AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 200,000 Max Cl/Cd: 74.75 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-aquilasm-il-200000.txt Download as CSV file: xf-aquilasm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3164 0.10198 0.09848 -0.0278 1.0000 0.0308
-8.750 -0.3147 0.09949 0.09604 -0.0298 1.0000 0.0312
-8.500 -0.3168 0.09745 0.09407 -0.0328 1.0000 0.0315
-8.250 -0.2430 0.08135 0.07829 -0.0349 1.0000 0.0328
-8.000 -0.2374 0.07799 0.07498 -0.0338 1.0000 0.0334
-7.750 -0.2370 0.07511 0.07215 -0.0332 1.0000 0.0340
-7.500 -0.2421 0.07276 0.06989 -0.0320 1.0000 0.0343
-7.250 -0.2648 0.07252 0.06978 -0.0273 1.0000 0.0344
-7.000 -0.3479 0.08155 0.07859 -0.0345 1.0000 0.0324
-6.750 -0.3454 0.07844 0.07554 -0.0318 0.9982 0.0330
-6.500 -0.3191 0.07404 0.07112 -0.0361 0.9923 0.0339
-6.250 -0.2887 0.06938 0.06641 -0.0429 0.9851 0.0353
-6.000 -0.2568 0.06452 0.06148 -0.0507 0.9763 0.0369
-5.750 -0.2178 0.05925 0.05607 -0.0601 0.9695 0.0395
-5.500 -0.1655 0.05563 0.05190 -0.0712 0.9592 0.0420
-5.250 -0.1435 0.04867 0.04490 -0.0751 0.9506 0.0432
-5.000 -0.1156 0.04501 0.04125 -0.0779 0.9431 0.0448
-4.750 -0.0888 0.04210 0.03824 -0.0799 0.9315 0.0474
-4.500 -0.0580 0.03950 0.03534 -0.0818 0.9194 0.0525
-4.250 -0.0336 0.03606 0.03151 -0.0828 0.9065 0.0567
-4.000 -0.0124 0.03376 0.02919 -0.0827 0.8943 0.0597
-3.750 0.0119 0.03201 0.02716 -0.0823 0.8820 0.0655
-3.500 0.0341 0.02974 0.02448 -0.0815 0.8688 0.0713
-3.250 0.0553 0.02786 0.02255 -0.0809 0.8558 0.0753
-3.000 0.0789 0.02638 0.02066 -0.0799 0.8432 0.0861
-2.750 0.1018 0.02480 0.01901 -0.0793 0.8313 0.0931
-2.500 0.1252 0.02331 0.01731 -0.0785 0.8199 0.1061
-2.000 0.1869 0.01972 0.01242 -0.0747 0.7980 0.0552
-1.750 0.2128 0.01777 0.01029 -0.0739 0.7869 0.0526
-1.500 0.2396 0.01631 0.00859 -0.0730 0.7766 0.0501
-1.250 0.2663 0.01531 0.00740 -0.0721 0.7655 0.0498
-1.000 0.2924 0.01455 0.00653 -0.0712 0.7539 0.0515
-0.750 0.3180 0.01389 0.00578 -0.0704 0.7430 0.0565
-0.500 0.3431 0.01324 0.00513 -0.0696 0.7326 0.0622
-0.250 0.3681 0.01277 0.00461 -0.0687 0.7215 0.0727
0.000 0.3932 0.01237 0.00420 -0.0680 0.7101 0.0924
0.250 0.4585 0.00966 0.00380 -0.0755 0.6987 1.0000
0.500 0.4831 0.00976 0.00371 -0.0747 0.6878 1.0000
0.750 0.5077 0.00987 0.00364 -0.0738 0.6767 1.0000
1.000 0.5321 0.00998 0.00363 -0.0730 0.6650 1.0000
1.250 0.5567 0.01010 0.00363 -0.0723 0.6537 1.0000
1.500 0.5815 0.01023 0.00363 -0.0715 0.6429 1.0000
1.750 0.6064 0.01037 0.00363 -0.0708 0.6321 1.0000
2.000 0.6311 0.01050 0.00369 -0.0701 0.6202 1.0000
2.250 0.6559 0.01064 0.00375 -0.0694 0.6087 1.0000
2.500 0.6808 0.01079 0.00382 -0.0687 0.5976 1.0000
2.750 0.7059 0.01095 0.00388 -0.0681 0.5867 1.0000
3.000 0.7307 0.01110 0.00398 -0.0674 0.5748 1.0000
3.250 0.7555 0.01126 0.00410 -0.0668 0.5628 1.0000
3.500 0.7803 0.01144 0.00424 -0.0662 0.5509 1.0000
3.750 0.8052 0.01162 0.00437 -0.0655 0.5392 1.0000
4.000 0.8301 0.01182 0.00449 -0.0649 0.5276 1.0000
4.250 0.8548 0.01202 0.00465 -0.0643 0.5154 1.0000
4.500 0.8794 0.01221 0.00486 -0.0637 0.5027 1.0000
