BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 100,000 Max Cl/Cd: 34.78 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737b-il-100000.txt Download as CSV file: xf-b737b-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6114 0.11867 0.11346 0.0062 1.0000 0.1629
-11.000 -0.6987 0.08410 0.07888 -0.0189 1.0000 0.0949
-10.750 -0.8352 0.06637 0.06044 -0.0311 1.0000 0.0821
-10.500 -0.8209 0.06205 0.05611 -0.0309 1.0000 0.0795
-10.250 -0.8282 0.05714 0.05099 -0.0304 1.0000 0.0773
-10.000 -0.8505 0.05068 0.04383 -0.0287 1.0000 0.0734
-9.750 -0.8573 0.04707 0.03932 -0.0260 1.0000 0.0710
-9.500 -0.8453 0.04355 0.03552 -0.0248 1.0000 0.0706
-9.250 -0.8325 0.04063 0.03224 -0.0233 1.0000 0.0707
-9.000 -0.8183 0.03781 0.02907 -0.0219 1.0000 0.0717
-8.750 -0.7990 0.03522 0.02642 -0.0212 1.0000 0.0733
-8.500 -0.7782 0.03319 0.02426 -0.0202 1.0000 0.0748
-8.250 -0.7569 0.03122 0.02209 -0.0190 1.0000 0.0760
-8.000 -0.7347 0.02945 0.02013 -0.0179 1.0000 0.0777
-7.750 -0.7124 0.02803 0.01848 -0.0168 1.0000 0.0805
-7.500 -0.6891 0.02624 0.01671 -0.0159 1.0000 0.0837
-7.250 -0.6660 0.02488 0.01542 -0.0149 1.0000 0.0872
-7.000 -0.6431 0.02370 0.01417 -0.0137 1.0000 0.0913
-6.750 -0.6223 0.02237 0.01299 -0.0125 1.0000 0.0969
-6.500 -0.6014 0.02138 0.01202 -0.0110 1.0000 0.1043
-6.250 -0.5830 0.02021 0.01102 -0.0094 1.0000 0.1135
-6.000 -0.5647 0.01913 0.01009 -0.0077 1.0000 0.1306
-5.750 -0.5502 0.01751 0.00903 -0.0056 1.0000 0.1825
-5.500 -0.5373 0.01612 0.00845 -0.0035 1.0000 0.3194
-5.250 -0.5181 0.01566 0.00819 -0.0019 1.0000 0.3763
-5.000 -0.4980 0.01535 0.00805 -0.0005 1.0000 0.4185
-4.750 -0.4776 0.01513 0.00797 0.0010 1.0000 0.4571
-4.500 -0.4574 0.01500 0.00795 0.0025 1.0000 0.4966
-4.250 -0.4387 0.01500 0.00813 0.0044 1.0000 0.5379
-4.000 -0.4208 0.01511 0.00840 0.0065 1.0000 0.5769
-3.750 -0.4027 0.01518 0.00858 0.0083 1.0000 0.6104
-3.500 -0.3839 0.01522 0.00867 0.0097 1.0000 0.6394
-3.250 -0.3645 0.01528 0.00880 0.0109 1.0000 0.6650
-3.000 -0.3362 0.01540 0.00897 0.0104 0.9961 0.6931
-2.750 -0.2871 0.01554 0.00916 0.0065 0.9829 0.7225
-2.500 -0.2414 0.01561 0.00923 0.0033 0.9681 0.7512
-2.250 -0.1969 0.01568 0.00936 0.0008 0.9540 0.7753
-2.000 -0.1518 0.01571 0.00939 -0.0017 0.9402 0.7991
-1.750 -0.1082 0.01564 0.00932 -0.0037 0.9248 0.8215
-1.500 -0.0667 0.01554 0.00921 -0.0049 0.9079 0.8409
-1.250 -0.0283 0.01544 0.00908 -0.0054 0.8902 0.8592
-1.000 0.0073 0.01537 0.00896 -0.0054 0.8720 0.8769
-0.750 0.0421 0.01533 0.00887 -0.0054 0.8535 0.8940
-0.500 0.0793 0.01535 0.00883 -0.0059 0.8335 0.9094
-0.250 0.1189 0.01538 0.00879 -0.0071 0.8125 0.9246
0.000 0.1618 0.01541 0.00873 -0.0090 0.7907 0.9397
