AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 500,000 Max Cl/Cd: 99.57 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-aquilasm-il-500000-n5.txt Download as CSV file: xf-aquilasm-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2432 0.09247 0.09038 -0.0291 1.0000 0.0118
-9.250 -0.2402 0.08915 0.08707 -0.0299 1.0000 0.0118
-9.000 -0.2372 0.08596 0.08390 -0.0305 1.0000 0.0121
-8.750 -0.2263 0.08164 0.07957 -0.0338 0.9745 0.0125
-8.500 -0.2114 0.07666 0.07457 -0.0386 0.9539 0.0133
-8.250 -0.1976 0.07158 0.06944 -0.0435 0.9318 0.0139
-8.000 -0.1931 0.06690 0.06469 -0.0479 0.9042 0.0145
-7.750 -0.1935 0.06320 0.06091 -0.0498 0.8778 0.0145
-7.500 -0.1966 0.05984 0.05748 -0.0514 0.8555 0.0146
-7.250 -0.2023 0.05665 0.05423 -0.0526 0.8353 0.0147
-7.000 -0.2023 0.05292 0.05044 -0.0552 0.8198 0.0147
-6.750 -0.1983 0.04889 0.04632 -0.0578 0.8057 0.0147
-6.500 -0.1917 0.04475 0.04209 -0.0602 0.7932 0.0147
-6.250 -0.1830 0.04056 0.03779 -0.0622 0.7816 0.0147
-6.000 -0.1721 0.03643 0.03353 -0.0640 0.7700 0.0147
-5.750 -0.1594 0.03238 0.02934 -0.0653 0.7593 0.0147
-5.250 -0.1362 0.03656 0.03288 -0.0738 0.7652 0.0110
-5.000 -0.1171 0.03255 0.02858 -0.0737 0.7539 0.0110
-4.750 -0.0970 0.02893 0.02465 -0.0733 0.7427 0.0110
-4.500 -0.0762 0.02525 0.02060 -0.0725 0.7327 0.0111
-4.250 -0.0557 0.02172 0.01665 -0.0716 0.7225 0.0113
-4.000 -0.0318 0.02082 0.01557 -0.0713 0.7114 0.0117
-3.750 -0.0075 0.01944 0.01397 -0.0708 0.7009 0.0120
-3.500 0.0153 0.01556 0.00944 -0.0693 0.6918 0.0117
-3.250 0.0405 0.01389 0.00741 -0.0685 0.6817 0.0117
-3.000 0.0663 0.01290 0.00620 -0.0680 0.6717 0.0118
-2.750 0.0923 0.01222 0.00535 -0.0675 0.6617 0.0120
-2.500 0.1184 0.01165 0.00465 -0.0670 0.6513 0.0123
-2.250 0.1446 0.01117 0.00407 -0.0665 0.6412 0.0127
-2.000 0.1707 0.01077 0.00356 -0.0661 0.6313 0.0134
-1.750 0.1968 0.01044 0.00312 -0.0656 0.6211 0.0141
-1.500 0.2232 0.01015 0.00276 -0.0652 0.6108 0.0149
-1.250 0.2496 0.00992 0.00248 -0.0649 0.6009 0.0162
-1.000 0.2762 0.00981 0.00231 -0.0646 0.5909 0.0182
-0.750 0.3030 0.00965 0.00212 -0.0643 0.5807 0.0210
-0.500 0.3298 0.00956 0.00198 -0.0640 0.5708 0.0242
-0.250 0.3564 0.00946 0.00184 -0.0637 0.5609 0.0288
0.000 0.3834 0.00941 0.00175 -0.0635 0.5505 0.0344
0.250 0.4102 0.00934 0.00166 -0.0632 0.5407 0.0444
0.500 0.4369 0.00927 0.00160 -0.0629 0.5308 0.0645
0.750 0.4550 0.00788 0.00165 -0.0618 0.5214 0.5889
1.250 0.5522 0.00712 0.00171 -0.0705 0.4973 1.0000
1.500 0.5770 0.00724 0.00173 -0.0699 0.4873 1.0000
1.750 0.6021 0.00735 0.00176 -0.0693 0.4766 1.0000
2.000 0.6272 0.00746 0.00180 -0.0687 0.4663 1.0000
2.250 0.6522 0.00758 0.00185 -0.0681 0.4559 1.0000
2.500 0.6771 0.00772 0.00191 -0.0675 0.4452 1.0000
2.750 0.7023 0.00785 0.00198 -0.0670 0.4345 1.0000
3.000 0.7273 0.00799 0.00207 -0.0664 0.4237 1.0000
3.250 0.7523 0.00814 0.00216 -0.0659 0.4130 1.0000
