AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 100,000 Max Cl/Cd: 67.08 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah6407-il-100000.txt Download as CSV file: xf-ah6407-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3247 0.10089 0.09617 -0.0241 1.0000 0.0634
-7.250 -0.3351 0.10018 0.09558 -0.0229 1.0000 0.0647
-7.000 -0.3424 0.09991 0.09541 -0.0253 1.0000 0.0657
-6.750 -0.3411 0.09916 0.09472 -0.0310 1.0000 0.0662
-6.500 -0.3401 0.09480 0.09043 -0.0295 1.0000 0.0669
-6.250 -0.3391 0.09058 0.08625 -0.0228 1.0000 0.0685
-6.000 -0.3363 0.08794 0.08365 -0.0209 1.0000 0.0704
-5.750 -0.3325 0.08552 0.08127 -0.0210 1.0000 0.0728
-5.500 -0.3253 0.08301 0.07878 -0.0231 1.0000 0.0761
-5.250 -0.2882 0.07988 0.07556 -0.0411 1.0000 0.0802
-5.000 -0.2937 0.07628 0.07205 -0.0342 1.0000 0.0815
-4.750 -0.2894 0.07362 0.06943 -0.0313 1.0000 0.0840
-4.500 -0.2725 0.07080 0.06660 -0.0340 1.0000 0.0897
-4.250 -0.2416 0.06663 0.06234 -0.0425 1.0000 0.0961
-4.000 -0.2312 0.06425 0.05997 -0.0412 1.0000 0.1017
-3.750 -0.1918 0.06001 0.05561 -0.0507 1.0000 0.1108
-3.500 -0.1641 0.05741 0.05292 -0.0544 1.0000 0.1211
-3.250 -0.1130 0.05430 0.04948 -0.0652 1.0000 0.1373
-3.000 -0.1049 0.05075 0.04610 -0.0627 1.0000 0.1407
-2.750 -0.0568 0.04876 0.04375 -0.0712 1.0000 0.1669
-2.500 -0.0433 0.04560 0.04075 -0.0696 1.0000 0.1711
-2.250 -0.0106 0.04322 0.03826 -0.0730 1.0000 0.1870
-1.750 0.1626 0.02962 0.02251 -0.0999 0.9966 0.1046
-1.500 0.2217 0.02709 0.01930 -0.1060 0.9926 0.1047
-1.250 0.2768 0.02525 0.01691 -0.1112 0.9873 0.1048
-1.000 0.3301 0.02410 0.01548 -0.1162 0.9818 0.1128
-0.750 0.3792 0.02319 0.01439 -0.1202 0.9741 0.1200
-0.500 0.4285 0.02235 0.01356 -0.1243 0.9669 0.1335
-0.250 0.4779 0.02161 0.01302 -0.1284 0.9589 0.1764
0.000 0.5262 0.02039 0.01253 -0.1324 0.9513 0.3884
0.250 0.5672 0.01879 0.01201 -0.1343 0.9430 1.0000
0.500 0.6081 0.01866 0.01164 -0.1364 0.9306 1.0000
0.750 0.6493 0.01844 0.01125 -0.1386 0.9184 1.0000
1.000 0.6924 0.01810 0.01081 -0.1409 0.9071 1.0000
1.250 0.7348 0.01765 0.01028 -0.1429 0.8962 1.0000
1.500 0.7759 0.01713 0.00970 -0.1444 0.8853 1.0000
1.750 0.8104 0.01671 0.00925 -0.1446 0.8710 1.0000
2.000 0.8412 0.01637 0.00891 -0.1441 0.8541 1.0000
2.250 0.8708 0.01604 0.00857 -0.1433 0.8352 1.0000
2.500 0.9015 0.01565 0.00815 -0.1425 0.8156 1.0000
2.750 0.9291 0.01541 0.00789 -0.1413 0.7913 1.0000
3.000 0.9566 0.01521 0.00767 -0.1401 0.7635 1.0000
