BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 50,000 Max Cl/Cd: 19.42 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737a-il-50000-n5.txt Download as CSV file: xf-b737a-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7059 0.10545 0.09660 0.0039 1.0000 0.1675
-12.500 -0.6884 0.10497 0.09609 0.0049 1.0000 0.1726
-12.250 -0.7164 0.09618 0.08727 -0.0004 1.0000 0.1764
-12.000 -0.7088 0.09375 0.08482 -0.0008 1.0000 0.1797
-11.750 -0.6973 0.09202 0.08308 -0.0007 1.0000 0.1835
-11.500 -0.7410 0.07995 0.07095 -0.0086 1.0000 0.1863
-11.250 -0.8631 0.05980 0.05053 -0.0210 1.0000 0.1849
-11.000 -0.8949 0.05434 0.04481 -0.0210 1.0000 0.1864
-10.750 -0.9107 0.05018 0.04029 -0.0205 1.0000 0.1888
-10.500 -0.9010 0.04848 0.03848 -0.0196 1.0000 0.1917
-10.250 -0.8789 0.04817 0.03822 -0.0187 1.0000 0.1954
-10.000 -0.8686 0.04650 0.03640 -0.0178 1.0000 0.1991
-9.750 -0.8632 0.04414 0.03373 -0.0169 1.0000 0.2026
-9.500 -0.8501 0.04241 0.03182 -0.0160 1.0000 0.2055
-9.250 -0.8285 0.04149 0.03092 -0.0153 1.0000 0.2078
-9.000 -0.8095 0.04022 0.02958 -0.0145 1.0000 0.2099
-8.750 -0.7912 0.03879 0.02802 -0.0137 1.0000 0.2120
-8.500 -0.7728 0.03734 0.02642 -0.0130 1.0000 0.2143
-8.250 -0.7543 0.03590 0.02479 -0.0122 1.0000 0.2169
-8.000 -0.7358 0.03445 0.02311 -0.0114 1.0000 0.2199
-7.750 -0.7133 0.03345 0.02213 -0.0106 1.0000 0.2222
-7.500 -0.6907 0.03256 0.02128 -0.0098 1.0000 0.2249
-7.250 -0.6687 0.03164 0.02035 -0.0090 1.0000 0.2282
-7.000 -0.6473 0.03069 0.01933 -0.0081 1.0000 0.2325
-6.750 -0.6267 0.02970 0.01817 -0.0072 1.0000 0.2377
-6.500 -0.6043 0.02899 0.01762 -0.0063 1.0000 0.2417
-6.250 -0.5832 0.02830 0.01698 -0.0052 1.0000 0.2471
-6.000 -0.5632 0.02761 0.01622 -0.0040 1.0000 0.2540
-5.750 -0.5433 0.02700 0.01571 -0.0028 1.0000 0.2600
-5.500 -0.5245 0.02649 0.01529 -0.0015 1.0000 0.2668
-5.250 -0.5069 0.02602 0.01475 -0.0001 1.0000 0.2748
-5.000 -0.4900 0.02561 0.01448 0.0014 1.0000 0.2814
-4.750 -0.4739 0.02527 0.01419 0.0030 1.0000 0.2892
-4.500 -0.4575 0.02498 0.01387 0.0044 1.0000 0.2973
-4.250 -0.4316 0.02467 0.01370 0.0041 0.9951 0.3059
-4.000 -0.3900 0.02439 0.01342 0.0011 0.9820 0.3187
-3.750 -0.3421 0.02403 0.01322 -0.0029 0.9650 0.3337
-3.500 -0.2889 0.02355 0.01290 -0.0073 0.9395 0.3492
-3.250 -0.2357 0.02299 0.01245 -0.0111 0.9079 0.3661
-2.750 -0.1557 0.02211 0.01178 -0.0136 0.8509 0.3991
-2.500 -0.1262 0.02180 0.01161 -0.0131 0.8262 0.4190
