AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 100,000 Max Cl/Cd: 56.44 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-aquilasm-il-100000-n5.txt Download as CSV file: xf-aquilasm-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3192 0.09470 0.09009 -0.0341 1.0000 0.0445
-7.750 -0.3252 0.09257 0.08807 -0.0356 1.0000 0.0447
-7.500 -0.3274 0.09007 0.08563 -0.0379 1.0000 0.0448
-7.250 -0.3297 0.08761 0.08322 -0.0393 1.0000 0.0449
-7.000 -0.3342 0.08541 0.08107 -0.0393 1.0000 0.0450
-6.750 -0.3168 0.08131 0.07686 -0.0450 0.9908 0.0451
-6.500 -0.3031 0.07503 0.07074 -0.0442 0.9847 0.0463
-6.250 -0.2822 0.07091 0.06662 -0.0463 0.9750 0.0475
-6.000 -0.2570 0.06686 0.06253 -0.0506 0.9650 0.0497
-5.750 -0.1643 0.04557 0.04105 -0.0674 0.9208 0.0590
-5.500 -0.1485 0.04092 0.03649 -0.0673 0.9118 0.0608
-5.250 -0.1304 0.03720 0.03269 -0.0686 0.9002 0.0626
-5.000 -0.1127 0.03371 0.02907 -0.0700 0.8874 0.0648
-4.750 -0.0940 0.03035 0.02552 -0.0714 0.8749 0.0672
-4.500 -0.0717 0.02742 0.02219 -0.0730 0.8625 0.0714
-4.000 -0.0319 0.03487 0.02827 -0.0763 0.8711 0.0329
-3.750 -0.0082 0.03234 0.02548 -0.0762 0.8588 0.0321
-3.500 0.0168 0.03000 0.02278 -0.0760 0.8471 0.0314
-3.250 0.0428 0.02785 0.02025 -0.0755 0.8360 0.0309
-3.000 0.0697 0.02595 0.01795 -0.0751 0.8256 0.0309
-2.750 0.0963 0.02452 0.01607 -0.0743 0.8139 0.0328
-2.500 0.1235 0.02339 0.01451 -0.0735 0.8025 0.0339
-2.250 0.1500 0.02176 0.01260 -0.0729 0.7919 0.0344
-2.000 0.1770 0.02039 0.01103 -0.0723 0.7818 0.0354
-1.750 0.2031 0.01940 0.00990 -0.0717 0.7702 0.0367
-1.500 0.2293 0.01865 0.00904 -0.0711 0.7589 0.0397
-1.250 0.2558 0.01804 0.00827 -0.0703 0.7484 0.0442
-1.000 0.2809 0.01717 0.00736 -0.0695 0.7383 0.0473
-0.750 0.3057 0.01671 0.00687 -0.0687 0.7266 0.0548
-0.500 0.3307 0.01622 0.00627 -0.0678 0.7157 0.0618
-0.250 0.3567 0.01586 0.00580 -0.0671 0.7053 0.0770
0.000 0.3832 0.01536 0.00540 -0.0667 0.6947 0.1242
0.500 0.4680 0.01308 0.00501 -0.0720 0.6715 1.0000
0.750 0.4927 0.01320 0.00493 -0.0712 0.6607 1.0000
1.000 0.5175 0.01333 0.00486 -0.0704 0.6499 1.0000
1.250 0.5420 0.01348 0.00487 -0.0697 0.6382 1.0000
1.500 0.5667 0.01363 0.00488 -0.0690 0.6268 1.0000
1.750 0.5915 0.01378 0.00491 -0.0683 0.6158 1.0000
2.000 0.6164 0.01394 0.00493 -0.0675 0.6052 1.0000
2.250 0.6411 0.01412 0.00502 -0.0669 0.5934 1.0000
2.500 0.6658 0.01430 0.00512 -0.0662 0.5818 1.0000
2.750 0.6905 0.01448 0.00523 -0.0655 0.5706 1.0000
3.000 0.7153 0.01468 0.00535 -0.0649 0.5596 1.0000
3.250 0.7400 0.01488 0.00548 -0.0642 0.5481 1.0000