4.750 0.9039 0.01243 0.00506 -0.0630 0.4900 1.0000
5.000 0.9283 0.01266 0.00527 -0.0624 0.4773 1.0000
5.250 0.9526 0.01291 0.00549 -0.0618 0.4648 1.0000
5.500 0.9768 0.01317 0.00575 -0.0611 0.4522 1.0000
5.750 1.0009 0.01345 0.00600 -0.0605 0.4399 1.0000
6.000 1.0248 0.01375 0.00627 -0.0598 0.4275 1.0000
6.250 1.0484 0.01404 0.00658 -0.0591 0.4144 1.0000
6.500 1.0719 0.01434 0.00693 -0.0584 0.4016 1.0000
6.750 1.0952 0.01467 0.00729 -0.0577 0.3890 1.0000
7.000 1.1183 0.01503 0.00766 -0.0570 0.3767 1.0000
7.250 1.1411 0.01540 0.00804 -0.0562 0.3643 1.0000
7.500 1.1637 0.01580 0.00846 -0.0555 0.3524 1.0000
7.750 1.1856 0.01619 0.00886 -0.0546 0.3396 1.0000
8.000 1.2065 0.01656 0.00926 -0.0536 0.3249 1.0000
8.250 1.2270 0.01694 0.00968 -0.0525 0.3105 1.0000
8.500 1.2474 0.01738 0.01016 -0.0515 0.2972 1.0000
8.750 1.2673 0.01782 0.01066 -0.0504 0.2843 1.0000
9.000 1.2868 0.01827 0.01119 -0.0492 0.2710 1.0000
9.250 1.3054 0.01875 0.01175 -0.0479 0.2575 1.0000
9.500 1.3228 0.01927 0.01235 -0.0465 0.2431 1.0000
9.750 1.3382 0.01984 0.01295 -0.0448 0.2267 1.0000
10.000 1.3526 0.02039 0.01358 -0.0431 0.2059 1.0000
10.250 1.3635 0.02115 0.01430 -0.0409 0.1827 1.0000
10.500 1.3703 0.02208 0.01516 -0.0382 0.1582 1.0000
10.750 1.3738 0.02319 0.01622 -0.0351 0.1337 1.0000
11.000 1.3735 0.02463 0.01755 -0.0319 0.1089 1.0000
11.250 1.3707 0.02639 0.01920 -0.0289 0.0876 1.0000
11.500 1.3655 0.02846 0.02120 -0.0261 0.0725 1.0000
11.750 1.3586 0.03086 0.02356 -0.0237 0.0602 1.0000
12.000 1.3524 0.03345 0.02616 -0.0219 0.0505 1.0000
12.250 1.3444 0.03641 0.02919 -0.0204 0.0426 1.0000
12.500 1.3322 0.04001 0.03284 -0.0193 0.0381 1.0000
12.750 1.3267 0.04316 0.03611 -0.0187 0.0341 1.0000
13.000 1.3141 0.04721 0.04019 -0.0184 0.0314 1.0000
13.250 1.3059 0.05092 0.04399 -0.0182 0.0301 1.0000
13.500 1.3028 0.05419 0.04742 -0.0182 0.0282 1.0000
13.750 1.2991 0.05760 0.05093 -0.0184 0.0264 1.0000
14.000 1.2947 0.06117 0.05457 -0.0187 0.0251 1.0000
14.250 1.2898 0.06478 0.05823 -0.0189 0.0241 1.0000
14.500 1.2877 0.06805 0.06157 -0.0186 0.0230 1.0000
14.750 1.2878 0.07135 0.06504 -0.0190 0.0221 1.0000
15.000 1.2880 0.07466 0.06848 -0.0194 0.0214 1.0000
15.250 1.2887 0.07791 0.07187 -0.0197 0.0208 1.0000
15.500 1.2888 0.08136 0.07546 -0.0201 0.0203 1.0000
15.750 1.2875 0.08510 0.07933 -0.0208 0.0196 1.0000
16.000 1.2864 0.08886 0.08324 -0.0216 0.0194 1.0000
16.250 1.2839 0.09295 0.08745 -0.0227 0.0190 1.0000
16.500 1.2800 0.09737 0.09204 -0.0241 0.0188 1.0000
16.750 1.2747 0.10208 0.09690 -0.0257 0.0185 1.0000
17.000 1.2672 0.10739 0.10240 -0.0279 0.0185 1.0000
17.250 1.2579 0.11314 0.10834 -0.0305 0.0184 1.0000
17.500 1.2459 0.11962 0.11503 -0.0339 0.0184 1.0000
17.750 1.2318 0.12673 0.12236 -0.0378 0.0185 1.0000
18.000 1.2143 0.13495 0.13082 -0.0428 0.0187 1.0000
18.250 1.1942 0.14417 0.14027 -0.0486 0.0189 1.0000
18.500 1.1666 0.15598 0.15233 -0.0563 0.0194 1.0000
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Polar data table (+)
Polar graphs
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