AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.47 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-aquilasm-il-1000000-n5.txt Download as CSV file: xf-aquilasm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3397 0.10476 0.10312 -0.0229 1.0000 0.0081
-9.500 -0.3367 0.10111 0.09949 -0.0243 1.0000 0.0081
-9.250 -0.3321 0.09802 0.09641 -0.0253 1.0000 0.0081
-8.750 -0.3125 0.09074 0.08914 -0.0306 0.9683 0.0078
-8.500 -0.2779 0.08274 0.08108 -0.0446 0.9477 0.0082
-8.250 -0.2428 0.07827 0.07647 -0.0534 0.9146 0.0076
-8.000 -0.2380 0.07504 0.07306 -0.0555 0.8696 0.0077
-7.750 -0.2408 0.07239 0.07030 -0.0557 0.8379 0.0076
-7.500 -0.2467 0.06958 0.06742 -0.0563 0.8136 0.0078
-7.250 -0.2458 0.06555 0.06331 -0.0595 0.7944 0.0079
-7.000 -0.2399 0.06193 0.05962 -0.0622 0.7793 0.0079
-6.500 -0.2214 0.05441 0.05190 -0.0671 0.7513 0.0078
-6.250 -0.2094 0.04942 0.04678 -0.0699 0.7394 0.0079
-6.000 -0.1947 0.04586 0.04309 -0.0714 0.7277 0.0078
-5.750 -0.1786 0.04202 0.03909 -0.0725 0.7170 0.0077
-5.500 -0.1618 0.03758 0.03443 -0.0734 0.7069 0.0076
-5.250 -0.1438 0.03304 0.02964 -0.0736 0.6968 0.0077
-5.000 -0.1268 0.02656 0.02273 -0.0727 0.6887 0.0081
-4.750 -0.1182 0.01567 0.01077 -0.0699 0.6822 0.0083
-4.500 -0.0955 0.01344 0.00810 -0.0690 0.6724 0.0084
-4.250 -0.0703 0.01252 0.00697 -0.0685 0.6628 0.0087
-4.000 -0.0443 0.01188 0.00618 -0.0681 0.6525 0.0088
-3.750 -0.0185 0.01110 0.00521 -0.0677 0.6430 0.0089
-3.500 0.0075 0.01052 0.00447 -0.0672 0.6329 0.0089
-3.250 0.0337 0.01005 0.00389 -0.0668 0.6227 0.0090
-3.000 0.0602 0.00967 0.00341 -0.0665 0.6132 0.0091
-2.750 0.0866 0.00936 0.00301 -0.0661 0.6034 0.0093
-2.500 0.1133 0.00910 0.00267 -0.0658 0.5933 0.0095
-2.250 0.1401 0.00888 0.00239 -0.0655 0.5833 0.0098
-2.000 0.1669 0.00870 0.00213 -0.0652 0.5738 0.0103
-1.750 0.1939 0.00855 0.00192 -0.0649 0.5636 0.0107
-1.500 0.2210 0.00842 0.00173 -0.0647 0.5540 0.0113
-1.250 0.2480 0.00830 0.00158 -0.0645 0.5445 0.0124
-1.000 0.2752 0.00824 0.00147 -0.0643 0.5342 0.0138
-0.750 0.3024 0.00817 0.00137 -0.0641 0.5248 0.0155
-0.500 0.3296 0.00813 0.00130 -0.0639 0.5150 0.0181
-0.250 0.3568 0.00810 0.00125 -0.0637 0.5049 0.0218
0.000 0.3842 0.00809 0.00121 -0.0636 0.4951 0.0254
0.250 0.4113 0.00806 0.00117 -0.0634 0.4854 0.0319
0.500 0.4384 0.00805 0.00115 -0.0632 0.4753 0.0422
1.000 0.4922 0.00794 0.00115 -0.0629 0.4555 0.1186
1.250 0.5082 0.00650 0.00124 -0.0612 0.4464 0.7123
1.500 0.5627 0.00599 0.00135 -0.0668 0.4332 0.9861
1.750 0.6094 0.00611 0.00137 -0.0711 0.4210 1.0000
2.000 0.6345 0.00622 0.00141 -0.0705 0.4109 1.0000
2.250 0.6594 0.00634 0.00146 -0.0699 0.4000 1.0000
2.500 0.6846 0.00646 0.00152 -0.0694 0.3900 1.0000
2.750 0.7097 0.00658 0.00159 -0.0688 0.3796 1.0000
3.000 0.7348 0.00672 0.00167 -0.0683 0.3690 1.0000
3.500 0.7850 0.00701 0.00184 -0.0672 0.3476 1.0000
3.750 0.8102 0.00715 0.00195 -0.0667 0.3381 1.0000
4.000 0.8352 0.00731 0.00205 -0.0662 0.3284 1.0000
4.250 0.8603 0.00747 0.00217 -0.0657 0.3177 1.0000
4.500 0.8855 0.00763 0.00230 -0.0652 0.3085 1.0000
