AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH-7-47-6 AIRFOIL (ah7476-il) Reynolds number: 500,000 Max Cl/Cd: 148.4 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah7476-il-500000.txt Download as CSV file: xf-ah7476-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH-7-47-6 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3566 0.12496 0.12268 -0.0216 1.0000 0.0142
-9.500 -0.3586 0.12310 0.12084 -0.0213 1.0000 0.0142
-9.250 -0.3630 0.12153 0.11932 -0.0208 1.0000 0.0142
-8.750 -0.3380 0.11306 0.11084 -0.0258 0.9975 0.0144
-8.500 -0.3239 0.10930 0.10708 -0.0278 0.9962 0.0146
-8.250 -0.3088 0.10586 0.10364 -0.0309 0.9949 0.0149
-8.000 -0.2948 0.10258 0.10035 -0.0339 0.9926 0.0152
-7.750 -0.2809 0.09932 0.09709 -0.0370 0.9897 0.0156
-7.500 -0.2658 0.09598 0.09375 -0.0406 0.9870 0.0162
-7.250 -0.2480 0.09241 0.09018 -0.0452 0.9848 0.0172
-7.000 -0.2246 0.08852 0.08628 -0.0530 0.9785 0.0178
-6.750 -0.1926 0.08390 0.08165 -0.0644 0.9747 0.0179
-6.250 -0.1433 0.07455 0.07227 -0.0747 0.9719 0.0183
-6.000 -0.1282 0.07168 0.06940 -0.0760 0.9663 0.0186
-5.750 -0.1007 0.06818 0.06587 -0.0813 0.9633 0.0191
-5.500 -0.0658 0.06418 0.06184 -0.0891 0.9612 0.0201
-5.250 -0.0046 0.05845 0.05603 -0.1059 0.9598 0.0222
-5.000 0.0656 0.05158 0.04901 -0.1244 0.9590 0.0224
-4.750 0.0956 0.04680 0.04421 -0.1296 0.9583 0.0230
-4.500 0.1162 0.04457 0.04195 -0.1310 0.9516 0.0234
-4.250 0.1576 0.04129 0.03861 -0.1377 0.9500 0.0244
-4.000 0.2116 0.03704 0.03423 -0.1476 0.9493 0.0264
-3.750 0.2939 0.02863 0.02533 -0.1645 0.9499 0.0287
-3.500 0.3330 0.02657 0.02322 -0.1689 0.9490 0.0295
-3.250 0.3771 0.02422 0.02072 -0.1740 0.9483 0.0310
-3.000 0.4268 0.02223 0.01830 -0.1787 0.9474 0.0350
-2.750 0.4723 0.01849 0.01432 -0.1845 0.9467 0.0372
-2.500 0.5107 0.01717 0.01289 -0.1875 0.9454 0.0396
0.000 0.8371 0.00915 0.00366 -0.1967 0.8945 0.0436
0.250 0.8684 0.00879 0.00329 -0.1973 0.8871 0.0430
0.500 0.8975 0.00859 0.00309 -0.1974 0.8774 0.0436
0.750 0.9267 0.00842 0.00289 -0.1975 0.8650 0.0436
1.000 0.9553 0.00832 0.00273 -0.1974 0.8495 0.0431
1.250 0.9832 0.00831 0.00263 -0.1971 0.8333 0.0429
1.500 1.0105 0.00835 0.00257 -0.1967 0.8158 0.0431
1.750 1.0371 0.00841 0.00257 -0.1962 0.7964 0.0438
2.000 1.0634 0.00849 0.00260 -0.1957 0.7757 0.0465
2.250 1.0894 0.00851 0.00271 -0.1951 0.7435 0.1467
2.500 1.1100 0.00748 0.00303 -0.1938 0.6950 1.0000
2.750 1.1304 0.00803 0.00319 -0.1920 0.6289 1.0000
3.000 1.1510 0.00865 0.00346 -0.1905 0.5694 1.0000
3.250 1.1726 0.00921 0.00376 -0.1892 0.5206 1.0000
3.500 1.1958 0.00964 0.00402 -0.1883 0.4876 1.0000
3.750 1.2197 0.01003 0.00427 -0.1875 0.4630 1.0000
4.000 1.2439 0.01039 0.00453 -0.1867 0.4427 1.0000
