BOEING 737 MIDSPAN AIRFOIL (b737c-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737c-il) Reynolds number: 200,000 Max Cl/Cd: 65.15 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737c-il-200000.txt Download as CSV file: xf-b737c-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4334 0.08716 0.08396 -0.0229 1.0000 0.0403
-9.000 -0.4431 0.08172 0.07855 -0.0274 1.0000 0.0405
-8.750 -0.4555 0.07617 0.07299 -0.0319 1.0000 0.0406
-8.500 -0.4695 0.07167 0.06845 -0.0345 1.0000 0.0406
-8.250 -0.4865 0.06812 0.06484 -0.0348 1.0000 0.0407
-8.000 -0.4997 0.06467 0.06126 -0.0346 1.0000 0.0409
-7.750 -0.5084 0.06142 0.05784 -0.0336 1.0000 0.0410
-7.500 -0.5128 0.05822 0.05446 -0.0320 1.0000 0.0412
-7.250 -0.5138 0.04982 0.04621 -0.0321 1.0000 0.0423
-7.000 -0.5076 0.04592 0.04238 -0.0310 1.0000 0.0435
-6.750 -0.5441 0.05456 0.05051 -0.0283 1.0000 0.0434
-6.500 -0.5362 0.05179 0.04771 -0.0270 1.0000 0.0452
-6.250 -0.5280 0.04923 0.04501 -0.0252 1.0000 0.0479
-6.000 -0.5164 0.05135 0.04639 -0.0211 1.0000 0.0529
-5.750 -0.5124 0.04449 0.03953 -0.0199 1.0000 0.0544
-5.500 -0.5010 0.04102 0.03615 -0.0188 1.0000 0.0563
-5.250 -0.4885 0.03891 0.03395 -0.0170 1.0000 0.0608
-5.000 -0.4765 0.03758 0.03206 -0.0140 1.0000 0.0674
-4.750 -0.4624 0.03419 0.02874 -0.0129 1.0000 0.0696
-4.500 -0.4421 0.03194 0.02635 -0.0122 0.9989 0.0732
-4.250 -0.3497 0.01349 0.00782 -0.0236 0.9764 0.0860
-4.000 -0.3103 0.01100 0.00504 -0.0265 0.9702 0.0993
-3.750 -0.3087 0.02253 0.01518 -0.0175 0.9821 0.0420
-3.500 -0.2669 0.02040 0.01288 -0.0199 0.9743 0.0404
-3.250 -0.2217 0.01828 0.01058 -0.0230 0.9695 0.0402
-3.000 -0.1832 0.01646 0.00868 -0.0248 0.9588 0.0395
-2.750 -0.1463 0.01513 0.00731 -0.0263 0.9461 0.0399
-2.500 -0.1125 0.01416 0.00631 -0.0272 0.9299 0.0410
-2.250 -0.0839 0.01325 0.00545 -0.0274 0.9094 0.0460
-2.000 -0.0564 0.01268 0.00478 -0.0270 0.8874 0.0508
-1.750 -0.0301 0.01207 0.00406 -0.0265 0.8675 0.0610
-1.500 -0.0097 0.01057 0.00332 -0.0255 0.8494 0.3052
-1.250 0.0062 0.00932 0.00322 -0.0232 0.8344 0.6299
-1.000 0.0261 0.00887 0.00324 -0.0207 0.8220 0.7514
-0.750 0.0491 0.00886 0.00342 -0.0186 0.8122 0.8494
-0.500 0.0746 0.00899 0.00351 -0.0173 0.8021 0.8960
-0.250 0.1036 0.00914 0.00358 -0.0169 0.7930 0.9259
0.000 0.1422 0.00936 0.00367 -0.0183 0.7849 0.9552
0.250 0.2091 0.00957 0.00378 -0.0260 0.7765 0.9801
0.500 0.2603 0.00962 0.00370 -0.0310 0.7694 0.9921
0.750 0.3050 0.00962 0.00363 -0.0349 0.7607 1.0000
1.000 0.3304 0.00966 0.00359 -0.0347 0.7522 1.0000
1.250 0.3555 0.00972 0.00357 -0.0344 0.7424 1.0000
1.500 0.3804 0.00978 0.00358 -0.0341 0.7311 1.0000
