AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.26 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah6407-il-1000000.txt Download as CSV file: xf-ah6407-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3281 0.10188 0.10028 -0.0270 1.0000 0.0101
-8.500 -0.3308 0.10021 0.09864 -0.0253 1.0000 0.0103
-8.250 -0.3324 0.09841 0.09687 -0.0241 0.9997 0.0105
-8.000 -0.3171 0.09482 0.09327 -0.0278 0.9982 0.0112
-7.750 -0.3002 0.09034 0.08879 -0.0335 0.9958 0.0126
-7.500 -0.2810 0.08567 0.08412 -0.0407 0.9924 0.0127
-7.250 -0.2590 0.08111 0.07956 -0.0472 0.9894 0.0128
-7.000 -0.2335 0.07620 0.07464 -0.0548 0.9871 0.0128
-6.750 -0.2110 0.07035 0.06878 -0.0623 0.9854 0.0133
-6.500 -0.0999 0.01606 0.01291 -0.1370 0.9816 0.0123
-6.250 -0.0668 0.01418 0.01067 -0.1390 0.9787 0.0128
-6.000 -0.0336 0.01245 0.00862 -0.1409 0.9759 0.0141
-5.750 -0.0034 0.01265 0.00887 -0.1413 0.9727 0.0149
-5.500 0.0269 0.01223 0.00833 -0.1418 0.9692 0.0159
-5.250 0.0552 0.01173 0.00770 -0.1419 0.9637 0.0168
-5.000 0.0847 0.01062 0.00638 -0.1424 0.9589 0.0182
-4.750 0.1114 0.01065 0.00641 -0.1420 0.9515 0.0191
-4.250 0.1638 0.01050 0.00613 -0.1407 0.9317 0.0217
-4.000 0.1908 0.01067 0.00626 -0.1402 0.9229 0.0225
-3.750 0.2205 0.00945 0.00486 -0.1408 0.9156 0.0247
-3.500 0.2486 0.00931 0.00468 -0.1407 0.9077 0.0261
-3.000 0.3050 0.00904 0.00428 -0.1405 0.8900 0.0291
-2.750 0.3331 0.00899 0.00416 -0.1403 0.8801 0.0298
-2.500 0.3628 0.00808 0.00310 -0.1408 0.8697 0.0321
-2.250 0.3916 0.00781 0.00278 -0.1409 0.8588 0.0336
-2.000 0.4204 0.00762 0.00254 -0.1409 0.8479 0.0351
-1.750 0.4490 0.00749 0.00235 -0.1410 0.8363 0.0369
-1.500 0.4776 0.00737 0.00216 -0.1410 0.8243 0.0382
-1.250 0.5062 0.00727 0.00199 -0.1410 0.8119 0.0391
-1.000 0.5347 0.00720 0.00185 -0.1410 0.7985 0.0398
-0.750 0.5635 0.00708 0.00164 -0.1411 0.7834 0.0420
-0.500 0.5921 0.00700 0.00150 -0.1411 0.7660 0.0475
-0.250 0.6203 0.00700 0.00142 -0.1411 0.7470 0.0524
0.000 0.6490 0.00684 0.00141 -0.1413 0.7275 0.1316
0.250 0.6773 0.00682 0.00145 -0.1413 0.7058 0.1918
0.500 0.7051 0.00688 0.00149 -0.1413 0.6817 0.2255
1.000 0.7607 0.00698 0.00164 -0.1414 0.6248 0.3458
1.250 0.7892 0.00663 0.00186 -0.1419 0.5904 0.6577
1.500 0.8099 0.00617 0.00189 -0.1403 0.5548 1.0000
1.750 0.8369 0.00646 0.00200 -0.1401 0.5170 1.0000
2.000 0.8639 0.00675 0.00211 -0.1400 0.4827 1.0000
2.250 0.8909 0.00703 0.00223 -0.1398 0.4531 1.0000
2.500 0.9181 0.00728 0.00235 -0.1397 0.4281 1.0000
2.750 0.9452 0.00752 0.00249 -0.1396 0.4067 1.0000
3.000 0.9724 0.00774 0.00262 -0.1395 0.3882 1.0000
3.250 0.9996 0.00795 0.00276 -0.1394 0.3708 1.0000
3.500 1.0267 0.00817 0.00291 -0.1393 0.3546 1.0000
3.750 1.0537 0.00840 0.00307 -0.1391 0.3388 1.0000
4.000 1.0807 0.00862 0.00323 -0.1390 0.3246 1.0000
4.250 1.1076 0.00884 0.00340 -0.1388 0.3111 1.0000
4.500 1.1339 0.00912 0.00358 -0.1386 0.2921 1.0000
4.750 1.1604 0.00939 0.00378 -0.1384 0.2749 1.0000
5.000 1.1868 0.00963 0.00397 -0.1382 0.2611 1.0000
