BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 100,000 Max Cl/Cd: 23.89 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737a-il-100000.txt Download as CSV file: xf-b737a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 737 ROOT AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0633 0.08145 0.07486 -0.0232 1.0000 0.0963
-15.750 -1.1248 0.06922 0.06225 -0.0312 1.0000 0.0962
-15.500 -1.1362 0.06474 0.05768 -0.0330 1.0000 0.0980
-15.250 -1.1431 0.06103 0.05389 -0.0341 1.0000 0.1004
-15.000 -1.1708 0.05535 0.04791 -0.0363 1.0000 0.1022
-14.750 -1.2028 0.05013 0.04225 -0.0375 1.0000 0.1039
-14.500 -1.1837 0.04906 0.04140 -0.0365 1.0000 0.1085
-14.250 -1.2089 0.04511 0.03703 -0.0360 1.0000 0.1115
-14.000 -1.1937 0.04380 0.03593 -0.0351 1.0000 0.1175
-13.750 -1.1890 0.04211 0.03431 -0.0338 1.0000 0.1235
-13.500 -1.1932 0.04018 0.03226 -0.0317 1.0000 0.1294
-13.250 -1.1867 0.03914 0.03122 -0.0300 1.0000 0.1362
-13.000 -1.1670 0.03929 0.03160 -0.0287 1.0000 0.1431
-12.750 -1.1506 0.03932 0.03169 -0.0273 1.0000 0.1494
-12.500 -1.1444 0.03838 0.03049 -0.0256 1.0000 0.1556
-12.250 -1.1101 0.04033 0.03279 -0.0248 1.0000 0.1620
-12.000 -1.1030 0.03909 0.03126 -0.0232 1.0000 0.1669
-11.750 -1.0675 0.04095 0.03340 -0.0225 1.0000 0.1725
-11.500 -1.0614 0.03927 0.03136 -0.0210 1.0000 0.1766
-11.250 -1.0327 0.03982 0.03207 -0.0203 1.0000 0.1805
-11.000 -1.0073 0.04008 0.03237 -0.0195 1.0000 0.1847
-10.750 -0.9960 0.03864 0.03064 -0.0183 1.0000 0.1884
-10.500 -0.9798 0.03743 0.02924 -0.0172 1.0000 0.1912
-10.250 -0.9520 0.03750 0.02945 -0.0167 1.0000 0.1942
-10.000 -0.9287 0.03707 0.02902 -0.0159 1.0000 0.1973
-9.750 -0.9106 0.03604 0.02783 -0.0150 1.0000 0.2006
-9.500 -0.8955 0.03467 0.02615 -0.0138 1.0000 0.2034
-9.250 -0.8747 0.03357 0.02497 -0.0130 1.0000 0.2058
-9.000 -0.8503 0.03294 0.02441 -0.0124 1.0000 0.2081
-8.750 -0.8274 0.03220 0.02366 -0.0117 1.0000 0.2104
-8.500 -0.8052 0.03140 0.02280 -0.0108 1.0000 0.2130
-8.250 -0.7843 0.03046 0.02173 -0.0099 1.0000 0.2157
-8.000 -0.7642 0.02949 0.02057 -0.0089 1.0000 0.2185
-7.750 -0.7437 0.02851 0.01944 -0.0079 1.0000 0.2210
-7.500 -0.7200 0.02771 0.01876 -0.0072 1.0000 0.2237
-7.250 -0.6975 0.02703 0.01811 -0.0062 1.0000 0.2263
-7.000 -0.6758 0.02627 0.01732 -0.0052 1.0000 0.2288
-6.750 -0.6546 0.02544 0.01643 -0.0042 1.0000 0.2312
-6.500 -0.6340 0.02461 0.01553 -0.0030 1.0000 0.2335
-6.250 -0.6149 0.02387 0.01468 -0.0017 1.0000 0.2362
-6.000 -0.5970 0.02311 0.01390 -0.0003 1.0000 0.2390
-5.750 -0.5801 0.02249 0.01342 0.0012 1.0000 0.2422
-5.500 -0.5640 0.02203 0.01302 0.0028 1.0000 0.2463
-5.250 -0.5473 0.02159 0.01255 0.0042 1.0000 0.2522
-5.000 -0.5293 0.02105 0.01202 0.0052 1.0000 0.2591
-4.750 -0.5106 0.02066 0.01177 0.0062 1.0000 0.2675
