BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 50,000 Max Cl/Cd: 23.56 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737b-il-50000.txt Download as CSV file: xf-b737b-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6042 0.09960 0.09226 -0.0013 1.0000 0.1665
-10.000 -0.7511 0.07380 0.06633 -0.0253 1.0000 0.1328
-9.750 -0.7578 0.06865 0.06103 -0.0258 1.0000 0.1314
-9.500 -0.7641 0.06365 0.05586 -0.0260 1.0000 0.1304
-9.250 -0.7696 0.05879 0.05072 -0.0257 1.0000 0.1296
-9.000 -0.7714 0.05421 0.04579 -0.0250 1.0000 0.1291
-8.750 -0.7675 0.05003 0.04122 -0.0240 1.0000 0.1289
-8.500 -0.7592 0.04620 0.03696 -0.0229 1.0000 0.1291
-8.250 -0.7477 0.04281 0.03308 -0.0215 1.0000 0.1304
-8.000 -0.7330 0.03983 0.02967 -0.0202 1.0000 0.1333
-7.750 -0.7113 0.03758 0.02746 -0.0193 1.0000 0.1384
-7.500 -0.6909 0.03524 0.02483 -0.0181 1.0000 0.1433
-7.250 -0.6689 0.03301 0.02242 -0.0170 1.0000 0.1497
-7.000 -0.6464 0.03127 0.02059 -0.0159 1.0000 0.1600
-6.750 -0.6227 0.02949 0.01892 -0.0148 1.0000 0.1723
-6.500 -0.6005 0.02787 0.01733 -0.0134 1.0000 0.1918
-6.250 -0.5804 0.02624 0.01601 -0.0117 1.0000 0.2235
-6.000 -0.5673 0.02430 0.01481 -0.0090 1.0000 0.2968
-5.750 -0.5588 0.02322 0.01448 -0.0048 1.0000 0.3995
-5.500 -0.5443 0.02323 0.01476 -0.0011 1.0000 0.4615
-5.250 -0.5273 0.02348 0.01520 0.0024 1.0000 0.5074
-5.000 -0.5115 0.02392 0.01578 0.0063 1.0000 0.5531
-4.750 -0.4947 0.02465 0.01673 0.0111 1.0000 0.5938
-4.500 -0.4775 0.02473 0.01688 0.0149 1.0000 0.6282
-4.250 -0.4600 0.02438 0.01652 0.0177 1.0000 0.6582
-4.000 -0.4419 0.02415 0.01631 0.0208 1.0000 0.6854
-3.750 -0.4264 0.02376 0.01591 0.0237 1.0000 0.7159
-3.500 -0.4092 0.02362 0.01579 0.0270 1.0000 0.7440
-3.250 -0.3931 0.02343 0.01558 0.0301 1.0000 0.7741
-3.000 -0.3772 0.02324 0.01537 0.0330 1.0000 0.8058
-2.750 -0.3551 0.02322 0.01530 0.0350 1.0000 0.8373
-2.500 -0.3214 0.02332 0.01532 0.0349 1.0000 0.8694
-2.250 -0.2691 0.02349 0.01534 0.0311 1.0000 0.9021
-2.000 -0.1904 0.02363 0.01529 0.0219 1.0000 0.9330
-1.750 -0.0993 0.02351 0.01498 0.0095 1.0000 0.9609
-1.500 -0.0117 0.02311 0.01446 -0.0034 1.0000 0.9872
-1.250 0.0148 0.02296 0.01428 -0.0073 1.0000 1.0000
-1.000 -0.0183 0.02305 0.01438 -0.0019 1.0000 1.0000
-0.750 -0.0502 0.02292 0.01426 0.0033 1.0000 1.0000
-0.500 0.0063 0.02327 0.01454 -0.0052 0.9813 1.0000
-0.250 0.0890 0.02357 0.01479 -0.0168 0.9544 1.0000
0.000 0.1738 0.02358 0.01480 -0.0279 0.9273 1.0000
0.250 0.2557 0.02325 0.01450 -0.0374 0.8996 1.0000
0.500 0.3185 0.02277 0.01403 -0.0427 0.8710 1.0000
0.750 0.3493 0.02265 0.01390 -0.0426 0.8396 1.0000
1.000 0.3739 0.02263 0.01385 -0.0412 0.8087 1.0000
1.250 0.3956 0.02261 0.01377 -0.0388 0.7787 1.0000
1.500 0.4136 0.02269 0.01377 -0.0359 0.7478 1.0000
1.750 0.4294 0.02287 0.01388 -0.0327 0.7152 1.0000
2.000 0.4461 0.02304 0.01396 -0.0296 0.6827 1.0000
2.250 0.4637 0.02320 0.01398 -0.0265 0.6502 1.0000
2.500 0.4826 0.02334 0.01394 -0.0236 0.6185 1.0000
2.750 0.5014 0.02357 0.01403 -0.0209 0.5859 1.0000
3.000 0.5201 0.02395 0.01427 -0.0186 0.5535 1.0000
3.250 0.5399 0.02436 0.01453 -0.0165 0.5235 1.0000
3.500 0.5616 0.02470 0.01465 -0.0145 0.4970 1.0000
3.750 0.5816 0.02533 0.01523 -0.0128 0.4698 1.0000
4.000 0.6038 0.02589 0.01562 -0.0112 0.4467 1.0000
4.250 0.6261 0.02658 0.01615 -0.0099 0.4253 1.0000
4.500 0.6472 0.02752 0.01710 -0.0087 0.4048 1.0000
4.750 0.6690 0.02847 0.01801 -0.0075 0.3864 1.0000
5.000 0.6911 0.02950 0.01900 -0.0065 0.3699 1.0000
5.250 0.7137 0.03061 0.02006 -0.0056 0.3554 1.0000
5.500 0.7370 0.03169 0.02108 -0.0047 0.3418 1.0000
5.750 0.7557 0.03331 0.02291 -0.0037 0.3289 1.0000
6.000 0.7748 0.03504 0.02477 -0.0029 0.3178 1.0000
6.250 0.8001 0.03619 0.02578 -0.0022 0.3074 1.0000
6.500 0.8114 0.03873 0.02877 -0.0012 0.2978 1.0000
6.750 0.8346 0.04024 0.03020 -0.0005 0.2891 1.0000
7.000 0.8418 0.04330 0.03370 0.0005 0.2808 1.0000
7.250 0.8688 0.04460 0.03483 0.0011 0.2730 1.0000
7.500 0.8625 0.04919 0.04003 0.0019 0.2674 1.0000
7.750 0.8680 0.05254 0.04360 0.0026 0.2611 1.0000
8.000 0.8864 0.05488 0.04594 0.0033 0.2551 1.0000
8.250 0.8572 0.06222 0.05370 0.0026 0.2538 1.0000
8.500 0.8201 0.07093 0.06259 0.0001 0.2546 1.0000
8.750 0.7846 0.08008 0.07180 -0.0037 0.2569 1.0000
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Polar data table (+)
Polar graphs
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