BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 50,000 Max Cl/Cd: 26.73 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737b-il-50000-n5.txt Download as CSV file: xf-b737b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 737 MIDSPAN 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6950 0.09454 0.08672 -0.0132 1.0000 0.0587
-11.750 -0.7367 0.08218 0.07424 -0.0226 1.0000 0.0575
-11.500 -0.7763 0.07304 0.06486 -0.0294 1.0000 0.0567
-11.250 -0.8047 0.06707 0.05865 -0.0322 1.0000 0.0563
-11.000 -0.8240 0.06278 0.05411 -0.0322 1.0000 0.0563
-10.750 -0.8337 0.05915 0.05022 -0.0315 1.0000 0.0566
-10.500 -0.8360 0.05587 0.04669 -0.0306 1.0000 0.0573
-10.250 -0.8344 0.05281 0.04333 -0.0296 1.0000 0.0584
-10.000 -0.8301 0.04984 0.04001 -0.0285 1.0000 0.0598
-9.750 -0.8227 0.04698 0.03671 -0.0272 1.0000 0.0612
-9.500 -0.8097 0.04442 0.03386 -0.0262 1.0000 0.0625
-9.250 -0.7916 0.04230 0.03167 -0.0253 1.0000 0.0640
-9.000 -0.7732 0.04033 0.02957 -0.0244 1.0000 0.0658
-8.750 -0.7545 0.03850 0.02753 -0.0234 1.0000 0.0685
-8.500 -0.7345 0.03674 0.02552 -0.0223 1.0000 0.0715
-8.250 -0.7141 0.03517 0.02403 -0.0214 1.0000 0.0745
-8.000 -0.6934 0.03371 0.02248 -0.0203 1.0000 0.0778
-7.750 -0.6729 0.03234 0.02098 -0.0191 1.0000 0.0822
-7.500 -0.6545 0.03102 0.01973 -0.0178 1.0000 0.0873
-7.250 -0.6352 0.02978 0.01840 -0.0165 1.0000 0.0934
-7.000 -0.6179 0.02850 0.01721 -0.0151 1.0000 0.1013
-6.750 -0.6007 0.02723 0.01602 -0.0137 1.0000 0.1127
-6.500 -0.5837 0.02592 0.01484 -0.0122 1.0000 0.1314
-6.250 -0.5684 0.02448 0.01379 -0.0108 1.0000 0.1682
-6.000 -0.5528 0.02327 0.01299 -0.0093 1.0000 0.2320
-5.750 -0.5355 0.02245 0.01237 -0.0078 1.0000 0.2918
-5.500 -0.5178 0.02181 0.01195 -0.0061 1.0000 0.3416
-5.250 -0.5006 0.02132 0.01173 -0.0043 1.0000 0.3929
-5.000 -0.4843 0.02104 0.01175 -0.0020 1.0000 0.4486
-4.750 -0.4664 0.02087 0.01176 0.0003 1.0000 0.4923
-4.500 -0.4461 0.02064 0.01157 0.0019 1.0000 0.5224
-4.250 -0.4257 0.02041 0.01134 0.0035 1.0000 0.5492
-4.000 -0.4058 0.02022 0.01117 0.0051 1.0000 0.5747
-3.750 -0.3865 0.02007 0.01102 0.0068 1.0000 0.6005
-3.500 -0.3677 0.01994 0.01091 0.0084 1.0000 0.6258
-3.250 -0.3496 0.01987 0.01086 0.0102 1.0000 0.6497
-3.000 -0.3278 0.01984 0.01083 0.0111 0.9974 0.6750
-2.750 -0.2858 0.01989 0.01086 0.0085 0.9815 0.7021
-2.500 -0.2450 0.01991 0.01086 0.0063 0.9651 0.7283
-2.250 -0.2033 0.01994 0.01086 0.0040 0.9496 0.7531
-2.000 -0.1626 0.01996 0.01087 0.0021 0.9336 0.7761
-1.750 -0.1231 0.01996 0.01085 0.0004 0.9170 0.7990
-1.500 -0.0839 0.01995 0.01081 -0.0011 0.9001 0.8218
-1.250 -0.0424 0.01996 0.01080 -0.0029 0.8832 0.8426
-1.000 0.0002 0.01995 0.01075 -0.0047 0.8648 0.8634