-4.500 -0.4824 0.02021 0.01137 0.0054 0.9971 0.2801
-4.250 -0.4157 0.01966 0.01098 -0.0019 0.9804 0.3008
-4.000 -0.3562 0.01919 0.01059 -0.0076 0.9643 0.3193
-3.750 -0.3009 0.01865 0.01021 -0.0123 0.9478 0.3354
-3.500 -0.2533 0.01811 0.00983 -0.0153 0.9313 0.3488
-3.250 -0.2108 0.01770 0.00948 -0.0174 0.9148 0.3632
-3.000 -0.1732 0.01728 0.00920 -0.0183 0.8964 0.3757
-2.750 -0.1404 0.01692 0.00894 -0.0182 0.8764 0.3885
-2.500 -0.1117 0.01667 0.00874 -0.0173 0.8546 0.4027
-2.250 -0.0862 0.01639 0.00860 -0.0158 0.8313 0.4178
-2.000 -0.0624 0.01613 0.00848 -0.0140 0.8065 0.4373
-1.750 -0.0400 0.01583 0.00835 -0.0118 0.7798 0.4655
-1.500 -0.0190 0.01548 0.00826 -0.0092 0.7510 0.5096
-1.250 0.0002 0.01523 0.00835 -0.0061 0.7139 0.5759
-1.000 0.0192 0.01517 0.00840 -0.0026 0.6639 0.6390
-0.750 0.0371 0.01529 0.00832 0.0012 0.5757 0.6838
-0.500 0.0544 0.01587 0.00829 0.0046 0.4662 0.7182
-0.250 0.0740 0.01655 0.00856 0.0072 0.4137 0.7453
0.000 0.0955 0.01712 0.00889 0.0094 0.3854 0.7697
0.250 0.1179 0.01762 0.00921 0.0114 0.3659 0.7913
0.500 0.1409 0.01800 0.00952 0.0133 0.3503 0.8116
0.750 0.1642 0.01843 0.00986 0.0151 0.3383 0.8310
1.000 0.1880 0.01882 0.01016 0.0168 0.3275 0.8499
1.250 0.2126 0.01928 0.01056 0.0183 0.3182 0.8689
1.500 0.2386 0.01966 0.01093 0.0195 0.3090 0.8879
1.750 0.2694 0.02037 0.01147 0.0199 0.3007 0.9058
2.000 0.3065 0.02082 0.01202 0.0190 0.2916 0.9226
2.250 0.3507 0.02155 0.01260 0.0166 0.2825 0.9391
2.500 0.4008 0.02235 0.01344 0.0128 0.2734 0.9540
2.750 0.4515 0.02299 0.01403 0.0086 0.2643 0.9664
3.000 0.4997 0.02395 0.01490 0.0046 0.2568 0.9784
3.250 0.5529 0.02457 0.01567 -0.0005 0.2484 0.9894
3.500 0.6056 0.02535 0.01633 -0.0056 0.2414 1.0000
3.750 0.6228 0.02624 0.01726 -0.0045 0.2374 1.0000
4.000 0.6377 0.02684 0.01807 -0.0030 0.2330 1.0000
4.250 0.6519 0.02749 0.01880 -0.0014 0.2289 1.0000
4.500 0.6650 0.02813 0.01944 0.0004 0.2255 1.0000
4.750 0.6772 0.02890 0.02018 0.0024 0.2226 1.0000
5.000 0.6893 0.03027 0.02150 0.0042 0.2200 1.0000
5.250 0.6999 0.03132 0.02283 0.0064 0.2171 1.0000
5.500 0.7153 0.03266 0.02438 0.0077 0.2137 1.0000
5.750 0.7337 0.03400 0.02583 0.0085 0.2105 1.0000
6.000 0.7545 0.03523 0.02710 0.0091 0.2076 1.0000
6.250 0.7772 0.03648 0.02831 0.0095 0.2053 1.0000
6.500 0.7982 0.03833 0.03013 0.0099 0.2033 1.0000
6.750 0.8117 0.04091 0.03295 0.0106 0.2018 1.0000
7.000 0.8197 0.04383 0.03624 0.0115 0.2006 1.0000
7.250 0.8232 0.04735 0.04012 0.0122 0.1995 1.0000
7.500 0.8194 0.05170 0.04481 0.0127 0.1986 1.0000
7.750 0.8019 0.05762 0.05107 0.0125 0.1989 1.0000
8.000 0.7823 0.06410 0.05775 0.0114 0.2004 1.0000
8.250 0.7782 0.06929 0.06301 0.0104 0.2017 1.0000
8.500 0.7860 0.07355 0.06728 0.0099 0.2024 1.0000
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