AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 200,000 Max Cl/Cd: 101 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79100b-il-200000-n5.txt Download as CSV file: xf-ah79100b-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1288 0.10389 0.10025 -0.0769 0.9584 0.0222
-9.000 -0.1136 0.10038 0.09674 -0.0800 0.9546 0.0226
-8.750 -0.1027 0.09730 0.09365 -0.0820 0.9466 0.0229
-8.500 -0.0871 0.09375 0.09009 -0.0855 0.9422 0.0234
-8.250 -0.0741 0.09047 0.08680 -0.0883 0.9348 0.0239
-8.000 -0.0572 0.08675 0.08308 -0.0925 0.9297 0.0240
-7.750 -0.0405 0.08314 0.07945 -0.0966 0.9234 0.0246
-7.500 -0.0245 0.07825 0.07453 -0.1021 0.9161 0.0202
-7.250 -0.0046 0.07425 0.07050 -0.1070 0.9099 0.0190
-7.000 0.0147 0.07013 0.06635 -0.1126 0.9021 0.0191
-6.750 0.0336 0.06612 0.06231 -0.1183 0.8936 0.0194
-6.500 0.0569 0.06174 0.05789 -0.1255 0.8855 0.0197
-6.250 0.0769 0.05659 0.05269 -0.1337 0.8753 0.0204
-6.000 0.1033 0.05131 0.04735 -0.1429 0.8676 0.0202
-5.750 0.1329 0.04444 0.04036 -0.1553 0.8586 0.0201
-5.500 0.1788 0.03290 0.02831 -0.1742 0.8512 0.0203
-5.250 0.2232 0.02553 0.02019 -0.1850 0.8449 0.0223
-5.000 0.2574 0.02440 0.01884 -0.1878 0.8402 0.0244
-4.750 0.2967 0.02068 0.01435 -0.1923 0.8345 0.0268
-4.500 0.3304 0.01914 0.01247 -0.1947 0.8292 0.0290
-4.250 0.3645 0.01796 0.01100 -0.1965 0.8244 0.0303
-4.000 0.3944 0.01703 0.00982 -0.1973 0.8178 0.0319
-3.750 0.4265 0.01627 0.00879 -0.1984 0.8126 0.0342
-3.500 0.4575 0.01551 0.00781 -0.1992 0.8079 0.0352
-3.250 0.4870 0.01471 0.00689 -0.1998 0.8025 0.0363
-3.000 0.5179 0.01411 0.00623 -0.2006 0.7978 0.0381
-2.750 0.5480 0.01380 0.00586 -0.2013 0.7931 0.0410
-2.500 0.5769 0.01348 0.00549 -0.2016 0.7875 0.0438
-2.250 0.6075 0.01318 0.00509 -0.2023 0.7826 0.0461
-2.000 0.6384 0.01283 0.00471 -0.2032 0.7773 0.0508
-1.750 0.6675 0.01267 0.00450 -0.2035 0.7710 0.0581
-1.500 0.6987 0.01246 0.00426 -0.2043 0.7661 0.0736
-1.250 0.7284 0.01223 0.00415 -0.2049 0.7606 0.1149
-1.000 0.7608 0.01169 0.00417 -0.2066 0.7552 0.3100
-0.750 0.7914 0.01148 0.00427 -0.2074 0.7504 0.4627
-0.500 0.8179 0.01147 0.00440 -0.2071 0.7434 0.5323
-0.250 0.8456 0.01147 0.00447 -0.2070 0.7374 0.5885
0.000 0.8723 0.01148 0.00457 -0.2066 0.7314 0.6397
0.250 0.8987 0.01151 0.00465 -0.2063 0.7257 0.6737
0.500 0.9263 0.01154 0.00467 -0.2061 0.7209 0.6966
0.750 0.9522 0.01158 0.00477 -0.2057 0.7147 0.7203
1.000 0.9785 0.01162 0.00482 -0.2053 0.7088 0.7456
1.250 1.0040 0.01164 0.00487 -0.2047 0.7027 0.7761
1.500 1.0275 0.01164 0.00493 -0.2037 0.6955 0.8136
1.750 1.0482 0.01157 0.00493 -0.2020 0.6890 0.8725
2.000 1.0708 0.01154 0.00494 -0.2008 0.6814 1.0000
