AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 500,000 Max Cl/Cd: 139.59 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100b-il-500000-n5.txt Download as CSV file: xf-ah79100b-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1560 0.11628 0.11384 -0.0728 0.9744 0.0108
-10.500 -0.1453 0.11289 0.11045 -0.0750 0.9696 0.0111
-10.250 -0.1362 0.10943 0.10698 -0.0770 0.9636 0.0106
-9.500 -0.1015 0.09769 0.09523 -0.0879 0.9436 0.0126
-9.000 -0.0668 0.08814 0.08563 -0.0967 0.9324 0.0094
-8.750 -0.0414 0.08396 0.08141 -0.1031 0.9273 0.0092
-8.500 -0.0149 0.07921 0.07661 -0.1107 0.9188 0.0091
-8.250 0.0166 0.07382 0.07115 -0.1203 0.9105 0.0091
-8.000 0.0452 0.06872 0.06596 -0.1292 0.8991 0.0090
-7.750 0.0606 0.06350 0.06066 -0.1356 0.8810 0.0093
-7.500 0.0690 0.05992 0.05700 -0.1388 0.8639 0.0093
-7.250 0.0686 0.05489 0.05192 -0.1429 0.8483 0.0095
-7.000 0.0771 0.05066 0.04764 -0.1480 0.8361 0.0097
-6.750 0.1087 0.01592 0.01109 -0.1969 0.8192 0.0121
-6.500 0.1388 0.01478 0.00965 -0.1984 0.8134 0.0130
-6.250 0.1666 0.01488 0.00974 -0.1985 0.8079 0.0137
-6.000 0.1954 0.01440 0.00910 -0.1992 0.8020 0.0148
-5.750 0.2256 0.01348 0.00786 -0.2002 0.7964 0.0162
-5.500 0.2550 0.01279 0.00701 -0.2010 0.7907 0.0171
-5.250 0.2834 0.01257 0.00672 -0.2014 0.7846 0.0180
-5.000 0.3119 0.01241 0.00646 -0.2017 0.7791 0.0193
-4.750 0.3407 0.01213 0.00606 -0.2020 0.7739 0.0207
-4.500 0.3701 0.01165 0.00545 -0.2026 0.7693 0.0218
-4.250 0.3996 0.01120 0.00489 -0.2032 0.7650 0.0227
-4.000 0.4287 0.01087 0.00451 -0.2037 0.7603 0.0235
-3.750 0.4578 0.01061 0.00419 -0.2041 0.7553 0.0246
-3.500 0.4870 0.01038 0.00387 -0.2045 0.7508 0.0258
-3.250 0.5163 0.01011 0.00354 -0.2049 0.7460 0.0266
-3.000 0.5455 0.00989 0.00326 -0.2053 0.7407 0.0273
-2.750 0.5753 0.00964 0.00292 -0.2059 0.7357 0.0285
-2.500 0.6046 0.00944 0.00271 -0.2063 0.7300 0.0302
-2.250 0.6334 0.00933 0.00256 -0.2065 0.7243 0.0325
-2.000 0.6620 0.00926 0.00243 -0.2068 0.7192 0.0351
-1.750 0.6913 0.00912 0.00228 -0.2071 0.7138 0.0399
-1.500 0.7199 0.00906 0.00218 -0.2074 0.7088 0.0459
-1.250 0.7487 0.00899 0.00212 -0.2076 0.7040 0.0591
-0.750 0.8075 0.00870 0.00207 -0.2087 0.6937 0.1617
-0.500 0.8383 0.00839 0.00211 -0.2098 0.6888 0.3168
-0.250 0.8677 0.00823 0.00220 -0.2103 0.6823 0.4287
0.000 0.8956 0.00824 0.00226 -0.2104 0.6759 0.4789
0.250 0.9238 0.00822 0.00235 -0.2105 0.6693 0.5325
0.500 0.9514 0.00824 0.00243 -0.2105 0.6631 0.5730
0.750 0.9791 0.00827 0.00251 -0.2105 0.6572 0.6048
1.000 1.0065 0.00832 0.00257 -0.2105 0.6510 0.6213
1.250 1.0338 0.00839 0.00264 -0.2103 0.6453 0.6392
1.500 1.0611 0.00844 0.00274 -0.2103 0.6387 0.6567
1.750 1.0879 0.00852 0.00282 -0.2101 0.6318 0.6747
2.000 1.1149 0.00857 0.00293 -0.2100 0.6236 0.6969
2.250 1.1412 0.00866 0.00304 -0.2097 0.6152 0.7205
2.750 1.1930 0.00880 0.00330 -0.2089 0.5961 0.7802
3.000 1.2172 0.00888 0.00343 -0.2082 0.5852 0.8210
3.250 1.2340 0.00884 0.00351 -0.2057 0.5723 0.9243