-0.750 0.0436 0.01992 0.01067 -0.0067 0.8439 0.8838
-0.500 0.0874 0.01987 0.01053 -0.0086 0.8215 0.9032
-0.250 0.1301 0.01982 0.01037 -0.0105 0.7980 0.9210
0.000 0.1712 0.01979 0.01025 -0.0125 0.7729 0.9378
0.250 0.2139 0.01974 0.01008 -0.0148 0.7485 0.9532
0.500 0.2558 0.01969 0.00994 -0.0173 0.7231 0.9688
0.750 0.2974 0.01963 0.00980 -0.0198 0.6967 0.9844
1.000 0.3396 0.01956 0.00963 -0.0226 0.6695 0.9997
1.250 0.3573 0.01959 0.00958 -0.0211 0.6454 1.0000
1.500 0.3751 0.01964 0.00952 -0.0193 0.6218 1.0000
1.750 0.3930 0.01974 0.00953 -0.0176 0.5966 1.0000
2.000 0.4115 0.01986 0.00955 -0.0159 0.5708 1.0000
2.250 0.4305 0.02002 0.00959 -0.0142 0.5440 1.0000
2.500 0.4497 0.02022 0.00967 -0.0126 0.5158 1.0000
2.750 0.4697 0.02046 0.00979 -0.0111 0.4864 1.0000
3.000 0.4900 0.02075 0.00992 -0.0096 0.4581 1.0000
3.250 0.5105 0.02110 0.01012 -0.0083 0.4297 1.0000
3.500 0.5314 0.02151 0.01038 -0.0070 0.4025 1.0000
3.750 0.5526 0.02197 0.01070 -0.0059 0.3782 1.0000
4.000 0.5741 0.02249 0.01106 -0.0048 0.3562 1.0000
4.250 0.5959 0.02306 0.01153 -0.0039 0.3359 1.0000
4.500 0.6179 0.02368 0.01206 -0.0030 0.3180 1.0000
4.750 0.6400 0.02434 0.01262 -0.0021 0.3018 1.0000
5.000 0.6624 0.02504 0.01323 -0.0013 0.2876 1.0000
5.250 0.6850 0.02577 0.01389 -0.0005 0.2743 1.0000
5.500 0.7075 0.02654 0.01471 0.0002 0.2614 1.0000
5.750 0.7303 0.02736 0.01551 0.0009 0.2505 1.0000
6.000 0.7531 0.02817 0.01625 0.0015 0.2407 1.0000
6.250 0.7753 0.02908 0.01730 0.0022 0.2304 1.0000
6.500 0.7984 0.02995 0.01807 0.0028 0.2225 1.0000
6.750 0.8199 0.03098 0.01930 0.0035 0.2134 1.0000
7.000 0.8428 0.03188 0.02011 0.0041 0.2063 1.0000
7.250 0.8631 0.03309 0.02158 0.0048 0.1983 1.0000
7.500 0.8854 0.03404 0.02250 0.0054 0.1919 1.0000
7.750 0.9045 0.03540 0.02411 0.0061 0.1849 1.0000
8.000 0.9247 0.03657 0.02536 0.0068 0.1787 1.0000
8.250 0.9448 0.03783 0.02668 0.0075 0.1732 1.0000
8.500 0.9605 0.03945 0.02859 0.0084 0.1668 1.0000
8.750 0.9806 0.04059 0.02975 0.0090 0.1618 1.0000
9.000 0.9944 0.04245 0.03186 0.0100 0.1566 1.0000
9.250 1.0064 0.04431 0.03398 0.0110 0.1512 1.0000
9.500 1.0256 0.04547 0.03512 0.0116 0.1468 1.0000
9.750 1.0314 0.04793 0.03791 0.0128 0.1424 1.0000
10.000 1.0334 0.05056 0.04086 0.0140 0.1379 1.0000
10.250 1.0450 0.05220 0.04258 0.0149 0.1340 1.0000
10.500 1.0552 0.05405 0.04448 0.0158 0.1305 1.0000
10.750 1.0318 0.05849 0.04934 0.0172 0.1280 1.0000
11.000 1.0006 0.06375 0.05489 0.0174 0.1263 1.0000
11.250 0.9397 0.07412 0.06555 0.0124 0.1261 1.0000
11.500 0.8075 0.10323 0.09474 -0.0072 0.1251 1.0000
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Polar data table (+)
Polar graphs
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