AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 500,000 Max Cl/Cd: 104.01 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah6407-il-500000-n5.txt Download as CSV file: xf-ah6407-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH-6-40-7 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3147 0.11190 0.10960 -0.0293 1.0000 0.0074
-9.250 -0.3128 0.10950 0.10723 -0.0289 1.0000 0.0072
-9.000 -0.3130 0.10719 0.10493 -0.0282 1.0000 0.0070
-8.750 -0.3059 0.10390 0.10166 -0.0298 0.9987 0.0069
-8.500 -0.2931 0.09995 0.09772 -0.0333 0.9965 0.0068
-8.250 -0.2800 0.09598 0.09375 -0.0369 0.9940 0.0068
-8.000 -0.2669 0.09199 0.08976 -0.0406 0.9905 0.0069
-7.750 -0.2526 0.08703 0.08481 -0.0459 0.9872 0.0074
-7.500 -0.2380 0.08261 0.08039 -0.0506 0.9815 0.0076
-7.250 -0.2189 0.07827 0.07605 -0.0562 0.9779 0.0075
-6.250 -0.0351 0.01750 0.01367 -0.1444 0.9551 0.0092
-6.000 -0.0013 0.01518 0.01088 -0.1469 0.9516 0.0103
-5.750 0.0312 0.01356 0.00883 -0.1485 0.9481 0.0111
-5.500 0.0616 0.01254 0.00760 -0.1493 0.9429 0.0125
-5.250 0.0910 0.01225 0.00724 -0.1496 0.9385 0.0138
-5.000 0.1198 0.01190 0.00677 -0.1498 0.9328 0.0155
-4.750 0.1488 0.01154 0.00630 -0.1500 0.9275 0.0174
-4.500 0.1769 0.01161 0.00638 -0.1499 0.9217 0.0191
-4.250 0.2054 0.01139 0.00607 -0.1500 0.9155 0.0215
-4.000 0.2336 0.01129 0.00586 -0.1499 0.9084 0.0237
-3.750 0.2614 0.01104 0.00547 -0.1497 0.8979 0.0250
-3.500 0.2894 0.01058 0.00491 -0.1496 0.8840 0.0275
-3.250 0.3171 0.01044 0.00469 -0.1494 0.8705 0.0295
-3.000 0.3456 0.01020 0.00433 -0.1494 0.8595 0.0312
-2.750 0.3740 0.01000 0.00403 -0.1494 0.8493 0.0328
-2.500 0.4026 0.00974 0.00367 -0.1495 0.8384 0.0336
-2.250 0.4311 0.00951 0.00333 -0.1495 0.8263 0.0341
-2.000 0.4596 0.00933 0.00306 -0.1495 0.8127 0.0346
-1.750 0.4877 0.00923 0.00286 -0.1494 0.7971 0.0351
-1.500 0.5161 0.00906 0.00258 -0.1494 0.7804 0.0354
-1.250 0.5448 0.00886 0.00226 -0.1495 0.7634 0.0366
-1.000 0.5733 0.00875 0.00205 -0.1495 0.7469 0.0389
-0.750 0.6014 0.00871 0.00194 -0.1495 0.7296 0.0422
-0.500 0.6293 0.00873 0.00185 -0.1494 0.7096 0.0459
-0.250 0.6570 0.00877 0.00180 -0.1493 0.6871 0.0523
0.000 0.6847 0.00876 0.00180 -0.1493 0.6633 0.0928
0.250 0.7124 0.00878 0.00184 -0.1493 0.6388 0.1367
0.500 0.7397 0.00887 0.00191 -0.1492 0.6126 0.1781
0.750 0.7668 0.00901 0.00199 -0.1490 0.5841 0.2106
1.000 0.7937 0.00914 0.00210 -0.1490 0.5522 0.2583
1.250 0.8207 0.00922 0.00227 -0.1490 0.5186 0.3569
1.500 0.8445 0.00848 0.00255 -0.1485 0.4879 0.8444
1.750 0.8676 0.00853 0.00257 -0.1474 0.4619 1.0000
2.000 0.8943 0.00880 0.00270 -0.1472 0.4391 1.0000
2.250 0.9212 0.00905 0.00283 -0.1470 0.4191 1.0000
2.500 0.9480 0.00929 0.00298 -0.1468 0.4015 1.0000
2.750 0.9748 0.00952 0.00313 -0.1467 0.3857 1.0000
3.000 1.0016 0.00975 0.00329 -0.1465 0.3713 1.0000
3.250 1.0283 0.00999 0.00347 -0.1463 0.3573 1.0000