3.750 0.8023 0.00847 0.00239 -0.0648 0.3907 1.0000
4.000 0.8274 0.00863 0.00251 -0.0643 0.3800 1.0000
4.250 0.8523 0.00882 0.00265 -0.0638 0.3692 1.0000
4.500 0.8771 0.00902 0.00280 -0.0633 0.3580 1.0000
4.750 0.9021 0.00920 0.00296 -0.0628 0.3472 1.0000
5.000 0.9270 0.00940 0.00313 -0.0623 0.3367 1.0000
5.250 0.9517 0.00962 0.00332 -0.0618 0.3261 1.0000
5.500 0.9762 0.00986 0.00353 -0.0613 0.3155 1.0000
5.750 1.0010 0.01007 0.00373 -0.0608 0.3052 1.0000
6.000 1.0256 0.01030 0.00395 -0.0603 0.2954 1.0000
6.250 1.0497 0.01056 0.00418 -0.0598 0.2853 1.0000
6.500 1.0740 0.01081 0.00444 -0.0593 0.2751 1.0000
6.750 1.0981 0.01107 0.00470 -0.0587 0.2651 1.0000
7.000 1.1216 0.01137 0.00498 -0.0581 0.2525 1.0000
7.250 1.1441 0.01176 0.00529 -0.0574 0.2341 1.0000
7.500 1.1666 0.01214 0.00563 -0.0567 0.2187 1.0000
7.750 1.1893 0.01249 0.00597 -0.0560 0.2061 1.0000
8.000 1.2114 0.01288 0.00633 -0.0552 0.1923 1.0000
8.250 1.2320 0.01339 0.00676 -0.0543 0.1728 1.0000
8.500 1.2525 0.01389 0.00721 -0.0533 0.1548 1.0000
8.750 1.2712 0.01451 0.00773 -0.0521 0.1346 1.0000
9.000 1.2886 0.01520 0.00832 -0.0508 0.1117 1.0000
9.250 1.3035 0.01606 0.00903 -0.0491 0.0867 1.0000
9.500 1.3178 0.01690 0.00978 -0.0473 0.0665 1.0000
9.750 1.3305 0.01780 0.01059 -0.0453 0.0499 1.0000
10.250 1.3572 0.01921 0.01200 -0.0414 0.0344 1.0000
10.500 1.3673 0.01995 0.01275 -0.0389 0.0285 1.0000
10.750 1.3761 0.02078 0.01359 -0.0364 0.0234 1.0000
11.000 1.3844 0.02168 0.01452 -0.0340 0.0183 1.0000
11.250 1.3898 0.02280 0.01565 -0.0315 0.0131 1.0000
11.500 1.3956 0.02397 0.01686 -0.0293 0.0101 1.0000
11.750 1.4021 0.02518 0.01814 -0.0274 0.0087 1.0000
12.000 1.4072 0.02657 0.01960 -0.0256 0.0076 1.0000
12.250 1.4117 0.02810 0.02121 -0.0241 0.0069 1.0000
12.500 1.4167 0.02969 0.02289 -0.0227 0.0066 1.0000
12.750 1.4209 0.03144 0.02475 -0.0216 0.0063 1.0000
13.000 1.4241 0.03339 0.02683 -0.0207 0.0060 1.0000
13.250 1.4265 0.03551 0.02905 -0.0199 0.0058 1.0000
13.500 1.4282 0.03780 0.03146 -0.0194 0.0056 1.0000
13.750 1.4278 0.04041 0.03417 -0.0190 0.0054 1.0000
14.000 1.4259 0.04330 0.03718 -0.0189 0.0052 1.0000
14.250 1.4242 0.04627 0.04026 -0.0189 0.0052 1.0000
14.500 1.4190 0.04976 0.04386 -0.0192 0.0050 1.0000
14.750 1.4116 0.05366 0.04789 -0.0198 0.0049 1.0000
15.000 1.4047 0.05767 0.05202 -0.0205 0.0048 1.0000
15.250 1.3953 0.06217 0.05665 -0.0216 0.0048 1.0000
15.500 1.3861 0.06682 0.06144 -0.0229 0.0047 1.0000
15.750 1.3757 0.07181 0.06655 -0.0245 0.0047 1.0000
16.000 1.3667 0.07676 0.07162 -0.0261 0.0046 1.0000
16.250 1.3581 0.08175 0.07674 -0.0279 0.0045 1.0000
16.500 1.3482 0.08706 0.08217 -0.0299 0.0046 1.0000
16.750 1.3392 0.09239 0.08763 -0.0320 0.0045 1.0000
17.000 1.3300 0.09783 0.09319 -0.0342 0.0045 1.0000
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Polar data table (+)
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