AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.75 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah6407-il-1000000-n5.txt Download as CSV file: xf-ah6407-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3309 0.12250 0.12081 -0.0273 1.0000 0.0046
-10.250 -0.3262 0.11942 0.11775 -0.0281 1.0000 0.0043
-10.000 -0.3228 0.11621 0.11454 -0.0286 1.0000 0.0040
-9.750 -0.3214 0.11284 0.11119 -0.0289 1.0000 0.0038
-8.750 -0.2813 0.09746 0.09583 -0.0397 0.9932 0.0038
-7.750 -0.2047 0.01795 0.01497 -0.1412 0.9538 0.0051
-7.500 -0.1734 0.01537 0.01200 -0.1438 0.9499 0.0052
-7.250 -0.1423 0.01335 0.00962 -0.1457 0.9454 0.0056
-7.000 -0.1129 0.01236 0.00845 -0.1465 0.9405 0.0060
-6.750 -0.0838 0.01166 0.00760 -0.1470 0.9358 0.0063
-6.500 -0.0547 0.01106 0.00686 -0.1474 0.9303 0.0067
-6.000 0.0034 0.01006 0.00559 -0.1481 0.9196 0.0075
-5.750 0.0325 0.00958 0.00496 -0.1484 0.9139 0.0084
-5.500 0.0616 0.00920 0.00450 -0.1487 0.9082 0.0095
-5.250 0.0905 0.00890 0.00412 -0.1489 0.9018 0.0107
-5.000 0.1194 0.00862 0.00374 -0.1490 0.8957 0.0123
-4.750 0.1479 0.00846 0.00357 -0.1491 0.8867 0.0147
-4.500 0.1761 0.00833 0.00337 -0.1490 0.8735 0.0166
-4.250 0.2036 0.00838 0.00340 -0.1488 0.8565 0.0193
-4.000 0.2314 0.00843 0.00338 -0.1486 0.8408 0.0216
-3.750 0.2597 0.00842 0.00329 -0.1486 0.8285 0.0232
-3.500 0.2879 0.00846 0.00329 -0.1485 0.8171 0.0241
-3.250 0.3160 0.00854 0.00331 -0.1484 0.8048 0.0245
-3.000 0.3454 0.00815 0.00279 -0.1488 0.7913 0.0263
-2.750 0.3740 0.00801 0.00255 -0.1489 0.7745 0.0276
-2.500 0.4024 0.00796 0.00239 -0.1489 0.7544 0.0286
-2.250 0.4308 0.00790 0.00221 -0.1490 0.7337 0.0291
-2.000 0.4594 0.00783 0.00203 -0.1490 0.7153 0.0294
-1.750 0.4879 0.00780 0.00190 -0.1491 0.6974 0.0301
-1.500 0.5162 0.00780 0.00179 -0.1492 0.6759 0.0307
-1.250 0.5444 0.00782 0.00168 -0.1492 0.6517 0.0312
-1.000 0.5726 0.00786 0.00161 -0.1492 0.6287 0.0321
-0.750 0.6006 0.00794 0.00156 -0.1492 0.6046 0.0335
-0.500 0.6285 0.00803 0.00154 -0.1492 0.5790 0.0348
-0.250 0.6563 0.00815 0.00154 -0.1492 0.5512 0.0377
0.000 0.6839 0.00829 0.00156 -0.1492 0.5202 0.0440
0.250 0.7114 0.00845 0.00161 -0.1491 0.4878 0.0545
0.500 0.7392 0.00853 0.00169 -0.1493 0.4596 0.1042
0.750 0.7669 0.00864 0.00177 -0.1493 0.4376 0.1307
1.000 0.7948 0.00873 0.00186 -0.1494 0.4181 0.1667
1.250 0.8225 0.00884 0.00195 -0.1494 0.4009 0.1938
1.500 0.8502 0.00893 0.00205 -0.1495 0.3855 0.2233
1.750 0.8782 0.00896 0.00219 -0.1496 0.3714 0.2921
2.000 0.9063 0.00894 0.00234 -0.1499 0.3585 0.3978
2.250 0.9349 0.00874 0.00255 -0.1503 0.3459 0.6229
2.500 0.9566 0.00819 0.00265 -0.1490 0.3343 1.0000
2.750 0.9840 0.00836 0.00277 -0.1489 0.3225 1.0000
3.000 1.0115 0.00852 0.00288 -0.1489 0.3135 1.0000
3.250 1.0387 0.00869 0.00302 -0.1488 0.3048 1.0000
3.500 1.0661 0.00885 0.00315 -0.1487 0.2967 1.0000
3.750 1.0932 0.00903 0.00329 -0.1486 0.2883 1.0000
