BOEING 737 OUTBOARD AIRFOIL (b737d-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 OUTBOARD AIRFOIL (b737d-il) Reynolds number: 50,000 Max Cl/Cd: 33.65 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737d-il-50000.txt Download as CSV file: xf-b737d-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 737 OUTBOARD 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3752 0.10516 0.09887 -0.0096 1.0000 0.2916
-9.250 -0.3755 0.10247 0.09622 -0.0087 1.0000 0.3147
-9.000 -0.5129 0.10813 0.10157 -0.0001 1.0000 0.2860
-8.750 -0.4968 0.10447 0.09790 0.0021 1.0000 0.3128
-8.500 -0.4935 0.10187 0.09536 0.0038 1.0000 0.3435
-8.250 -0.4802 0.09933 0.09285 0.0072 1.0000 0.3864
-8.000 -0.4521 0.09630 0.08980 0.0114 1.0000 0.4419
-7.750 -0.4267 0.09313 0.08664 0.0146 1.0000 0.4945
-7.500 -0.4100 0.09059 0.08409 0.0173 1.0000 0.5435
-7.250 -0.3979 0.08829 0.08183 0.0199 1.0000 0.5888
-7.000 -0.3765 0.08496 0.07852 0.0213 1.0000 0.6329
-5.750 -0.4393 0.06629 0.06047 0.0107 1.0000 0.4986
-5.500 -0.4907 0.06135 0.05580 0.0062 1.0000 0.4574
-5.250 -0.5316 0.05536 0.04988 0.0004 1.0000 0.4145
-5.000 -0.5412 0.04731 0.04107 -0.0111 1.0000 0.3257
-4.750 -0.5118 0.04348 0.03568 -0.0163 1.0000 0.2288
-4.500 -0.4839 0.04086 0.03232 -0.0158 1.0000 0.1834
-4.250 -0.4587 0.03895 0.02967 -0.0144 1.0000 0.1551
-4.000 -0.4353 0.03683 0.02709 -0.0130 1.0000 0.1395
-3.750 -0.4114 0.03552 0.02508 -0.0113 1.0000 0.1273
-3.500 -0.3881 0.03311 0.02256 -0.0105 1.0000 0.1227
-3.250 -0.3643 0.03150 0.02067 -0.0094 1.0000 0.1215
-3.000 -0.3399 0.03009 0.01901 -0.0085 1.0000 0.1219
-2.750 -0.3140 0.02878 0.01752 -0.0075 1.0000 0.1213
-2.500 -0.2874 0.02765 0.01625 -0.0065 1.0000 0.1218
-2.250 -0.2622 0.02678 0.01526 -0.0052 1.0000 0.1255
-2.000 -0.2390 0.02578 0.01427 -0.0043 1.0000 0.1350
-1.750 -0.0550 0.02220 0.01349 -0.0181 1.0000 1.0000
-1.500 -0.0630 0.02210 0.01325 -0.0139 1.0000 1.0000
-1.250 -0.0714 0.02194 0.01297 -0.0096 1.0000 1.0000
-1.000 -0.0794 0.02175 0.01265 -0.0054 1.0000 1.0000
-0.750 -0.0849 0.02157 0.01233 -0.0015 1.0000 1.0000
-0.500 -0.0844 0.02148 0.01205 0.0015 1.0000 1.0000
-0.250 -0.0758 0.02153 0.01187 0.0033 1.0000 1.0000
0.000 -0.0622 0.02172 0.01182 0.0042 1.0000 1.0000
0.250 -0.0458 0.02199 0.01189 0.0047 1.0000 1.0000
0.500 -0.0281 0.02234 0.01205 0.0050 1.0000 1.0000
0.750 -0.0095 0.02274 0.01229 0.0052 1.0000 1.0000
1.000 0.0096 0.02320 0.01259 0.0052 1.0000 1.0000
1.250 0.0289 0.02371 0.01298 0.0051 1.0000 1.0000
1.500 0.0482 0.02428 0.01345 0.0050 1.0000 1.0000
1.750 0.0676 0.02489 0.01398 0.0049 1.0000 1.0000
2.000 0.0868 0.02557 0.01459 0.0046 1.0000 1.0000
2.250 0.1498 0.02706 0.01604 -0.0039 0.9811 1.0000
2.500 0.2020 0.02825 0.01724 -0.0101 0.9622 1.0000
2.750 0.2482 0.02936 0.01838 -0.0150 0.9459 1.0000
3.000 0.2933 0.03044 0.01952 -0.0196 0.9295 1.0000
3.250 0.3400 0.03148 0.02068 -0.0241 0.9120 1.0000
3.500 0.3737 0.03233 0.02164 -0.0262 0.8919 1.0000
3.750 0.4225 0.03314 0.02261 -0.0304 0.8705 1.0000
4.000 0.4638 0.03369 0.02337 -0.0327 0.8446 1.0000
4.250 0.5152 0.03378 0.02370 -0.0356 0.8157 1.0000
4.500 0.5689 0.03342 0.02362 -0.0380 0.7866 1.0000
4.750 0.6133 0.03287 0.02338 -0.0384 0.7589 1.0000
5.000 0.6549 0.03201 0.02279 -0.0377 0.7309 1.0000
5.250 0.6928 0.03089 0.02193 -0.0360 0.7013 1.0000
5.500 0.7298 0.02942 0.02074 -0.0336 0.6692 1.0000
5.750 0.7630 0.02785 0.01936 -0.0304 0.6322 1.0000
6.000 0.7926 0.02640 0.01800 -0.0269 0.5878 1.0000
6.250 0.8209 0.02517 0.01669 -0.0233 0.5362 1.0000
6.500 0.8427 0.02504 0.01627 -0.0201 0.4787 1.0000
6.750 0.8618 0.02575 0.01665 -0.0174 0.4226 1.0000
7.000 0.8788 0.02695 0.01760 -0.0150 0.3703 1.0000
7.250 0.8962 0.02841 0.01867 -0.0128 0.3200 1.0000
7.500 0.9102 0.03024 0.02033 -0.0106 0.2696 1.0000
7.750 0.9236 0.03194 0.02180 -0.0083 0.2245 1.0000
8.000 0.9396 0.03409 0.02377 -0.0064 0.1871 1.0000
8.250 0.9602 0.03676 0.02637 -0.0052 0.1611 1.0000
8.500 0.9786 0.03934 0.02910 -0.0039 0.1429 1.0000
8.750 0.9972 0.04243 0.03249 -0.0027 0.1319 1.0000
9.000 1.0190 0.04569 0.03574 -0.0020 0.1231 1.0000
9.250 1.0240 0.04907 0.03988 0.0004 0.1179 1.0000
9.500 1.0393 0.05219 0.04313 0.0015 0.1118 1.0000
9.750 1.0482 0.05666 0.04788 0.0028 0.1097 1.0000
10.000 1.0456 0.06112 0.05285 0.0049 0.1093 1.0000
10.250 1.0384 0.06567 0.05783 0.0069 0.1091 1.0000
10.500 1.0263 0.07029 0.06280 0.0086 0.1092 1.0000
10.750 1.0118 0.07499 0.06775 0.0100 0.1095 1.0000
11.000 0.9959 0.07967 0.07260 0.0111 0.1099 1.0000
11.250 0.9012 0.08899 0.08224 0.0067 0.1195 1.0000
11.500 0.8809 0.09638 0.08964 0.0033 0.1216 1.0000
11.750 0.8761 0.10281 0.09607 0.0015 0.1231 1.0000
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Polar data table (+)
Polar graphs
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