AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 50,000 Max Cl/Cd: 25.35 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-aquilasm-il-50000.txt Download as CSV file: xf-aquilasm-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3354 0.10725 0.10070 -0.0256 1.0000 0.1572
-8.250 -0.3239 0.10279 0.09629 -0.0249 1.0000 0.1624
-8.000 -0.3229 0.10048 0.09407 -0.0251 1.0000 0.1703
-7.750 -0.3440 0.10049 0.09429 -0.0267 1.0000 0.1729
-7.500 -0.3200 0.09499 0.08878 -0.0246 1.0000 0.1835
-7.250 -0.3420 0.09474 0.08876 -0.0255 1.0000 0.1876
-7.000 -0.3262 0.09038 0.08444 -0.0228 1.0000 0.1972
-6.750 -0.3492 0.09011 0.08437 -0.0247 1.0000 0.2029
-6.500 -0.3368 0.08616 0.08050 -0.0209 1.0000 0.2139
-6.250 -0.3645 0.08643 0.08093 -0.0229 1.0000 0.2184
-6.000 -0.3573 0.08292 0.07752 -0.0181 1.0000 0.2314
-5.750 -0.3604 0.08049 0.07520 -0.0147 1.0000 0.2410
-5.500 -0.3809 0.07980 0.07461 -0.0150 1.0000 0.2495
-5.250 -0.3899 0.07846 0.07333 -0.0134 1.0000 0.2634
-5.000 -0.3956 0.07657 0.07151 -0.0114 1.0000 0.2787
-4.750 -0.3966 0.07379 0.06882 -0.0068 1.0000 0.2953
-4.500 0.0895 0.04189 0.03573 -0.0337 1.0000 1.0000
-4.250 0.0962 0.04041 0.03436 -0.0338 1.0000 1.0000
-3.750 0.0396 0.04244 0.03683 -0.0181 1.0000 0.9712
-3.500 -0.0118 0.04456 0.03923 -0.0062 1.0000 0.9457
-3.250 -0.0645 0.04664 0.04155 0.0051 1.0000 0.9271
-3.000 -0.1125 0.04791 0.04301 0.0146 1.0000 0.9033
-2.750 -0.1605 0.04893 0.04424 0.0237 1.0000 0.8846
-2.500 -0.2038 0.04948 0.04495 0.0316 1.0000 0.8686
-2.250 -0.2487 0.04964 0.04527 0.0396 1.0000 0.8531
-2.000 -0.2935 0.04931 0.04511 0.0461 0.9967 0.8286
-1.750 -0.3350 0.04849 0.04441 0.0487 0.9792 0.7938
-1.500 -0.0457 0.03815 0.02926 -0.0509 0.9573 0.1555
-1.250 -0.0034 0.03658 0.02719 -0.0534 0.9457 0.1468
-1.000 0.0396 0.03547 0.02558 -0.0557 0.9341 0.1398
-0.750 0.0845 0.03437 0.02411 -0.0584 0.9228 0.1375
-0.500 0.1317 0.03360 0.02297 -0.0613 0.9114 0.1444
-0.250 0.1736 0.03284 0.02208 -0.0633 0.8993 0.1525
0.000 0.2109 0.03236 0.02151 -0.0648 0.8867 0.1719
0.250 0.2476 0.03178 0.02103 -0.0663 0.8742 0.2056
0.500 0.3090 0.02923 0.02028 -0.0708 0.8639 1.0000
0.750 0.3473 0.02983 0.02038 -0.0726 0.8506 1.0000
1.000 0.3891 0.03034 0.02054 -0.0751 0.8377 1.0000
1.250 0.4227 0.03090 0.02087 -0.0762 0.8238 1.0000
1.500 0.4534 0.03150 0.02130 -0.0769 0.8097 1.0000
1.750 0.4833 0.03210 0.02174 -0.0774 0.7956 1.0000
2.000 0.5115 0.03273 0.02225 -0.0775 0.7816 1.0000
