AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.11 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-aquilasm-il-1000000.txt Download as CSV file: xf-aquilasm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3177 0.08673 0.08521 -0.0309 1.0000 0.0107
-8.000 -0.3172 0.08369 0.08220 -0.0318 1.0000 0.0107
-7.750 -0.3192 0.08039 0.07894 -0.0332 0.9918 0.0107
-7.500 -0.2933 0.07461 0.07313 -0.0434 0.9741 0.0107
-7.250 -0.2668 0.06811 0.06659 -0.0531 0.9609 0.0111
-7.000 -0.2323 0.06306 0.06146 -0.0629 0.9383 0.0112
-6.750 -0.2147 0.05957 0.05782 -0.0670 0.9038 0.0115
-6.500 -0.2045 0.05643 0.05453 -0.0689 0.8765 0.0116
-6.250 -0.1933 0.05322 0.05119 -0.0704 0.8549 0.0118
-6.000 -0.1801 0.05000 0.04783 -0.0719 0.8365 0.0121
-5.750 -0.1647 0.04679 0.04448 -0.0731 0.8202 0.0127
-5.500 -0.1471 0.04319 0.04071 -0.0743 0.8055 0.0134
-5.250 -0.1235 0.03906 0.03632 -0.0749 0.7921 0.0141
-4.750 -0.0834 0.03241 0.02922 -0.0746 0.7673 0.0142
-4.500 -0.0699 0.02724 0.02373 -0.0743 0.7561 0.0147
-4.250 -0.0484 0.02574 0.02209 -0.0740 0.7445 0.0150
-4.000 -0.0258 0.02443 0.02062 -0.0737 0.7331 0.0156
-3.750 -0.0019 0.02266 0.01865 -0.0731 0.7219 0.0170
-3.500 0.0264 0.02135 0.01700 -0.0718 0.7112 0.0185
-3.250 0.0385 0.00492 0.00035 -0.0668 0.6865 0.0194
-2.750 0.0944 0.01152 0.00587 -0.0682 0.6822 0.0146
-2.500 0.1206 0.01067 0.00484 -0.0676 0.6720 0.0145
-2.000 0.1725 0.00935 0.00334 -0.0666 0.6512 0.0157
-1.750 0.1991 0.00907 0.00300 -0.0663 0.6414 0.0165
-1.500 0.2256 0.00883 0.00269 -0.0659 0.6311 0.0175
-1.250 0.2524 0.00858 0.00237 -0.0656 0.6208 0.0182
-1.000 0.2786 0.00823 0.00195 -0.0651 0.6110 0.0194
-0.750 0.3054 0.00811 0.00180 -0.0648 0.6011 0.0217
-0.500 0.3327 0.00801 0.00166 -0.0646 0.5911 0.0239
-0.250 0.3595 0.00782 0.00143 -0.0643 0.5816 0.0285
0.000 0.3866 0.00777 0.00132 -0.0641 0.5716 0.0335
0.250 0.4138 0.00771 0.00124 -0.0639 0.5613 0.0420
0.500 0.4406 0.00755 0.00117 -0.0636 0.5516 0.0834
0.750 0.4573 0.00610 0.00123 -0.0621 0.5428 0.6603
1.250 0.5630 0.00551 0.00130 -0.0729 0.5186 1.0000
1.500 0.5880 0.00559 0.00132 -0.0723 0.5084 1.0000
1.750 0.6130 0.00569 0.00134 -0.0716 0.4983 1.0000
2.000 0.6381 0.00578 0.00137 -0.0711 0.4879 1.0000
2.250 0.6634 0.00588 0.00141 -0.0705 0.4773 1.0000
2.500 0.6885 0.00599 0.00147 -0.0699 0.4671 1.0000
3.000 0.7390 0.00622 0.00159 -0.0689 0.4454 1.0000
3.250 0.7643 0.00635 0.00166 -0.0684 0.4342 1.0000
3.500 0.7895 0.00648 0.00175 -0.0678 0.4230 1.0000
3.750 0.8146 0.00663 0.00184 -0.0673 0.4115 1.0000
4.000 0.8398 0.00677 0.00194 -0.0668 0.4004 1.0000
4.250 0.8651 0.00692 0.00204 -0.0663 0.3889 1.0000
4.500 0.8902 0.00708 0.00217 -0.0658 0.3772 1.0000
4.750 0.9152 0.00725 0.00230 -0.0653 0.3656 1.0000
5.000 0.9401 0.00743 0.00243 -0.0648 0.3539 1.0000