3.250 0.9833 0.01512 0.00748 -0.1387 0.7306 1.0000
3.500 1.0091 0.01518 0.00740 -0.1373 0.6929 1.0000
3.750 1.0344 0.01542 0.00746 -0.1359 0.6536 1.0000
4.000 1.0588 0.01584 0.00767 -0.1347 0.6140 1.0000
4.250 1.0833 0.01637 0.00799 -0.1336 0.5788 1.0000
4.500 1.1078 0.01698 0.00842 -0.1327 0.5481 1.0000
4.750 1.1328 0.01764 0.00894 -0.1319 0.5233 1.0000
5.000 1.1578 0.01831 0.00956 -0.1313 0.5008 1.0000
5.250 1.1832 0.01901 0.01018 -0.1307 0.4822 1.0000
5.500 1.2090 0.01974 0.01086 -0.1303 0.4659 1.0000
5.750 1.2344 0.02047 0.01162 -0.1298 0.4504 1.0000
6.000 1.2590 0.02115 0.01236 -0.1291 0.4342 1.0000
6.250 1.2835 0.02184 0.01312 -0.1285 0.4191 1.0000
6.500 1.3079 0.02253 0.01389 -0.1278 0.4045 1.0000
6.750 1.3300 0.02307 0.01455 -0.1267 0.3863 1.0000
7.000 1.3497 0.02341 0.01486 -0.1251 0.3625 1.0000
7.250 1.3660 0.02359 0.01507 -0.1231 0.3344 1.0000
7.500 1.3830 0.02387 0.01554 -0.1211 0.3087 1.0000
7.750 1.3996 0.02420 0.01605 -0.1191 0.2808 1.0000
8.000 1.4097 0.02467 0.01652 -0.1160 0.2141 1.0000
8.250 1.3995 0.02863 0.01922 -0.1108 0.0870 1.0000
8.500 1.4033 0.03109 0.02164 -0.1069 0.0701 1.0000
8.750 1.4052 0.03342 0.02394 -0.1032 0.0624 1.0000
9.000 1.4137 0.03514 0.02582 -0.1001 0.0563 1.0000
9.250 1.4181 0.03729 0.02794 -0.0968 0.0524 1.0000
9.500 1.4306 0.03988 0.03055 -0.0944 0.0498 1.0000
9.750 1.4511 0.04223 0.03306 -0.0930 0.0475 1.0000
10.000 1.4703 0.04467 0.03567 -0.0917 0.0449 1.0000
10.250 1.4879 0.04734 0.03843 -0.0906 0.0420 1.0000
10.500 1.5185 0.05271 0.04393 -0.0915 0.0403 1.0000
10.750 1.5307 0.05691 0.04849 -0.0896 0.0401 1.0000
11.000 1.5358 0.06080 0.05278 -0.0870 0.0400 1.0000
11.250 1.5376 0.06531 0.05767 -0.0844 0.0402 1.0000
11.500 1.5333 0.06845 0.06119 -0.0809 0.0404 1.0000
11.750 1.5221 0.07106 0.06412 -0.0766 0.0406 1.0000
12.000 1.5066 0.07397 0.06735 -0.0725 0.0409 1.0000
12.250 1.4886 0.07719 0.07089 -0.0691 0.0412 1.0000
12.500 1.4671 0.08098 0.07502 -0.0665 0.0416 1.0000
12.750 1.4410 0.08566 0.08006 -0.0652 0.0422 1.0000
13.000 1.4048 0.09174 0.08653 -0.0657 0.0429 1.0000
13.250 1.3719 0.09890 0.09400 -0.0682 0.0436 1.0000
13.500 1.3410 0.10692 0.10228 -0.0724 0.0442 1.0000
13.750 1.3096 0.11625 0.11184 -0.0784 0.0447 1.0000
14.000 1.2763 0.12754 0.12332 -0.0867 0.0454 1.0000
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Polar data table (+)
Polar graphs
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