0.250 0.2098 0.01542 0.00862 -0.0121 0.7679 0.9545
0.500 0.2582 0.01538 0.00847 -0.0155 0.7440 0.9695
0.750 0.3062 0.01528 0.00828 -0.0193 0.7168 0.9838
1.000 0.3561 0.01511 0.00797 -0.0235 0.6891 0.9967
1.250 0.3830 0.01497 0.00775 -0.0239 0.6623 1.0000
1.500 0.4021 0.01488 0.00751 -0.0226 0.6380 1.0000
1.750 0.4206 0.01482 0.00738 -0.0213 0.6099 1.0000
2.000 0.4392 0.01482 0.00722 -0.0197 0.5822 1.0000
2.250 0.4578 0.01488 0.00714 -0.0182 0.5511 1.0000
2.500 0.4767 0.01499 0.00710 -0.0166 0.5175 1.0000
2.750 0.4960 0.01518 0.00711 -0.0150 0.4836 1.0000
3.000 0.5158 0.01547 0.00719 -0.0135 0.4502 1.0000
3.250 0.5360 0.01584 0.00735 -0.0121 0.4192 1.0000
3.500 0.5567 0.01628 0.00755 -0.0108 0.3924 1.0000
3.750 0.5778 0.01675 0.00788 -0.0096 0.3666 1.0000
4.000 0.5994 0.01728 0.00822 -0.0084 0.3451 1.0000
4.250 0.6214 0.01788 0.00864 -0.0074 0.3262 1.0000
4.500 0.6439 0.01852 0.00915 -0.0065 0.3089 1.0000
4.750 0.6668 0.01917 0.00972 -0.0056 0.2931 1.0000
5.000 0.6900 0.01987 0.01037 -0.0049 0.2790 1.0000
5.250 0.7134 0.02061 0.01108 -0.0041 0.2666 1.0000
5.500 0.7377 0.02144 0.01172 -0.0036 0.2559 1.0000
5.750 0.7609 0.02212 0.01252 -0.0028 0.2450 1.0000
6.000 0.7849 0.02300 0.01337 -0.0023 0.2359 1.0000
6.250 0.8086 0.02376 0.01414 -0.0017 0.2269 1.0000
6.500 0.8324 0.02475 0.01516 -0.0011 0.2191 1.0000
6.750 0.8556 0.02555 0.01604 -0.0005 0.2111 1.0000
7.000 0.8794 0.02664 0.01712 0.0000 0.2044 1.0000
7.250 0.9014 0.02757 0.01824 0.0008 0.1971 1.0000
7.500 0.9266 0.02868 0.01918 0.0010 0.1909 1.0000
7.750 0.9457 0.02980 0.02067 0.0021 0.1843 1.0000
8.000 0.9686 0.03071 0.02159 0.0027 0.1781 1.0000
8.250 0.9890 0.03213 0.02314 0.0034 0.1724 1.0000
8.500 1.0083 0.03333 0.02457 0.0043 0.1661 1.0000
8.750 1.0330 0.03438 0.02544 0.0045 0.1606 1.0000
9.000 1.0455 0.03619 0.02772 0.0060 0.1551 1.0000
9.250 1.0655 0.03724 0.02886 0.0068 0.1494 1.0000
9.500 1.0860 0.03881 0.03038 0.0072 0.1446 1.0000
9.750 1.0925 0.04104 0.03312 0.0091 0.1396 1.0000
10.000 1.1118 0.04215 0.03425 0.0098 0.1347 1.0000
10.250 1.1295 0.04406 0.03615 0.0103 0.1307 1.0000
10.500 1.1229 0.04733 0.04001 0.0126 0.1271 1.0000
10.750 1.1255 0.04981 0.04276 0.0141 0.1234 1.0000
11.000 1.1524 0.05041 0.04319 0.0143 0.1194 1.0000
11.250 1.1482 0.05397 0.04699 0.0158 0.1171 1.0000
11.500 1.1175 0.05866 0.05213 0.0182 0.1161 1.0000
11.750 1.0775 0.06414 0.05791 0.0193 0.1160 1.0000
12.000 1.0277 0.07223 0.06625 0.0165 0.1166 1.0000
12.250 0.9690 0.08428 0.07846 0.0095 0.1177 1.0000
12.500 0.7508 0.15181 0.14606 -0.0294 0.1753 1.0000
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Polar data table (+)
Polar graphs
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