3.500 1.0549 0.01023 0.00365 -0.1461 0.3444 1.0000
3.750 1.0815 0.01046 0.00384 -0.1459 0.3333 1.0000
4.000 1.1080 0.01069 0.00405 -0.1457 0.3231 1.0000
4.250 1.1346 0.01091 0.00426 -0.1455 0.3143 1.0000
4.500 1.1607 0.01116 0.00449 -0.1452 0.3046 1.0000
4.750 1.1867 0.01143 0.00473 -0.1449 0.2926 1.0000
5.000 1.2127 0.01169 0.00499 -0.1446 0.2813 1.0000
5.500 1.2624 0.01243 0.00556 -0.1438 0.2404 1.0000
5.750 1.2871 0.01281 0.00587 -0.1433 0.2223 1.0000
6.000 1.3113 0.01325 0.00623 -0.1428 0.2013 1.0000
6.250 1.3330 0.01397 0.00670 -0.1420 0.1531 1.0000
6.500 1.3503 0.01525 0.00757 -0.1405 0.0876 1.0000
6.750 1.3685 0.01639 0.00843 -0.1391 0.0433 1.0000
7.000 1.3876 0.01740 0.00928 -0.1377 0.0160 1.0000
7.250 1.4094 0.01802 0.00995 -0.1367 0.0123 1.0000
7.500 1.4306 0.01870 0.01070 -0.1356 0.0100 1.0000
7.750 1.4522 0.01927 0.01136 -0.1346 0.0091 1.0000
8.000 1.4728 0.01991 0.01209 -0.1334 0.0082 1.0000
8.250 1.4918 0.02070 0.01293 -0.1320 0.0072 1.0000
8.500 1.5097 0.02155 0.01388 -0.1304 0.0066 1.0000
8.750 1.5277 0.02233 0.01476 -0.1289 0.0062 1.0000
9.000 1.5442 0.02318 0.01574 -0.1271 0.0058 1.0000
9.250 1.5591 0.02408 0.01674 -0.1250 0.0054 1.0000
9.500 1.5722 0.02504 0.01778 -0.1227 0.0052 1.0000
9.750 1.5828 0.02609 0.01892 -0.1201 0.0049 1.0000
10.000 1.5865 0.02741 0.02034 -0.1163 0.0047 1.0000
10.250 1.5893 0.02882 0.02188 -0.1125 0.0045 1.0000
10.500 1.5964 0.03001 0.02319 -0.1096 0.0043 1.0000
10.750 1.6025 0.03134 0.02464 -0.1067 0.0041 1.0000
11.000 1.6075 0.03280 0.02623 -0.1040 0.0039 1.0000
11.250 1.6102 0.03454 0.02809 -0.1011 0.0037 1.0000
11.500 1.6120 0.03643 0.03011 -0.0985 0.0036 1.0000
11.750 1.6132 0.03848 0.03229 -0.0960 0.0035 1.0000
12.000 1.6134 0.04071 0.03468 -0.0938 0.0034 1.0000
12.250 1.6130 0.04312 0.03722 -0.0918 0.0033 1.0000
12.500 1.6115 0.04578 0.04001 -0.0901 0.0033 1.0000
12.750 1.6092 0.04863 0.04298 -0.0887 0.0032 1.0000
13.000 1.6046 0.05192 0.04641 -0.0875 0.0031 1.0000
13.250 1.5987 0.05553 0.05016 -0.0866 0.0031 1.0000
13.500 1.5904 0.05962 0.05439 -0.0861 0.0030 1.0000
13.750 1.5800 0.06417 0.05910 -0.0859 0.0030 1.0000
14.000 1.5678 0.06923 0.06433 -0.0861 0.0029 1.0000
14.250 1.5580 0.07419 0.06944 -0.0867 0.0029 1.0000
14.500 1.5486 0.07930 0.07473 -0.0877 0.0029 1.0000
14.750 1.5388 0.08470 0.08029 -0.0890 0.0028 1.0000
15.000 1.5280 0.09042 0.08618 -0.0906 0.0028 1.0000
15.250 1.5165 0.09638 0.09231 -0.0926 0.0028 1.0000
15.500 1.5045 0.10260 0.09869 -0.0948 0.0028 1.0000
15.750 1.4923 0.10900 0.10525 -0.0972 0.0028 1.0000
16.000 1.4799 0.11559 0.11201 -0.1000 0.0028 1.0000
16.250 1.4673 0.12237 0.11895 -0.1030 0.0027 1.0000
16.500 1.4547 0.12926 0.12599 -0.1062 0.0027 1.0000
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Polar data table (+)
Polar graphs
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