1.750 0.4052 0.00985 0.00361 -0.0336 0.7205 1.0000
2.000 0.4299 0.00995 0.00365 -0.0331 0.7109 1.0000
2.250 0.4547 0.01004 0.00373 -0.0327 0.7011 1.0000
2.500 0.4793 0.01014 0.00384 -0.0322 0.6911 1.0000
2.750 0.5038 0.01026 0.00394 -0.0316 0.6811 1.0000
3.000 0.5281 0.01037 0.00404 -0.0310 0.6701 1.0000
3.250 0.5520 0.01047 0.00416 -0.0303 0.6577 1.0000
3.500 0.5756 0.01056 0.00427 -0.0294 0.6430 1.0000
3.750 0.5987 0.01065 0.00433 -0.0283 0.6258 1.0000
4.000 0.6217 0.01073 0.00444 -0.0274 0.6078 1.0000
4.250 0.6447 0.01083 0.00456 -0.0264 0.5897 1.0000
4.500 0.6676 0.01097 0.00469 -0.0253 0.5699 1.0000
4.750 0.6901 0.01103 0.00484 -0.0242 0.5439 1.0000
5.000 0.7127 0.01094 0.00489 -0.0232 0.4900 1.0000
5.250 0.7306 0.01126 0.00480 -0.0212 0.4392 1.0000
5.500 0.7501 0.01179 0.00517 -0.0198 0.3836 1.0000
5.750 0.7685 0.01245 0.00558 -0.0183 0.3286 1.0000
6.000 0.7876 0.01312 0.00605 -0.0170 0.2786 1.0000
6.250 0.8067 0.01384 0.00656 -0.0158 0.2342 1.0000
6.500 0.8263 0.01456 0.00712 -0.0147 0.1942 1.0000
6.750 0.8461 0.01529 0.00773 -0.0137 0.1589 1.0000
7.000 0.8658 0.01607 0.00838 -0.0127 0.1263 1.0000
7.250 0.8837 0.01708 0.00921 -0.0114 0.0966 1.0000
7.500 0.9007 0.01825 0.01030 -0.0099 0.0731 1.0000
7.750 0.9168 0.01956 0.01157 -0.0083 0.0595 1.0000
8.000 0.9354 0.02061 0.01271 -0.0070 0.0511 1.0000
8.250 0.9505 0.02228 0.01435 -0.0053 0.0459 1.0000
8.500 0.9702 0.02340 0.01564 -0.0040 0.0420 1.0000
8.750 0.9883 0.02461 0.01687 -0.0029 0.0377 1.0000
9.000 1.0057 0.02685 0.01924 -0.0016 0.0347 1.0000
9.250 1.0246 0.02800 0.02061 -0.0005 0.0314 1.0000
9.500 1.0420 0.02949 0.02221 0.0006 0.0287 1.0000
9.750 1.0570 0.03290 0.02578 0.0018 0.0268 1.0000
10.000 1.0682 0.03627 0.02956 0.0035 0.0258 1.0000
10.250 1.0783 0.03843 0.03210 0.0055 0.0248 1.0000
10.500 1.0851 0.04074 0.03476 0.0075 0.0235 1.0000
10.750 1.0886 0.04320 0.03752 0.0096 0.0224 1.0000
11.000 1.0850 0.04622 0.04086 0.0121 0.0220 1.0000
11.250 1.0741 0.04956 0.04450 0.0149 0.0219 1.0000
11.500 1.0588 0.05330 0.04855 0.0169 0.0220 1.0000
11.750 1.0401 0.05761 0.05314 0.0177 0.0221 1.0000
12.000 1.0193 0.06266 0.05845 0.0169 0.0223 1.0000
12.250 0.9970 0.06855 0.06457 0.0145 0.0226 1.0000
12.500 0.9734 0.07533 0.07156 0.0107 0.0229 1.0000
12.750 0.9486 0.08305 0.07946 0.0058 0.0233 1.0000
13.000 0.9224 0.09230 0.08885 -0.0008 0.0238 1.0000
13.250 0.8939 0.10354 0.10018 -0.0085 0.0246 1.0000
13.500 0.8682 0.11460 0.11126 -0.0147 0.0257 1.0000
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Polar data table (+)
Polar graphs
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