2.500 1.1262 0.01184 0.00517 -0.2009 0.6683 1.0000
2.750 1.1539 0.01198 0.00529 -0.2009 0.6618 1.0000
3.000 1.1803 0.01215 0.00546 -0.2007 0.6539 1.0000
3.250 1.2075 0.01230 0.00557 -0.2006 0.6467 1.0000
3.500 1.2333 0.01248 0.00577 -0.2003 0.6377 1.0000
3.750 1.2594 0.01265 0.00594 -0.2000 0.6286 1.0000
4.000 1.2849 0.01283 0.00613 -0.1996 0.6187 1.0000
4.250 1.3100 0.01303 0.00635 -0.1991 0.6088 1.0000
4.500 1.3349 0.01324 0.00658 -0.1986 0.5976 1.0000
4.750 1.3594 0.01346 0.00679 -0.1979 0.5858 1.0000
5.000 1.3833 0.01370 0.00703 -0.1972 0.5727 1.0000
5.250 1.4062 0.01398 0.00729 -0.1963 0.5576 1.0000
5.500 1.4283 0.01428 0.00761 -0.1952 0.5402 1.0000
5.750 1.4494 0.01463 0.00793 -0.1939 0.5208 1.0000
6.000 1.4700 0.01502 0.00829 -0.1926 0.5023 1.0000
6.250 1.4897 0.01546 0.00869 -0.1911 0.4832 1.0000
6.500 1.5083 0.01594 0.00915 -0.1895 0.4610 1.0000
6.750 1.5253 0.01649 0.00965 -0.1876 0.4399 1.0000
7.000 1.5418 0.01706 0.01020 -0.1856 0.4176 1.0000
7.250 1.5561 0.01772 0.01080 -0.1833 0.3945 1.0000
7.500 1.5668 0.01847 0.01147 -0.1803 0.3682 1.0000
7.750 1.5736 0.01937 0.01228 -0.1767 0.3358 1.0000
8.000 1.5768 0.02050 0.01324 -0.1727 0.2986 1.0000
8.250 1.5760 0.02194 0.01445 -0.1683 0.2549 1.0000
8.500 1.5728 0.02370 0.01593 -0.1639 0.2089 1.0000
9.000 1.5641 0.02790 0.01959 -0.1558 0.1193 1.0000
9.250 1.5623 0.03005 0.02156 -0.1525 0.0875 1.0000
9.500 1.5640 0.03203 0.02346 -0.1497 0.0696 1.0000
9.750 1.5678 0.03391 0.02535 -0.1474 0.0587 1.0000
10.000 1.5731 0.03572 0.02722 -0.1453 0.0503 1.0000
10.250 1.5783 0.03761 0.02917 -0.1433 0.0429 1.0000
10.500 1.5821 0.03970 0.03131 -0.1414 0.0359 1.0000
10.750 1.5862 0.04182 0.03348 -0.1397 0.0289 1.0000
11.000 1.5897 0.04407 0.03580 -0.1380 0.0244 1.0000
11.250 1.5909 0.04664 0.03842 -0.1363 0.0216 1.0000
11.500 1.5930 0.04919 0.04113 -0.1347 0.0195 1.0000
11.750 1.5938 0.05195 0.04400 -0.1333 0.0180 1.0000
12.000 1.5917 0.05514 0.04730 -0.1320 0.0167 1.0000
12.250 1.5922 0.05813 0.05043 -0.1309 0.0157 1.0000
12.500 1.5934 0.06111 0.05356 -0.1300 0.0147 1.0000
12.750 1.5937 0.06429 0.05687 -0.1292 0.0139 1.0000
13.000 1.5931 0.06765 0.06037 -0.1285 0.0133 1.0000
13.250 1.5909 0.07133 0.06417 -0.1280 0.0128 1.0000
13.500 1.5866 0.07542 0.06838 -0.1276 0.0124 1.0000
13.750 1.5833 0.07945 0.07255 -0.1274 0.0121 1.0000
14.000 1.5823 0.08321 0.07647 -0.1273 0.0118 1.0000
14.250 1.5812 0.08706 0.08050 -0.1272 0.0114 1.0000
14.500 1.5802 0.09094 0.08453 -0.1273 0.0112 1.0000
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Polar data table (+)
Polar graphs
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