Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il) Reynolds number: 50,000 Max Cl/Cd: 20.51 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-atr72sm-il-50000.txt Download as CSV file: xf-atr72sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Smoothed ATR airfoil coordinates obtained using
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3010 0.10721 0.10030 -0.0136 1.0000 0.3145
-9.000 -0.3101 0.10529 0.09849 -0.0133 1.0000 0.3278
-8.750 -0.3188 0.10392 0.09721 -0.0125 1.0000 0.3427
-8.500 -0.2994 0.10014 0.09346 -0.0112 1.0000 0.3587
-8.250 -0.2973 0.09778 0.09119 -0.0098 1.0000 0.3765
-8.000 -0.2992 0.09575 0.08926 -0.0081 1.0000 0.3946
-7.750 -0.2997 0.09353 0.08715 -0.0062 1.0000 0.4130
-6.750 -0.2562 0.08178 0.07564 0.0008 1.0000 0.4876
-6.500 -0.5355 0.06232 0.05595 -0.0176 1.0000 0.1819
-6.250 -0.5596 0.05733 0.05038 -0.0152 1.0000 0.1680
-6.000 -0.5574 0.05421 0.04715 -0.0130 1.0000 0.1662
-5.750 -0.5565 0.05121 0.04392 -0.0107 1.0000 0.1653
-5.500 -0.5536 0.04840 0.04082 -0.0085 1.0000 0.1650
-5.250 -0.5480 0.04571 0.03780 -0.0064 1.0000 0.1647
-5.000 -0.5401 0.04323 0.03494 -0.0044 1.0000 0.1654
-4.750 -0.5306 0.04118 0.03241 -0.0023 1.0000 0.1679
-4.500 -0.5178 0.03916 0.03021 -0.0008 1.0000 0.1718
-4.250 -0.5031 0.03766 0.02864 0.0006 1.0000 0.1768
-4.000 -0.4884 0.03635 0.02700 0.0021 1.0000 0.1829
-3.750 -0.4729 0.03494 0.02534 0.0034 1.0000 0.1889
-3.500 -0.4574 0.03395 0.02434 0.0045 1.0000 0.1973
-3.250 -0.4148 0.03280 0.02300 0.0010 0.9894 0.2106
-3.000 -0.3464 0.03173 0.02182 -0.0064 0.9685 0.2348
-2.750 -0.2826 0.03051 0.02077 -0.0127 0.9455 0.2669
-2.500 -0.2082 0.02892 0.01974 -0.0204 0.9241 0.3353
-2.250 -0.1767 0.02655 0.01944 -0.0194 0.9013 0.5759
-2.000 0.2678 0.02637 0.01871 -0.0749 0.8815 1.0000
-1.750 0.3189 0.02503 0.01710 -0.0781 0.8390 1.0000
-1.500 0.3418 0.02432 0.01612 -0.0764 0.7918 1.0000
-1.250 0.3611 0.02379 0.01526 -0.0739 0.7519 1.0000
-1.000 0.3770 0.02363 0.01479 -0.0714 0.7154 1.0000
-0.750 0.3936 0.02362 0.01447 -0.0693 0.6848 1.0000
-0.500 0.4105 0.02378 0.01440 -0.0676 0.6579 1.0000
-0.250 0.4283 0.02397 0.01435 -0.0660 0.6361 1.0000
0.000 0.4463 0.02422 0.01439 -0.0645 0.6176 1.0000
0.250 0.4640 0.02456 0.01455 -0.0631 0.6009 1.0000
0.500 0.4815 0.02497 0.01482 -0.0617 0.5860 1.0000
0.750 0.4994 0.02542 0.01513 -0.0603 0.5730 1.0000
1.000 0.5186 0.02585 0.01537 -0.0589 0.5619 1.0000
1.250 0.5340 0.02657 0.01608 -0.0575 0.5502 1.0000
1.500 0.5526 0.02714 0.01650 -0.0561 0.5408 1.0000
1.750 0.5682 0.02789 0.01723 -0.0546 0.5308 1.0000
2.000 0.5854 0.02862 0.01787 -0.0531 0.5225 1.0000
2.250 0.6002 0.02953 0.01880 -0.0515 0.5141 1.0000
2.500 0.6197 0.03022 0.01934 -0.0502 0.5076 1.0000
2.750 0.6286 0.03157 0.02081 -0.0482 0.4998 1.0000
3.000 0.6481 0.03226 0.02139 -0.0468 0.4932 1.0000
3.250 0.6565 0.03372 0.02294 -0.0447 0.4867 1.0000
3.500 0.6657 0.03517 0.02443 -0.0427 0.4806 1.0000
3.750 0.6861 0.03600 0.02516 -0.0414 0.4757 1.0000
4.000 0.6866 0.03812 0.02741 -0.0388 0.4706 1.0000
4.250 0.6828 0.04047 0.02987 -0.0359 0.4651 1.0000
4.500 0.6973 0.04172 0.03109 -0.0343 0.4601 1.0000
4.750 0.7060 0.04353 0.03289 -0.0324 0.4560 1.0000
5.000 0.6637 0.04875 0.03830 -0.0278 0.4536 1.0000
5.250 0.5986 0.05596 0.04558 -0.0236 0.4534 1.0000
5.500 0.5444 0.06287 0.05245 -0.0214 0.4553 1.0000
5.750 0.5133 0.06860 0.05816 -0.0212 0.4587 1.0000
6.250 0.3225 0.08824 0.07798 -0.0284 0.6219 1.0000
6.500 0.3573 0.09199 0.08170 -0.0302 0.6142 1.0000
6.750 0.3505 0.09273 0.08240 -0.0281 0.6012 1.0000
7.000 0.3816 0.09677 0.08640 -0.0297 0.5956 1.0000
7.250 0.3743 0.09730 0.08691 -0.0278 0.5831 1.0000
7.500 0.3972 0.10089 0.09048 -0.0287 0.5773 1.0000
7.750 0.4007 0.10214 0.09171 -0.0277 0.5642 1.0000
8.000 0.4041 0.10413 0.09367 -0.0270 0.5541 1.0000
8.250 0.4311 0.10744 0.09698 -0.0278 0.5450 1.0000
8.500 0.4254 0.10878 0.09830 -0.0267 0.5350 1.0000
8.750 0.4533 0.11240 0.10193 -0.0277 0.5273 1.0000
9.000 0.4468 0.11358 0.10309 -0.0266 0.5163 1.0000
9.250 0.4830 0.11818 0.10771 -0.0279 0.5090 1.0000
9.500 0.4702 0.11853 0.10804 -0.0266 0.4969 1.0000
9.750 0.5070 0.12370 0.11325 -0.0281 0.4915 1.0000
10.000 0.4896 0.12354 0.11307 -0.0268 0.4799 1.0000
10.250 0.5278 0.12902 0.11858 -0.0281 0.4744 1.0000
10.500 0.5104 0.12865 0.11820 -0.0270 0.4622 1.0000
10.750 0.5380 0.13341 0.12298 -0.0279 0.4567 1.0000
11.000 0.5285 0.13378 0.12336 -0.0274 0.4454 1.0000
11.250 0.5629 0.13923 0.12886 -0.0284 0.4406 1.0000
11.500 0.5442 0.13890 0.12852 -0.0279 0.4300 1.0000
11.750 0.5762 0.14391 0.13357 -0.0287 0.4239 1.0000
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Polar data table (+)
Polar graphs
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