2.250 0.5386 0.03337 0.02280 -0.0774 0.7676 1.0000
2.500 0.5655 0.03400 0.02335 -0.0772 0.7536 1.0000
2.750 0.5915 0.03466 0.02395 -0.0769 0.7398 1.0000
3.000 0.6173 0.03532 0.02456 -0.0765 0.7260 1.0000
3.250 0.6427 0.03597 0.02519 -0.0759 0.7123 1.0000
3.500 0.6684 0.03661 0.02582 -0.0754 0.6988 1.0000
3.750 0.6947 0.03719 0.02640 -0.0748 0.6857 1.0000
4.000 0.7244 0.03755 0.02675 -0.0743 0.6730 1.0000
4.250 0.7586 0.03757 0.02682 -0.0740 0.6614 1.0000
4.500 0.7784 0.03846 0.02774 -0.0728 0.6474 1.0000
4.750 0.7968 0.03947 0.02878 -0.0716 0.6334 1.0000
5.000 0.8147 0.04055 0.02990 -0.0703 0.6196 1.0000
5.250 0.8320 0.04169 0.03110 -0.0691 0.6059 1.0000
5.500 0.8479 0.04300 0.03250 -0.0678 0.5924 1.0000
5.750 0.8640 0.04431 0.03388 -0.0665 0.5792 1.0000
6.000 0.8807 0.04562 0.03526 -0.0653 0.5666 1.0000
6.250 0.9064 0.04618 0.03590 -0.0644 0.5549 1.0000
6.500 0.9455 0.04555 0.03543 -0.0637 0.5444 1.0000
6.750 0.9499 0.04792 0.03789 -0.0621 0.5310 1.0000
7.000 0.9499 0.05073 0.04078 -0.0606 0.5177 1.0000
7.250 0.9408 0.05452 0.04462 -0.0591 0.5049 1.0000
7.500 0.9238 0.05903 0.04914 -0.0578 0.4931 1.0000
7.750 0.9515 0.05947 0.04972 -0.0566 0.4826 1.0000
8.000 1.0002 0.05787 0.04840 -0.0556 0.4719 1.0000
8.250 0.9196 0.06922 0.05951 -0.0558 0.4609 1.0000
8.500 0.9132 0.07333 0.06365 -0.0556 0.4513 1.0000
8.750 0.9456 0.07348 0.06403 -0.0543 0.4406 1.0000
9.000 0.9076 0.08101 0.07150 -0.0554 0.4327 1.0000
9.250 0.9126 0.08426 0.07483 -0.0552 0.4239 1.0000
10.500 1.2710 0.05557 0.04805 -0.0383 0.3259 1.0000
10.750 1.2017 0.06504 0.05752 -0.0356 0.3267 1.0000
11.000 1.2037 0.06650 0.05910 -0.0332 0.3114 1.0000
11.250 1.1929 0.06970 0.06239 -0.0316 0.2987 1.0000
11.500 1.1958 0.07102 0.06386 -0.0295 0.2821 1.0000
11.750 1.3522 0.05335 0.04575 -0.0238 0.1956 1.0000
12.000 1.3442 0.05549 0.04791 -0.0205 0.1807 1.0000
12.250 1.3363 0.05778 0.05021 -0.0177 0.1669 1.0000
12.500 1.3291 0.06039 0.05282 -0.0155 0.1543 1.0000
12.750 1.3233 0.06310 0.05551 -0.0138 0.1425 1.0000
13.000 1.3193 0.06588 0.05824 -0.0124 0.1309 1.0000
13.250 1.2953 0.07108 0.06377 -0.0121 0.1293 1.0000
13.500 1.2688 0.07708 0.07004 -0.0130 0.1286 1.0000
13.750 1.2390 0.08430 0.07750 -0.0151 0.1297 1.0000
14.000 1.2082 0.09249 0.08585 -0.0182 0.1313 1.0000
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Polar data table (+)
Polar graphs
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