5.250 0.9651 0.00761 0.00258 -0.0643 0.3425 1.0000
5.500 0.9902 0.00779 0.00274 -0.0639 0.3312 1.0000
5.750 1.0152 0.00799 0.00290 -0.0634 0.3197 1.0000
6.000 1.0400 0.00820 0.00307 -0.0629 0.3089 1.0000
6.250 1.0645 0.00843 0.00327 -0.0624 0.2974 1.0000
6.500 1.0889 0.00868 0.00347 -0.0619 0.2830 1.0000
6.750 1.1130 0.00895 0.00369 -0.0614 0.2672 1.0000
7.000 1.1371 0.00921 0.00391 -0.0609 0.2548 1.0000
7.250 1.1617 0.00944 0.00414 -0.0604 0.2449 1.0000
7.500 1.1855 0.00973 0.00439 -0.0599 0.2314 1.0000
7.750 1.2088 0.01005 0.00466 -0.0592 0.2169 1.0000
8.000 1.2313 0.01044 0.00497 -0.0585 0.1991 1.0000
8.250 1.2538 0.01082 0.00530 -0.0578 0.1823 1.0000
8.500 1.2759 0.01122 0.00564 -0.0570 0.1661 1.0000
8.750 1.2964 0.01174 0.00606 -0.0561 0.1464 1.0000
9.000 1.3154 0.01236 0.00655 -0.0549 0.1221 1.0000
9.250 1.3331 0.01306 0.00712 -0.0535 0.0980 1.0000
9.500 1.3491 0.01385 0.00777 -0.0519 0.0744 1.0000
9.750 1.3650 0.01462 0.00843 -0.0503 0.0559 1.0000
10.000 1.3809 0.01533 0.00908 -0.0487 0.0433 1.0000
10.250 1.3969 0.01600 0.00971 -0.0471 0.0342 1.0000
10.500 1.4107 0.01676 0.01043 -0.0452 0.0251 1.0000
10.750 1.4206 0.01764 0.01125 -0.0426 0.0156 1.0000
11.000 1.4265 0.01852 0.01212 -0.0393 0.0107 1.0000
11.250 1.4346 0.01932 0.01297 -0.0365 0.0090 1.0000
11.500 1.4445 0.02006 0.01377 -0.0342 0.0084 1.0000
11.750 1.4510 0.02105 0.01482 -0.0317 0.0076 1.0000
12.000 1.4558 0.02222 0.01607 -0.0292 0.0070 1.0000
12.250 1.4621 0.02337 0.01732 -0.0271 0.0067 1.0000
12.500 1.4699 0.02450 0.01853 -0.0254 0.0065 1.0000
12.750 1.4752 0.02590 0.02001 -0.0238 0.0063 1.0000
13.000 1.4792 0.02751 0.02171 -0.0223 0.0060 1.0000
13.250 1.4839 0.02914 0.02343 -0.0211 0.0058 1.0000
13.500 1.4858 0.03114 0.02553 -0.0200 0.0057 1.0000
13.750 1.4843 0.03359 0.02807 -0.0191 0.0054 1.0000
14.000 1.4829 0.03617 0.03075 -0.0185 0.0053 1.0000
14.250 1.4798 0.03905 0.03374 -0.0181 0.0052 1.0000
14.500 1.4743 0.04235 0.03715 -0.0180 0.0051 1.0000
14.750 1.4654 0.04617 0.04111 -0.0181 0.0050 1.0000
15.000 1.4483 0.05116 0.04625 -0.0187 0.0049 1.0000
15.250 1.4418 0.05503 0.05023 -0.0194 0.0049 1.0000
15.500 1.4266 0.06020 0.05554 -0.0205 0.0048 1.0000
15.750 1.4176 0.06477 0.06022 -0.0216 0.0048 1.0000
16.000 1.4113 0.06902 0.06458 -0.0228 0.0048 1.0000
16.250 1.4012 0.07400 0.06966 -0.0244 0.0047 1.0000
16.500 1.3915 0.07903 0.07480 -0.0261 0.0047 1.0000
16.750 1.3834 0.08392 0.07980 -0.0278 0.0047 1.0000
17.000 1.3760 0.08884 0.08482 -0.0296 0.0047 1.0000
17.250 1.3669 0.09413 0.09022 -0.0317 0.0046 1.0000
17.500 1.3570 0.09959 0.09578 -0.0339 0.0046 1.0000
17.750 1.3479 0.10507 0.10136 -0.0362 0.0046 1.0000
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Polar data table (+)
Polar graphs
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