AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 100,000 Max Cl/Cd: 51.58 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-aquilasm-il-100000.txt Download as CSV file: xf-aquilasm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AQUILA 9.3% smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3067 0.09390 0.08925 -0.0297 1.0000 0.0641
-7.750 -0.3088 0.09161 0.08705 -0.0308 1.0000 0.0658
-7.500 -0.3169 0.08988 0.08544 -0.0316 1.0000 0.0669
-7.250 -0.3271 0.08834 0.08403 -0.0340 1.0000 0.0678
-7.000 -0.3360 0.08692 0.08269 -0.0364 1.0000 0.0683
-6.750 -0.3487 0.08596 0.08175 -0.0368 1.0000 0.0686
-6.500 -0.3600 0.08497 0.08075 -0.0357 1.0000 0.0687
-6.250 -0.3675 0.08150 0.07738 -0.0333 1.0000 0.0693
-6.000 -0.3709 0.07780 0.07385 -0.0282 1.0000 0.0704
-5.750 -0.3763 0.07570 0.07182 -0.0248 1.0000 0.0715
-5.500 -0.3611 0.07245 0.06859 -0.0265 0.9961 0.0743
-5.250 -0.3018 0.06884 0.06430 -0.0452 0.9838 0.0837
-5.000 -0.2866 0.06246 0.05828 -0.0439 0.9776 0.0870
-4.750 -0.2413 0.05877 0.05411 -0.0539 0.9675 0.0992
-4.500 -0.2155 0.05425 0.04978 -0.0552 0.9601 0.1042
-4.250 -0.1790 0.05044 0.04571 -0.0609 0.9504 0.1165
-4.000 -0.1401 0.04683 0.04192 -0.0657 0.9431 0.1317
-3.750 -0.1096 0.04385 0.03883 -0.0683 0.9330 0.1485
-3.500 -0.0679 0.04071 0.03553 -0.0730 0.9274 0.1777
-3.250 -0.0406 0.03836 0.03316 -0.0742 0.9167 0.2106
-2.750 0.0127 0.03418 0.02911 -0.0746 0.8996 0.3399
-2.500 0.0311 0.03223 0.02733 -0.0720 0.8888 0.4003
-2.250 0.1006 0.02875 0.02279 -0.0814 0.8826 0.3069
-2.000 0.1669 0.02517 0.01703 -0.0818 0.8726 0.0875
-1.750 0.2014 0.02387 0.01533 -0.0816 0.8631 0.0813
-1.500 0.2358 0.02269 0.01384 -0.0817 0.8540 0.0829
-1.250 0.2635 0.02146 0.01248 -0.0809 0.8423 0.0847
-1.000 0.2915 0.02027 0.01130 -0.0802 0.8313 0.0878
-0.750 0.3210 0.01947 0.01043 -0.0795 0.8218 0.0975
-0.500 0.3451 0.01862 0.00967 -0.0782 0.8103 0.1084
-0.250 0.4142 0.01486 0.00842 -0.0851 0.8011 1.0000
0.000 0.4388 0.01496 0.00807 -0.0837 0.7895 1.0000
0.250 0.4641 0.01501 0.00783 -0.0825 0.7788 1.0000
0.500 0.4869 0.01517 0.00780 -0.0812 0.7658 1.0000
0.750 0.5099 0.01535 0.00780 -0.0800 0.7531 1.0000
1.000 0.5334 0.01552 0.00781 -0.0788 0.7408 1.0000
1.250 0.5576 0.01567 0.00782 -0.0777 0.7290 1.0000
1.500 0.5826 0.01578 0.00778 -0.0767 0.7178 1.0000
1.750 0.6073 0.01592 0.00779 -0.0757 0.7061 1.0000
2.000 0.6310 0.01613 0.00790 -0.0747 0.6933 1.0000
2.250 0.6550 0.01633 0.00802 -0.0737 0.6808 1.0000
2.500 0.6794 0.01653 0.00814 -0.0728 0.6685 1.0000
2.750 0.7043 0.01671 0.00824 -0.0720 0.6568 1.0000
3.000 0.7300 0.01685 0.00827 -0.0711 0.6453 1.0000
3.250 0.7546 0.01705 0.00841 -0.0703 0.6328 1.0000
3.500 0.7786 0.01729 0.00864 -0.0694 0.6197 1.0000
3.750 0.8029 0.01754 0.00886 -0.0686 0.6068 1.0000
4.000 0.8273 0.01779 0.00907 -0.0677 0.5940 1.0000