4.250 1.2682 0.01072 0.00481 -0.1860 0.4238 1.0000
4.500 1.2916 0.01113 0.00509 -0.1852 0.3987 1.0000
4.750 1.3154 0.01149 0.00536 -0.1844 0.3728 1.0000
5.000 1.3389 0.01187 0.00564 -0.1836 0.3426 1.0000
5.250 1.3603 0.01245 0.00600 -0.1824 0.2921 1.0000
5.500 1.3788 0.01333 0.00652 -0.1808 0.2313 1.0000
5.750 1.3986 0.01410 0.00706 -0.1794 0.1911 1.0000
6.000 1.4193 0.01476 0.00757 -0.1782 0.1606 1.0000
6.250 1.4398 0.01544 0.00810 -0.1769 0.1299 1.0000
6.500 1.4579 0.01635 0.00874 -0.1753 0.0867 1.0000
6.750 1.4757 0.01727 0.00947 -0.1735 0.0577 1.0000
7.000 1.4930 0.01822 0.01027 -0.1716 0.0324 1.0000
7.250 1.5103 0.01916 0.01111 -0.1695 0.0220 1.0000
7.500 1.5292 0.01986 0.01190 -0.1678 0.0197 1.0000
7.750 1.5460 0.02072 0.01281 -0.1658 0.0177 1.0000
8.000 1.5585 0.02192 0.01413 -0.1628 0.0163 1.0000
8.250 1.5741 0.02273 0.01504 -0.1605 0.0158 1.0000
8.500 1.5876 0.02365 0.01607 -0.1579 0.0152 1.0000
8.750 1.5988 0.02467 0.01720 -0.1548 0.0146 1.0000
9.000 1.6073 0.02575 0.01838 -0.1513 0.0140 1.0000
9.250 1.6153 0.02690 0.01961 -0.1478 0.0134 1.0000
9.500 1.6214 0.02824 0.02103 -0.1442 0.0128 1.0000
9.750 1.6227 0.03007 0.02297 -0.1399 0.0123 1.0000
10.000 1.6197 0.03259 0.02564 -0.1351 0.0119 1.0000
10.250 1.6263 0.03422 0.02740 -0.1320 0.0116 1.0000
10.500 1.6344 0.03567 0.02898 -0.1291 0.0114 1.0000
10.750 1.6412 0.03731 0.03078 -0.1262 0.0112 1.0000
11.000 1.6472 0.03910 0.03271 -0.1232 0.0110 1.0000
11.250 1.6521 0.04103 0.03480 -0.1203 0.0108 1.0000
11.500 1.6560 0.04316 0.03709 -0.1174 0.0106 1.0000
11.750 1.6587 0.04544 0.03954 -0.1145 0.0104 1.0000
12.000 1.6596 0.04794 0.04223 -0.1116 0.0102 1.0000
12.250 1.6588 0.05065 0.04514 -0.1088 0.0101 1.0000
12.500 1.6560 0.05360 0.04829 -0.1061 0.0100 1.0000
12.750 1.6518 0.05662 0.05149 -0.1036 0.0098 1.0000
13.000 1.6469 0.05973 0.05477 -0.1014 0.0096 1.0000
13.250 1.6407 0.06307 0.05828 -0.0995 0.0095 1.0000
13.500 1.6344 0.06642 0.06177 -0.0980 0.0093 1.0000
13.750 1.6243 0.07047 0.06599 -0.0967 0.0092 1.0000
14.000 1.6138 0.07467 0.07035 -0.0960 0.0091 1.0000
14.250 1.6003 0.07961 0.07549 -0.0956 0.0090 1.0000
14.500 1.5888 0.08441 0.08043 -0.0959 0.0089 1.0000
14.750 1.5734 0.09028 0.08650 -0.0970 0.0089 1.0000
15.000 1.5573 0.09663 0.09305 -0.0988 0.0088 1.0000
15.250 1.5395 0.10375 0.10040 -0.1015 0.0089 1.0000
15.500 1.5216 0.11133 0.10819 -0.1051 0.0089 1.0000
15.750 1.5017 0.11993 0.11702 -0.1097 0.0090 1.0000
16.000 1.4788 0.12983 0.12717 -0.1157 0.0091 1.0000
16.250 1.4374 0.14593 0.14364 -0.1269 0.0095 1.0000
16.500 1.3981 0.16326 0.16127 -0.1394 0.0100 1.0000
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Polar data table (+)
Polar graphs
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