Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il) Xfoil prediction polar at RE=100,000 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: 100,000 Max Cl/Cd: 33.35 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-atr72sm-il-100000.txt Download as CSV file: xf-atr72sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3407 0.09821 0.09327 -0.0281 1.0000 0.1446
-9.250 -0.3630 0.09479 0.08996 -0.0317 1.0000 0.1511
-9.000 -0.4126 0.08919 0.08454 -0.0380 1.0000 0.1536
-8.750 -0.3520 0.08818 0.08346 -0.0302 1.0000 0.1587
-8.500 -0.3582 0.08526 0.08061 -0.0306 1.0000 0.1644
-8.250 -0.4130 0.08101 0.07654 -0.0344 1.0000 0.1677
-8.000 -0.4766 0.07916 0.07477 -0.0310 1.0000 0.1686
-7.750 -0.5383 0.07835 0.07382 -0.0263 1.0000 0.1693
-7.500 -0.4415 0.07369 0.06948 -0.0257 1.0000 0.1769
-7.250 -0.6118 0.05412 0.04843 -0.0215 1.0000 0.0940
-7.000 -0.6100 0.05109 0.04536 -0.0190 1.0000 0.0932
-6.750 -0.6108 0.04818 0.04229 -0.0161 1.0000 0.0924
-6.500 -0.6108 0.04523 0.03912 -0.0132 1.0000 0.0914
-6.250 -0.6094 0.04221 0.03580 -0.0103 1.0000 0.0903
-6.000 -0.6050 0.03940 0.03265 -0.0076 1.0000 0.0894
-5.750 -0.5761 0.03609 0.02880 -0.0090 0.9940 0.0902
-5.500 -0.5289 0.03337 0.02526 -0.0129 0.9824 0.0943
-5.250 -0.4834 0.03102 0.02290 -0.0168 0.9715 0.0990
-5.000 -0.4403 0.02953 0.02104 -0.0196 0.9604 0.1059
-4.750 -0.3960 0.02786 0.01928 -0.0228 0.9505 0.1130
-4.500 -0.3471 0.02652 0.01771 -0.0263 0.9409 0.1232
-4.250 -0.3059 0.02546 0.01668 -0.0287 0.9289 0.1335
-4.000 -0.2591 0.02418 0.01544 -0.0318 0.9185 0.1453
-3.750 -0.2063 0.02289 0.01420 -0.0359 0.9096 0.1604
-3.500 -0.1655 0.02180 0.01320 -0.0377 0.8967 0.1765
-3.250 -0.1248 0.02066 0.01221 -0.0393 0.8841 0.1989
-3.000 -0.0862 0.01932 0.01114 -0.0404 0.8718 0.2338
-2.750 -0.0603 0.01777 0.01020 -0.0393 0.8564 0.3081
-2.500 -0.0510 0.01592 0.01006 -0.0342 0.8392 0.6297
-2.250 -0.0199 0.01568 0.01017 -0.0314 0.8201 0.7710
-2.000 0.0178 0.01587 0.01034 -0.0300 0.7961 0.8311
-1.750 0.0588 0.01612 0.01037 -0.0292 0.7700 0.8704
-1.500 0.1196 0.01663 0.01055 -0.0321 0.7273 0.8974
-1.250 0.1767 0.01706 0.01052 -0.0352 0.6729 0.9221
-1.000 0.2473 0.01760 0.01043 -0.0415 0.6103 0.9436
-0.750 0.3120 0.01797 0.01023 -0.0478 0.5618 0.9672
-0.500 0.3837 0.01785 0.00964 -0.0562 0.5243 0.9878
-0.250 0.4344 0.01762 0.00913 -0.0612 0.5003 1.0000
0.000 0.4520 0.01770 0.00902 -0.0601 0.4869 1.0000
0.250 0.4699 0.01780 0.00892 -0.0589 0.4751 1.0000
0.500 0.4881 0.01791 0.00892 -0.0577 0.4636 1.0000
0.750 0.5067 0.01809 0.00893 -0.0566 0.4544 1.0000
1.000 0.5256 0.01826 0.00900 -0.0555 0.4454 1.0000
1.250 0.5451 0.01850 0.00908 -0.0544 0.4381 1.0000
1.500 0.5642 0.01872 0.00926 -0.0532 0.4301 1.0000
1.750 0.5847 0.01902 0.00936 -0.0522 0.4237 1.0000
2.000 0.6037 0.01929 0.00966 -0.0510 0.4165 1.0000
2.250 0.6238 0.01961 0.00989 -0.0498 0.4101 1.0000
2.500 0.6450 0.02006 0.01018 -0.0489 0.4051 1.0000
2.750 0.6638 0.02045 0.01064 -0.0476 0.3993 1.0000
3.000 0.6838 0.02086 0.01102 -0.0464 0.3939 1.0000
3.250 0.7057 0.02137 0.01137 -0.0454 0.3891 1.0000
3.500 0.7240 0.02187 0.01195 -0.0440 0.3839 1.0000
3.750 0.7431 0.02237 0.01250 -0.0427 0.3789 1.0000
4.000 0.7637 0.02290 0.01298 -0.0415 0.3746 1.0000
4.250 0.7860 0.02362 0.01356 -0.0407 0.3710 1.0000
4.500 0.8020 0.02424 0.01438 -0.0389 0.3666 1.0000
4.750 0.8201 0.02487 0.01508 -0.0374 0.3620 1.0000
5.000 0.8400 0.02547 0.01565 -0.0361 0.3577 1.0000
5.250 0.8620 0.02621 0.01630 -0.0352 0.3542 1.0000
5.500 0.8767 0.02711 0.01736 -0.0333 0.3507 1.0000
5.750 0.8914 0.02799 0.01840 -0.0314 0.3468 1.0000
6.000 0.9090 0.02877 0.01924 -0.0299 0.3429 1.0000
6.250 0.9295 0.02946 0.01990 -0.0288 0.3393 1.0000
6.500 0.9520 0.03044 0.02077 -0.0281 0.3361 1.0000
6.750 0.9587 0.03163 0.02228 -0.0252 0.3325 1.0000
7.000 0.9691 0.03288 0.02371 -0.0229 0.3290 1.0000
7.250 0.9838 0.03393 0.02485 -0.0212 0.3255 1.0000
7.500 1.0051 0.03469 0.02559 -0.0203 0.3223 1.0000
7.750 1.0296 0.03565 0.02644 -0.0199 0.3192 1.0000
8.000 1.0257 0.03758 0.02872 -0.0161 0.3157 1.0000
8.250 1.0240 0.03966 0.03106 -0.0129 0.3123 1.0000
8.500 1.0282 0.04146 0.03303 -0.0105 0.3091 1.0000
8.750 1.0462 0.04246 0.03404 -0.0094 0.3059 1.0000
9.000 1.0814 0.04276 0.03420 -0.0101 0.3030 1.0000
9.250 1.0659 0.04584 0.03756 -0.0061 0.2999 1.0000
9.500 0.9930 0.05225 0.04440 0.0015 0.2970 1.0000
9.750 0.6981 0.08915 0.08155 -0.0044 0.3013 1.0000
10.000 0.7002 0.09372 0.08615 -0.0053 0.3017 1.0000
10.250 0.5888 0.11313 0.10566 -0.0162 0.3383 1.0000
10.500 1.0529 0.05787 0.05011 0.0053 0.2851 1.0000
10.750 0.5802 0.11896 0.11151 -0.0174 0.3241 1.0000
11.000 0.6067 0.12142 0.11399 -0.0171 0.3210 1.0000
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Polar data table (+)
Polar graphs
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