AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AQUILA 9.3% smoothed (aquilasm-il) Reynolds number: 200,000 Max Cl/Cd: 75.02 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-aquilasm-il-200000-n5.txt Download as CSV file: xf-aquilasm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3103 0.08945 0.08614 -0.0331 1.0000 0.0251
-7.750 -0.3147 0.08701 0.08376 -0.0338 1.0000 0.0252
-7.500 -0.3211 0.08463 0.08147 -0.0344 1.0000 0.0252
-7.250 -0.3028 0.07982 0.07665 -0.0425 0.9852 0.0254
-7.000 -0.2765 0.07441 0.07116 -0.0515 0.9701 0.0254
-6.750 -0.2504 0.06935 0.06600 -0.0584 0.9553 0.0255
-6.500 -0.2246 0.06458 0.06110 -0.0642 0.9405 0.0255
-6.250 -0.2099 0.05915 0.05566 -0.0668 0.9267 0.0262
-6.000 -0.1893 0.05549 0.05192 -0.0695 0.9113 0.0266
-5.750 -0.1691 0.05214 0.04846 -0.0718 0.8950 0.0270
-5.500 -0.1496 0.04891 0.04509 -0.0735 0.8790 0.0276
-5.250 -0.1301 0.04574 0.04173 -0.0748 0.8636 0.0281
-5.000 -0.1104 0.04270 0.03848 -0.0756 0.8490 0.0288
-4.750 -0.0899 0.03957 0.03510 -0.0761 0.8354 0.0288
-4.250 -0.0445 0.03261 0.02738 -0.0756 0.8109 0.0244
-4.000 -0.0236 0.02995 0.02446 -0.0752 0.7987 0.0229
-3.500 0.0252 0.02338 0.01677 -0.0728 0.7768 0.0193
-3.250 0.0492 0.02146 0.01450 -0.0721 0.7660 0.0192
-3.000 0.0742 0.01978 0.01246 -0.0713 0.7548 0.0192
-2.750 0.0999 0.01831 0.01062 -0.0706 0.7439 0.0193
-2.500 0.1256 0.01695 0.00899 -0.0699 0.7334 0.0197
-2.000 0.1775 0.01532 0.00704 -0.0688 0.7119 0.0213
-1.750 0.2038 0.01485 0.00646 -0.0684 0.7012 0.0236
-1.500 0.2301 0.01433 0.00577 -0.0677 0.6909 0.0254
-1.250 0.2552 0.01357 0.00495 -0.0671 0.6805 0.0270
-1.000 0.2809 0.01314 0.00448 -0.0665 0.6697 0.0293
-0.750 0.3069 0.01289 0.00415 -0.0660 0.6594 0.0336
-0.500 0.3323 0.01251 0.00371 -0.0654 0.6492 0.0389
-0.250 0.3583 0.01229 0.00342 -0.0650 0.6384 0.0470
0.000 0.3844 0.01210 0.00316 -0.0645 0.6279 0.0579
0.250 0.4100 0.01183 0.00297 -0.0640 0.6177 0.0994
0.500 0.4723 0.00948 0.00293 -0.0714 0.6057 1.0000
0.750 0.4970 0.00958 0.00288 -0.0707 0.5947 1.0000
1.000 0.5218 0.00969 0.00285 -0.0700 0.5842 1.0000
1.250 0.5465 0.00981 0.00283 -0.0693 0.5738 1.0000
1.500 0.5713 0.00994 0.00283 -0.0686 0.5631 1.0000
1.750 0.5962 0.01006 0.00286 -0.0679 0.5522 1.0000
2.000 0.6211 0.01020 0.00290 -0.0673 0.5415 1.0000
2.250 0.6459 0.01035 0.00295 -0.0667 0.5310 1.0000
2.500 0.6709 0.01049 0.00302 -0.0661 0.5199 1.0000
2.750 0.6959 0.01065 0.00312 -0.0655 0.5088 1.0000
3.000 0.7208 0.01081 0.00322 -0.0649 0.4980 1.0000
3.250 0.7456 0.01099 0.00332 -0.0643 0.4871 1.0000
3.500 0.7705 0.01117 0.00345 -0.0638 0.4758 1.0000
3.750 0.7953 0.01135 0.00361 -0.0632 0.4642 1.0000
4.000 0.8201 0.01155 0.00377 -0.0626 0.4528 1.0000