3.500 1.2582 0.00903 0.00365 -0.2050 0.5554 1.0000
3.750 1.2827 0.00927 0.00382 -0.2044 0.5368 1.0000
4.000 1.3070 0.00953 0.00401 -0.2038 0.5204 1.0000
4.250 1.3317 0.00977 0.00421 -0.2033 0.5082 1.0000
4.500 1.3560 0.01004 0.00445 -0.2027 0.4950 1.0000
4.750 1.3796 0.01034 0.00470 -0.2020 0.4771 1.0000
5.000 1.4014 0.01074 0.00499 -0.2009 0.4550 1.0000
5.250 1.4232 0.01114 0.00531 -0.1999 0.4346 1.0000
5.500 1.4453 0.01152 0.00564 -0.1989 0.4153 1.0000
5.750 1.4656 0.01199 0.00602 -0.1977 0.3926 1.0000
6.000 1.4855 0.01249 0.00642 -0.1963 0.3693 1.0000
6.250 1.5025 0.01315 0.00692 -0.1945 0.3352 1.0000
6.500 1.5171 0.01395 0.00752 -0.1923 0.2958 1.0000
6.750 1.5286 0.01489 0.00821 -0.1896 0.2520 1.0000
7.000 1.5366 0.01593 0.00900 -0.1862 0.2080 1.0000
7.250 1.5428 0.01709 0.00990 -0.1826 0.1641 1.0000
7.500 1.5489 0.01826 0.01086 -0.1791 0.1249 1.0000
7.750 1.5536 0.01956 0.01194 -0.1755 0.0884 1.0000
8.000 1.5600 0.02078 0.01303 -0.1723 0.0633 1.0000
8.250 1.5713 0.02171 0.01395 -0.1699 0.0528 1.0000
8.500 1.5835 0.02260 0.01484 -0.1677 0.0463 1.0000
8.750 1.5960 0.02349 0.01576 -0.1656 0.0410 1.0000
9.000 1.6079 0.02445 0.01675 -0.1635 0.0359 1.0000
9.250 1.6181 0.02556 0.01787 -0.1613 0.0279 1.0000
9.500 1.6261 0.02688 0.01917 -0.1589 0.0207 1.0000
9.750 1.6340 0.02826 0.02056 -0.1567 0.0162 1.0000
10.000 1.6429 0.02961 0.02196 -0.1546 0.0133 1.0000
10.250 1.6511 0.03106 0.02346 -0.1526 0.0116 1.0000
10.500 1.6596 0.03253 0.02501 -0.1507 0.0104 1.0000
10.750 1.6670 0.03416 0.02671 -0.1488 0.0096 1.0000
11.000 1.6730 0.03595 0.02858 -0.1469 0.0089 1.0000
11.250 1.6805 0.03766 0.03039 -0.1453 0.0085 1.0000
11.500 1.6869 0.03953 0.03236 -0.1436 0.0081 1.0000
11.750 1.6929 0.04149 0.03441 -0.1421 0.0077 1.0000
12.000 1.6980 0.04358 0.03659 -0.1406 0.0073 1.0000
12.250 1.7017 0.04589 0.03899 -0.1392 0.0070 1.0000
12.500 1.7033 0.04852 0.04171 -0.1378 0.0066 1.0000
12.750 1.7034 0.05142 0.04474 -0.1364 0.0064 1.0000
13.000 1.7069 0.05397 0.04740 -0.1354 0.0062 1.0000
13.250 1.7090 0.05676 0.05031 -0.1344 0.0061 1.0000
13.500 1.7099 0.05980 0.05347 -0.1336 0.0059 1.0000
13.750 1.7105 0.06296 0.05675 -0.1328 0.0058 1.0000
14.000 1.7106 0.06628 0.06019 -0.1323 0.0056 1.0000
14.250 1.7101 0.06973 0.06377 -0.1318 0.0055 1.0000
14.500 1.7091 0.07336 0.06751 -0.1315 0.0054 1.0000
14.750 1.7069 0.07724 0.07152 -0.1314 0.0052 1.0000
15.000 1.7049 0.08121 0.07562 -0.1315 0.0052 1.0000
15.250 1.7019 0.08540 0.07993 -0.1317 0.0051 1.0000
15.500 1.6993 0.08959 0.08425 -0.1321 0.0049 1.0000
15.750 1.6946 0.09422 0.08900 -0.1326 0.0048 1.0000
16.000 1.6906 0.09881 0.09371 -0.1334 0.0047 1.0000
16.250 1.6847 0.10379 0.09882 -0.1344 0.0046 1.0000
16.500 1.6770 0.10914 0.10429 -0.1357 0.0045 1.0000
16.750 1.6695 0.11448 0.10977 -0.1371 0.0045 1.0000
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Polar data table (+)
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