3.500 0.7645 0.01509 0.00566 -0.0636 0.5361 1.0000
3.750 0.7890 0.01532 0.00587 -0.0629 0.5243 1.0000
4.000 0.8135 0.01555 0.00607 -0.0623 0.5129 1.0000
4.250 0.8380 0.01579 0.00626 -0.0616 0.5014 1.0000
4.500 0.8622 0.01604 0.00649 -0.0609 0.4897 1.0000
4.750 0.8863 0.01631 0.00679 -0.0603 0.4773 1.0000
5.000 0.9102 0.01659 0.00708 -0.0596 0.4652 1.0000
5.250 0.9341 0.01689 0.00738 -0.0589 0.4533 1.0000
5.500 0.9577 0.01720 0.00769 -0.0582 0.4415 1.0000
5.750 0.9812 0.01753 0.00804 -0.0575 0.4300 1.0000
6.000 1.0044 0.01787 0.00842 -0.0568 0.4178 1.0000
6.250 1.0275 0.01823 0.00883 -0.0560 0.4056 1.0000
6.500 1.0503 0.01861 0.00925 -0.0553 0.3938 1.0000
6.750 1.0729 0.01901 0.00972 -0.0545 0.3822 1.0000
7.000 1.0952 0.01943 0.01017 -0.0536 0.3710 1.0000
7.250 1.1172 0.01987 0.01067 -0.0528 0.3595 1.0000
7.500 1.1388 0.02034 0.01122 -0.0519 0.3477 1.0000
7.750 1.1601 0.02082 0.01182 -0.0510 0.3362 1.0000
8.000 1.1809 0.02133 0.01240 -0.0500 0.3249 1.0000
8.250 1.2010 0.02186 0.01299 -0.0489 0.3134 1.0000
8.500 1.2203 0.02241 0.01361 -0.0478 0.3013 1.0000
8.750 1.2383 0.02298 0.01429 -0.0465 0.2875 1.0000
9.000 1.2550 0.02359 0.01497 -0.0450 0.2729 1.0000
9.250 1.2706 0.02424 0.01570 -0.0435 0.2576 1.0000
9.500 1.2854 0.02493 0.01649 -0.0418 0.2428 1.0000
9.750 1.2989 0.02568 0.01734 -0.0401 0.2281 1.0000
10.000 1.3110 0.02649 0.01828 -0.0382 0.2136 1.0000
10.250 1.3210 0.02737 0.01927 -0.0361 0.1986 1.0000
10.500 1.3276 0.02834 0.02032 -0.0335 0.1837 1.0000
10.750 1.3320 0.02948 0.02152 -0.0309 0.1678 1.0000
11.000 1.3337 0.03087 0.02294 -0.0284 0.1511 1.0000
11.250 1.3330 0.03256 0.02463 -0.0261 0.1344 1.0000
11.500 1.3307 0.03455 0.02662 -0.0241 0.1162 1.0000
11.750 1.3252 0.03698 0.02903 -0.0224 0.1000 1.0000
12.000 1.3183 0.03976 0.03177 -0.0211 0.0861 1.0000
12.250 1.3109 0.04282 0.03482 -0.0202 0.0743 1.0000
12.500 1.3042 0.04602 0.03807 -0.0198 0.0653 1.0000
12.750 1.2957 0.04962 0.04172 -0.0197 0.0580 1.0000
13.000 1.2864 0.05352 0.04569 -0.0199 0.0524 1.0000
13.250 1.2772 0.05760 0.04988 -0.0205 0.0481 1.0000
13.500 1.2681 0.06186 0.05429 -0.0212 0.0445 1.0000
13.750 1.2555 0.06677 0.05928 -0.0225 0.0416 1.0000
14.000 1.2440 0.07172 0.06435 -0.0239 0.0390 1.0000
14.250 1.2344 0.07662 0.06941 -0.0254 0.0365 1.0000
14.500 1.2232 0.08192 0.07484 -0.0272 0.0345 1.0000
14.750 1.2111 0.08756 0.08058 -0.0293 0.0328 1.0000
15.000 1.1988 0.09333 0.08638 -0.0315 0.0315 1.0000
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Polar data table (+)
Polar graphs
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