4.250 0.8447 0.01176 0.00394 -0.0621 0.4416 1.0000
4.500 0.8691 0.01198 0.00412 -0.0615 0.4302 1.0000
4.750 0.8937 0.01221 0.00434 -0.0609 0.4183 1.0000
5.000 0.9181 0.01244 0.00456 -0.0603 0.4065 1.0000
5.250 0.9423 0.01269 0.00480 -0.0598 0.3951 1.0000
5.500 0.9663 0.01296 0.00505 -0.0591 0.3837 1.0000
5.750 0.9900 0.01325 0.00534 -0.0585 0.3723 1.0000
6.000 1.0138 0.01353 0.00563 -0.0579 0.3608 1.0000
6.250 1.0375 0.01383 0.00594 -0.0573 0.3494 1.0000
6.500 1.0608 0.01414 0.00627 -0.0566 0.3382 1.0000
6.750 1.0838 0.01449 0.00664 -0.0559 0.3275 1.0000
7.000 1.1065 0.01484 0.00701 -0.0551 0.3165 1.0000
7.250 1.1293 0.01519 0.00740 -0.0544 0.3054 1.0000
7.500 1.1516 0.01557 0.00783 -0.0537 0.2946 1.0000
7.750 1.1732 0.01598 0.00826 -0.0528 0.2828 1.0000
8.000 1.1940 0.01642 0.00871 -0.0518 0.2679 1.0000
8.250 1.2141 0.01688 0.00918 -0.0508 0.2520 1.0000
8.500 1.2339 0.01737 0.00971 -0.0497 0.2374 1.0000
8.750 1.2534 0.01788 0.01025 -0.0486 0.2242 1.0000
9.000 1.2722 0.01841 0.01082 -0.0475 0.2113 1.0000
9.250 1.2903 0.01898 0.01143 -0.0462 0.1982 1.0000
9.500 1.3069 0.01961 0.01208 -0.0448 0.1825 1.0000
9.750 1.3203 0.02041 0.01284 -0.0430 0.1623 1.0000
10.000 1.3317 0.02131 0.01368 -0.0410 0.1388 1.0000
10.250 1.3375 0.02239 0.01464 -0.0382 0.1140 1.0000
10.500 1.3396 0.02369 0.01580 -0.0350 0.0900 1.0000
10.750 1.3425 0.02502 0.01706 -0.0323 0.0738 1.0000
11.000 1.3456 0.02642 0.01844 -0.0299 0.0617 1.0000
11.250 1.3492 0.02786 0.01991 -0.0277 0.0523 1.0000
11.500 1.3523 0.02944 0.02155 -0.0259 0.0444 1.0000
11.750 1.3543 0.03120 0.02336 -0.0242 0.0382 1.0000
12.250 1.3554 0.03532 0.02761 -0.0215 0.0268 1.0000
12.500 1.3541 0.03775 0.03011 -0.0206 0.0232 1.0000
12.750 1.3527 0.04032 0.03279 -0.0199 0.0198 1.0000
13.000 1.3480 0.04338 0.03591 -0.0194 0.0176 1.0000
13.250 1.3453 0.04637 0.03907 -0.0192 0.0161 1.0000
13.500 1.3417 0.04958 0.04242 -0.0193 0.0152 1.0000
13.750 1.3359 0.05319 0.04614 -0.0197 0.0142 1.0000
14.000 1.3279 0.05721 0.05028 -0.0203 0.0135 1.0000
14.250 1.3193 0.06147 0.05470 -0.0212 0.0131 1.0000
14.500 1.3116 0.06579 0.05917 -0.0222 0.0127 1.0000
14.750 1.3040 0.07026 0.06379 -0.0235 0.0123 1.0000
15.000 1.2961 0.07495 0.06863 -0.0250 0.0119 1.0000
15.250 1.2879 0.07979 0.07362 -0.0266 0.0116 1.0000
15.500 1.2804 0.08466 0.07863 -0.0284 0.0113 1.0000
15.750 1.2722 0.08979 0.08388 -0.0303 0.0110 1.0000
16.000 1.2645 0.09494 0.08916 -0.0324 0.0105 1.0000
16.250 1.2564 0.10025 0.09459 -0.0346 0.0103 1.0000
16.500 1.2484 0.10564 0.10010 -0.0369 0.0102 1.0000
16.750 1.2405 0.11112 0.10570 -0.0394 0.0099 1.0000
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Polar data table (+)
Polar graphs
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