4.250 1.1469 0.00942 0.00362 -0.1483 0.2678 1.0000
4.500 1.1735 0.00964 0.00380 -0.1482 0.2570 1.0000
4.750 1.1993 0.00997 0.00403 -0.1479 0.2357 1.0000
5.000 1.2248 0.01032 0.00427 -0.1476 0.2152 1.0000
5.250 1.2505 0.01062 0.00450 -0.1473 0.1984 1.0000
5.500 1.2753 0.01104 0.00479 -0.1468 0.1741 1.0000
5.750 1.2969 0.01187 0.00531 -0.1460 0.1205 1.0000
6.000 1.3174 0.01285 0.00600 -0.1449 0.0688 1.0000
6.250 1.3388 0.01367 0.00662 -0.1439 0.0347 1.0000
6.500 1.3611 0.01436 0.00719 -0.1431 0.0140 1.0000
6.750 1.3851 0.01480 0.00763 -0.1424 0.0102 1.0000
7.000 1.4092 0.01518 0.00804 -0.1419 0.0089 1.0000
7.250 1.4325 0.01565 0.00854 -0.1411 0.0074 1.0000
7.500 1.4558 0.01609 0.00902 -0.1404 0.0064 1.0000
7.750 1.4790 0.01653 0.00949 -0.1397 0.0058 1.0000
8.000 1.5015 0.01702 0.01001 -0.1389 0.0052 1.0000
8.250 1.5227 0.01763 0.01066 -0.1378 0.0046 1.0000
8.500 1.5442 0.01817 0.01126 -0.1368 0.0044 1.0000
8.750 1.5654 0.01871 0.01187 -0.1358 0.0041 1.0000
9.000 1.5860 0.01927 0.01248 -0.1347 0.0038 1.0000
9.250 1.6061 0.01984 0.01309 -0.1335 0.0035 1.0000
9.500 1.6250 0.02048 0.01378 -0.1321 0.0032 1.0000
9.750 1.6409 0.02136 0.01475 -0.1302 0.0029 1.0000
10.000 1.6572 0.02212 0.01558 -0.1284 0.0028 1.0000
10.250 1.6726 0.02286 0.01640 -0.1265 0.0027 1.0000
10.500 1.6861 0.02367 0.01729 -0.1242 0.0026 1.0000
10.750 1.6978 0.02452 0.01823 -0.1217 0.0025 1.0000
11.000 1.7059 0.02542 0.01925 -0.1185 0.0024 1.0000
11.250 1.7129 0.02645 0.02036 -0.1153 0.0023 1.0000
11.500 1.7200 0.02753 0.02154 -0.1123 0.0023 1.0000
11.750 1.7265 0.02872 0.02282 -0.1094 0.0022 1.0000
12.000 1.7323 0.03001 0.02420 -0.1066 0.0021 1.0000
12.250 1.7376 0.03140 0.02569 -0.1040 0.0021 1.0000
12.500 1.7416 0.03296 0.02735 -0.1014 0.0020 1.0000
12.750 1.7446 0.03468 0.02917 -0.0989 0.0019 1.0000
13.000 1.7449 0.03674 0.03134 -0.0965 0.0019 1.0000
13.250 1.7431 0.03911 0.03383 -0.0941 0.0018 1.0000
13.500 1.7377 0.04197 0.03683 -0.0919 0.0018 1.0000
13.750 1.7293 0.04537 0.04037 -0.0900 0.0017 1.0000
14.000 1.7209 0.04896 0.04411 -0.0885 0.0017 1.0000
14.250 1.7167 0.05229 0.04757 -0.0877 0.0017 1.0000
14.500 1.7108 0.05600 0.05142 -0.0871 0.0017 1.0000
14.750 1.7041 0.06001 0.05558 -0.0870 0.0017 1.0000
15.000 1.6946 0.06465 0.06036 -0.0872 0.0016 1.0000
15.250 1.6845 0.06966 0.06552 -0.0880 0.0016 1.0000
15.500 1.6746 0.07485 0.07085 -0.0891 0.0016 1.0000
15.750 1.6599 0.08101 0.07716 -0.0907 0.0016 1.0000
16.000 1.6479 0.08692 0.08321 -0.0925 0.0016 1.0000
16.250 1.6325 0.09361 0.09005 -0.0947 0.0016 1.0000
16.500 1.6173 0.10035 0.09692 -0.0971 0.0015 1.0000
16.750 1.5998 0.10756 0.10428 -0.0998 0.0015 1.0000
17.000 1.5840 0.11459 0.11143 -0.1026 0.0015 1.0000
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Polar data table (+)
Polar graphs
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