-2.250 -0.0998 0.02153 0.01150 -0.0119 0.8007 0.4440
-2.000 -0.0757 0.02129 0.01147 -0.0101 0.7743 0.4756
-1.750 -0.0539 0.02112 0.01155 -0.0078 0.7460 0.5155
-1.500 -0.0328 0.02105 0.01173 -0.0051 0.7144 0.5609
-1.250 -0.0117 0.02106 0.01183 -0.0023 0.6795 0.6068
-1.000 0.0087 0.02110 0.01187 0.0004 0.6376 0.6486
-0.750 0.0290 0.02118 0.01189 0.0034 0.5859 0.6824
-0.500 0.0488 0.02134 0.01178 0.0062 0.5233 0.7130
-0.250 0.0685 0.02162 0.01172 0.0089 0.4607 0.7389
0.000 0.0889 0.02202 0.01176 0.0112 0.4155 0.7616
0.250 0.1104 0.02244 0.01190 0.0130 0.3847 0.7825
0.500 0.1331 0.02284 0.01210 0.0146 0.3623 0.8025
1.000 0.1846 0.02362 0.01265 0.0166 0.3303 0.8395
1.250 0.2132 0.02404 0.01297 0.0171 0.3181 0.8576
1.500 0.2447 0.02448 0.01336 0.0172 0.3067 0.8786
1.750 0.2810 0.02502 0.01383 0.0164 0.2966 0.9020
2.000 0.3230 0.02560 0.01437 0.0144 0.2858 0.9268
2.250 0.3737 0.02631 0.01498 0.0107 0.2764 0.9488
2.500 0.4271 0.02695 0.01563 0.0060 0.2661 0.9673
2.750 0.4746 0.02763 0.01609 0.0022 0.2586 0.9826
3.000 0.5168 0.02824 0.01687 -0.0010 0.2504 0.9958
3.250 0.5412 0.02876 0.01738 -0.0012 0.2445 1.0000
3.500 0.5575 0.02930 0.01779 0.0003 0.2404 1.0000
3.750 0.5722 0.02994 0.01849 0.0018 0.2360 1.0000
4.000 0.5860 0.03061 0.01927 0.0036 0.2311 1.0000
4.250 0.6013 0.03129 0.01997 0.0051 0.2267 1.0000
4.500 0.6187 0.03198 0.02058 0.0064 0.2229 1.0000
4.750 0.6377 0.03284 0.02134 0.0075 0.2193 1.0000
5.000 0.6545 0.03395 0.02266 0.0086 0.2148 1.0000
5.250 0.6735 0.03504 0.02386 0.0094 0.2106 1.0000
5.500 0.6942 0.03605 0.02486 0.0101 0.2069 1.0000
5.750 0.7166 0.03701 0.02573 0.0106 0.2039 1.0000
6.000 0.7351 0.03846 0.02732 0.0112 0.2007 1.0000
6.250 0.7500 0.04028 0.02942 0.0120 0.1972 1.0000
6.500 0.7662 0.04197 0.03127 0.0126 0.1939 1.0000
6.750 0.7838 0.04348 0.03287 0.0132 0.1910 1.0000
7.000 0.8033 0.04482 0.03422 0.0137 0.1885 1.0000
7.250 0.8249 0.04610 0.03544 0.0140 0.1864 1.0000
7.500 0.8257 0.04936 0.03912 0.0148 0.1840 1.0000
7.750 0.8215 0.05308 0.04320 0.0154 0.1817 1.0000
8.000 0.8120 0.05719 0.04760 0.0157 0.1794 1.0000
8.250 0.7948 0.06192 0.05254 0.0154 0.1774 1.0000
8.500 0.7610 0.06813 0.05893 0.0140 0.1756 1.0000
8.750 0.7225 0.07663 0.06754 0.0092 0.1737 1.0000
9.000 0.7191 0.08119 0.07211 0.0071 0.1722 1.0000
9.250 0.6852 0.09196 0.08293 0.0002 0.1708 1.0000
9.500 0.6479 0.10306 0.09407 -0.0070 0.1696 1.0000
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