5.250 1.2131 0.00989 0.00418 -0.1380 0.2478 1.0000
5.750 1.2653 0.01044 0.00464 -0.1375 0.2187 1.0000
6.000 1.2909 0.01075 0.00489 -0.1372 0.2006 1.0000
6.250 1.3153 0.01123 0.00522 -0.1367 0.1693 1.0000
6.500 1.3341 0.01246 0.00598 -0.1354 0.0960 1.0000
6.750 1.3517 0.01389 0.00698 -0.1339 0.0305 1.0000
7.000 1.3737 0.01466 0.00765 -0.1329 0.0163 1.0000
7.250 1.3978 0.01511 0.00815 -0.1323 0.0147 1.0000
7.500 1.4207 0.01569 0.00876 -0.1315 0.0129 1.0000
7.750 1.4423 0.01643 0.00961 -0.1303 0.0115 1.0000
8.000 1.4654 0.01691 0.01014 -0.1296 0.0109 1.0000
8.250 1.4877 0.01745 0.01072 -0.1287 0.0101 1.0000
8.500 1.5093 0.01805 0.01136 -0.1277 0.0094 1.0000
8.750 1.5284 0.01890 0.01228 -0.1263 0.0087 1.0000
9.000 1.5413 0.02036 0.01391 -0.1238 0.0081 1.0000
9.250 1.5614 0.02095 0.01457 -0.1226 0.0079 1.0000
9.500 1.5794 0.02171 0.01540 -0.1210 0.0076 1.0000
9.750 1.5956 0.02257 0.01634 -0.1192 0.0073 1.0000
10.000 1.6103 0.02349 0.01734 -0.1171 0.0070 1.0000
10.250 1.6235 0.02440 0.01834 -0.1148 0.0067 1.0000
10.500 1.6356 0.02531 0.01931 -0.1124 0.0065 1.0000
10.750 1.6456 0.02623 0.02030 -0.1096 0.0062 1.0000
11.000 1.6503 0.02734 0.02149 -0.1060 0.0060 1.0000
11.250 1.6469 0.02914 0.02340 -0.1015 0.0058 1.0000
11.500 1.6287 0.03238 0.02684 -0.0955 0.0055 1.0000
11.750 1.6353 0.03374 0.02830 -0.0931 0.0054 1.0000
12.000 1.6412 0.03523 0.02990 -0.0908 0.0053 1.0000
12.250 1.6435 0.03711 0.03190 -0.0884 0.0053 1.0000
12.500 1.6453 0.03915 0.03405 -0.0862 0.0052 1.0000
12.750 1.6449 0.04151 0.03653 -0.0841 0.0051 1.0000
13.000 1.6432 0.04411 0.03927 -0.0822 0.0050 1.0000
13.250 1.6405 0.04696 0.04225 -0.0806 0.0049 1.0000
13.500 1.6361 0.05014 0.04558 -0.0793 0.0048 1.0000
13.750 1.6309 0.05358 0.04916 -0.0783 0.0047 1.0000
14.000 1.6248 0.05729 0.05301 -0.0777 0.0047 1.0000
14.250 1.6167 0.06145 0.05731 -0.0774 0.0046 1.0000
14.500 1.6087 0.06577 0.06178 -0.0776 0.0046 1.0000
14.750 1.5994 0.07054 0.06669 -0.0783 0.0045 1.0000
15.000 1.5887 0.07574 0.07204 -0.0793 0.0045 1.0000
15.250 1.5771 0.08128 0.07773 -0.0807 0.0044 1.0000
15.500 1.5655 0.08707 0.08365 -0.0826 0.0044 1.0000
15.750 1.5528 0.09324 0.08998 -0.0848 0.0044 1.0000
16.000 1.5398 0.09967 0.09654 -0.0874 0.0043 1.0000
16.250 1.5236 0.10675 0.10377 -0.0902 0.0043 1.0000
16.500 1.5089 0.11379 0.11096 -0.0934 0.0043 1.0000
16.750 1.4946 0.12096 0.11827 -0.0969 0.0043 1.0000
17.000 1.4795 0.12840 0.12585 -0.1006 0.0043 1.0000
17.250 1.4639 0.13614 0.13372 -0.1047 0.0043 1.0000
17.500 1.4476 0.14436 0.14209 -0.1093 0.0043 1.0000
17.750 1.4336 0.15232 0.15018 -0.1140 0.0043 1.0000
18.000 1.4138 0.16209 0.16011 -0.1200 0.0043 1.0000
18.250 1.3969 0.17153 0.16969 -0.1260 0.0043 1.0000
18.500 1.3746 0.18320 0.18153 -0.1337 0.0044 1.0000
18.750 1.3452 0.19850 0.19702 -0.1439 0.0046 1.0000
19.000 1.0221 0.17988 0.17847 -0.1041 0.0053 1.0000
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Polar data table (+)
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