4.250 0.8519 0.01803 0.00928 -0.0669 0.5813 1.0000
4.500 0.8768 0.01828 0.00952 -0.0662 0.5688 1.0000
4.750 0.9020 0.01851 0.00970 -0.0655 0.5564 1.0000
5.000 0.9273 0.01875 0.00989 -0.0648 0.5440 1.0000
5.250 0.9510 0.01907 0.01023 -0.0639 0.5305 1.0000
5.500 0.9748 0.01941 0.01062 -0.0631 0.5171 1.0000
5.750 0.9985 0.01976 0.01100 -0.0623 0.5037 1.0000
6.000 1.0222 0.02012 0.01139 -0.0615 0.4905 1.0000
6.250 1.0459 0.02051 0.01180 -0.0607 0.4775 1.0000
6.500 1.0696 0.02091 0.01226 -0.0600 0.4646 1.0000
6.750 1.0935 0.02132 0.01270 -0.0592 0.4521 1.0000
7.000 1.1175 0.02172 0.01311 -0.0585 0.4395 1.0000
7.250 1.1420 0.02214 0.01351 -0.0578 0.4272 1.0000
7.500 1.1642 0.02262 0.01411 -0.0569 0.4140 1.0000
7.750 1.1860 0.02314 0.01474 -0.0559 0.4009 1.0000
8.000 1.2076 0.02366 0.01536 -0.0550 0.3877 1.0000
8.250 1.2290 0.02418 0.01596 -0.0539 0.3743 1.0000
8.500 1.2500 0.02464 0.01652 -0.0528 0.3602 1.0000
8.750 1.2701 0.02503 0.01697 -0.0516 0.3451 1.0000
9.000 1.2895 0.02542 0.01741 -0.0502 0.3297 1.0000
9.250 1.3081 0.02586 0.01790 -0.0488 0.3143 1.0000
9.500 1.3257 0.02633 0.01845 -0.0473 0.2988 1.0000
9.750 1.3413 0.02689 0.01910 -0.0456 0.2830 1.0000
10.000 1.3531 0.02749 0.01988 -0.0434 0.2660 1.0000
10.250 1.3632 0.02813 0.02065 -0.0410 0.2481 1.0000
10.500 1.3702 0.02879 0.02136 -0.0382 0.2291 1.0000
10.750 1.3716 0.02970 0.02237 -0.0348 0.2085 1.0000
11.000 1.3668 0.03077 0.02346 -0.0308 0.1881 1.0000
11.250 1.3580 0.03225 0.02494 -0.0268 0.1672 1.0000
11.500 1.3478 0.03422 0.02682 -0.0235 0.1476 1.0000
11.750 1.3372 0.03666 0.02920 -0.0209 0.1291 1.0000
12.000 1.3275 0.03943 0.03193 -0.0191 0.1134 1.0000
12.250 1.3178 0.04251 0.03498 -0.0177 0.1003 1.0000
12.500 1.3085 0.04583 0.03827 -0.0167 0.0893 1.0000
12.750 1.3000 0.04927 0.04166 -0.0159 0.0801 1.0000
13.000 1.2919 0.05282 0.04514 -0.0153 0.0715 1.0000
13.250 1.2878 0.05624 0.04870 -0.0148 0.0643 1.0000
13.500 1.2883 0.05932 0.05171 -0.0137 0.0579 1.0000
13.750 1.2874 0.06261 0.05514 -0.0134 0.0531 1.0000
14.000 1.2943 0.06538 0.05783 -0.0123 0.0483 1.0000
14.250 1.2921 0.06897 0.06169 -0.0123 0.0460 1.0000
14.500 1.2918 0.07256 0.06552 -0.0123 0.0440 1.0000
14.750 1.2924 0.07613 0.06925 -0.0123 0.0422 1.0000
15.000 1.2957 0.07967 0.07290 -0.0122 0.0408 1.0000
15.250 1.2993 0.08398 0.07734 -0.0119 0.0397 1.0000
15.500 1.2898 0.08950 0.08310 -0.0129 0.0393 1.0000
15.750 1.2725 0.09540 0.08924 -0.0152 0.0392 1.0000
16.000 1.2570 0.10139 0.09546 -0.0177 0.0393 1.0000
16.250 1.2379 0.10813 0.10244 -0.0210 0.0393 1.0000
16.500 1.2184 0.11499 0.10956 -0.0253 0.0396 1.0000
16.750 1.1930 0.12350 0.11832 -0.0311 0.0400 1.0000
17.000 1.1027 0.14954 0.14484 -0.0506 0.0452 1.0000
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Polar data table (+)
Polar graphs
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