0.00399 -0.2058 0.3905 1.0000
4.750 1.3918 0.00954 0.00423 -0.2052 0.3735 1.0000
5.000 1.4156 0.00985 0.00449 -0.2045 0.3564 1.0000
5.250 1.4354 0.01045 0.00488 -0.2032 0.3197 1.0000
5.500 1.4536 0.01117 0.00535 -0.2016 0.2753 1.0000
5.750 1.4727 0.01179 0.00580 -0.2002 0.2428 1.0000
6.000 1.4895 0.01255 0.00634 -0.1984 0.2046 1.0000
6.250 1.5050 0.01338 0.00695 -0.1963 0.1642 1.0000
6.500 1.5176 0.01437 0.00768 -0.1938 0.1197 1.0000
6.750 1.5267 0.01543 0.00849 -0.1906 0.0760 1.0000
7.000 1.5395 0.01617 0.00911 -0.1879 0.0562 1.0000
7.250 1.5554 0.01671 0.00963 -0.1859 0.0482 1.0000
7.500 1.5723 0.01719 0.01011 -0.1841 0.0435 1.0000
7.750 1.5880 0.01775 0.01067 -0.1821 0.0386 1.0000
8.000 1.6050 0.01824 0.01118 -0.1804 0.0351 1.0000
8.250 1.6177 0.01899 0.01189 -0.1780 0.0259 1.0000
8.500 1.6296 0.01982 0.01268 -0.1755 0.0186 1.0000
8.750 1.6426 0.02060 0.01346 -0.1733 0.0143 1.0000
9.000 1.6547 0.02144 0.01432 -0.1710 0.0109 1.0000
9.250 1.6666 0.02233 0.01523 -0.1688 0.0089 1.0000
9.500 1.6794 0.02318 0.01612 -0.1668 0.0080 1.0000
9.750 1.6913 0.02412 0.01710 -0.1647 0.0074 1.0000
10.000 1.7021 0.02517 0.01819 -0.1626 0.0067 1.0000
10.250 1.7131 0.02623 0.01930 -0.1605 0.0063 1.0000
10.500 1.7243 0.02731 0.02046 -0.1587 0.0060 1.0000
10.750 1.7349 0.02848 0.02169 -0.1568 0.0057 1.0000
11.000 1.7445 0.02976 0.02303 -0.1549 0.0055 1.0000
11.250 1.7536 0.03113 0.02446 -0.1530 0.0052 1.0000
11.500 1.7617 0.03264 0.02603 -0.1512 0.0050 1.0000
11.750 1.7689 0.03427 0.02773 -0.1494 0.0048 1.0000
12.000 1.7743 0.03613 0.02967 -0.1475 0.0046 1.0000
12.250 1.7788 0.03815 0.03178 -0.1457 0.0044 1.0000
12.500 1.7862 0.03991 0.03362 -0.1442 0.0043 1.0000
12.750 1.7922 0.04187 0.03567 -0.1428 0.0042 1.0000
13.000 1.7978 0.04391 0.03779 -0.1414 0.0041 1.0000
13.250 1.8029 0.04608 0.04004 -0.1401 0.0040 1.0000
13.500 1.8070 0.04843 0.04248 -0.1389 0.0039 1.0000
13.750 1.8108 0.05086 0.04500 -0.1378 0.0038 1.0000
14.000 1.8147 0.05334 0.04757 -0.1368 0.0037 1.0000
14.250 1.8169 0.05610 0.05043 -0.1359 0.0036 1.0000
14.500 1.8198 0.05884 0.05325 -0.1351 0.0035 1.0000
14.750 1.8228 0.06160 0.05610 -0.1344 0.0033 1.0000
15.000 1.8235 0.06479 0.05939 -0.1338 0.0033 1.0000
15.250 1.8237 0.06810 0.06278 -0.1334 0.0032 1.0000
15.500 1.8230 0.07159 0.06637 -0.1331 0.0031 1.0000
15.750 1.8188 0.07573 0.07062 -0.1329 0.0030 1.0000
16.000 1.8158 0.07979 0.07479 -0.1330 0.0029 1.0000
16.250 1.8077 0.08476 0.07989 -0.1332 0.0028 1.0000
16.500 1.8047 0.08898 0.08422 -0.1336 0.0028 1.0000
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