4.750 0.9105 0.00780 0.00243 -0.0647 0.2990 1.0000
5.000 0.9354 0.00799 0.00258 -0.0642 0.2887 1.0000
5.250 0.9606 0.00816 0.00272 -0.0638 0.2797 1.0000
5.500 0.9855 0.00835 0.00289 -0.0633 0.2706 1.0000
5.750 1.0104 0.00854 0.00306 -0.0628 0.2613 1.0000
6.000 1.0354 0.00874 0.00323 -0.0624 0.2523 1.0000
6.250 1.0600 0.00897 0.00343 -0.0619 0.2428 1.0000
6.500 1.0840 0.00924 0.00365 -0.0613 0.2280 1.0000
6.750 1.1071 0.00960 0.00391 -0.0607 0.2075 1.0000
7.000 1.1300 0.00996 0.00419 -0.0600 0.1901 1.0000
7.250 1.1536 0.01027 0.00445 -0.0594 0.1772 1.0000
7.500 1.1762 0.01065 0.00476 -0.0587 0.1614 1.0000
7.750 1.1987 0.01104 0.00509 -0.0579 0.1455 1.0000
8.000 1.2199 0.01152 0.00547 -0.0570 0.1259 1.0000
8.250 1.2388 0.01218 0.00598 -0.0558 0.0995 1.0000
8.500 1.2571 0.01287 0.00653 -0.0545 0.0756 1.0000
8.750 1.2762 0.01346 0.00705 -0.0533 0.0596 1.0000
9.000 1.2949 0.01406 0.00758 -0.0521 0.0459 1.0000
9.250 1.3136 0.01464 0.00811 -0.0508 0.0359 1.0000
9.500 1.3325 0.01516 0.00862 -0.0497 0.0293 1.0000
9.750 1.3505 0.01573 0.00916 -0.0483 0.0232 1.0000
10.000 1.3670 0.01635 0.00976 -0.0468 0.0169 1.0000
10.250 1.3814 0.01706 0.01045 -0.0450 0.0104 1.0000
10.500 1.3939 0.01778 0.01117 -0.0428 0.0066 1.0000
10.750 1.4064 0.01834 0.01177 -0.0405 0.0059 1.0000
11.000 1.4179 0.01895 0.01242 -0.0382 0.0054 1.0000
11.250 1.4279 0.01966 0.01319 -0.0358 0.0048 1.0000
11.500 1.4384 0.02039 0.01397 -0.0336 0.0046 1.0000
11.750 1.4490 0.02115 0.01480 -0.0317 0.0045 1.0000
12.000 1.4582 0.02204 0.01577 -0.0297 0.0042 1.0000
12.250 1.4673 0.02300 0.01680 -0.0279 0.0041 1.0000
12.500 1.4756 0.02407 0.01795 -0.0263 0.0040 1.0000
12.750 1.4824 0.02533 0.01928 -0.0247 0.0038 1.0000
13.000 1.4882 0.02674 0.02078 -0.0232 0.0037 1.0000
13.250 1.4935 0.02829 0.02240 -0.0219 0.0035 1.0000
13.500 1.4985 0.02996 0.02415 -0.0209 0.0035 1.0000
13.750 1.5003 0.03201 0.02629 -0.0199 0.0033 1.0000
14.000 1.5001 0.03437 0.02875 -0.0191 0.0032 1.0000
14.250 1.4999 0.03684 0.03132 -0.0186 0.0031 1.0000
14.500 1.4985 0.03955 0.03413 -0.0182 0.0030 1.0000
14.750 1.4955 0.04255 0.03725 -0.0181 0.0030 1.0000
15.000 1.4966 0.04518 0.03996 -0.0181 0.0029 1.0000
15.250 1.4928 0.04845 0.04335 -0.0184 0.0029 1.0000
15.500 1.4935 0.05128 0.04627 -0.0187 0.0028 1.0000
15.750 1.4860 0.05525 0.05035 -0.0194 0.0028 1.0000
16.000 1.4806 0.05910 0.05430 -0.0202 0.0027 1.0000
16.250 1.4740 0.06322 0.05854 -0.0212 0.0027 1.0000
16.500 1.4647 0.06786 0.06329 -0.0225 0.0027 1.0000
16.750 1.4573 0.07235 0.06788 -0.0239 0.0027 1.0000
17.000 1.4473 0.07738 0.07303 -0.0256 0.0026 1.0000
17.250 1.4350 0.08289 0.07866 -0.0275 0.0027 1.0000
17.500 1.4255 0.08808 0.08395 -0.0295 0.0026 1.0000
17.750 1.4139 0.09375 0.08974 -0.0317 0.0026 1.0000
18.000 1.4009 0.09978 0.09588 -0.0343 0.0026 1.0000
18.250 1.3869 0.10614 0.10236 -0.0370 0.0025 1.0000
18.500 1.3760 0.11205 0.10838 -0.0397 0.0025 1.0000
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Polar data table (+)
Polar graphs
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