BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 100,000 Max Cl/Cd: 37.8 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737b-il-100000-n5.txt Download as CSV file: xf-b737b-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7431 0.10347 0.09773 -0.0056 1.0000 0.0346
-13.250 -0.7799 0.09068 0.08483 -0.0146 1.0000 0.0341
-13.000 -0.8143 0.08013 0.07409 -0.0226 1.0000 0.0338
-12.750 -0.8434 0.07195 0.06570 -0.0287 1.0000 0.0335
-12.500 -0.8678 0.06557 0.05909 -0.0328 1.0000 0.0334
-12.250 -0.8882 0.06051 0.05377 -0.0351 1.0000 0.0334
-12.000 -0.9051 0.05642 0.04943 -0.0357 1.0000 0.0335
-11.750 -0.9185 0.05304 0.04578 -0.0348 1.0000 0.0336
-11.500 -0.9269 0.05002 0.04246 -0.0331 1.0000 0.0338
-11.250 -0.9288 0.04707 0.03917 -0.0316 1.0000 0.0341
-11.000 -0.9260 0.04432 0.03605 -0.0301 1.0000 0.0344
-10.750 -0.9192 0.04178 0.03312 -0.0285 1.0000 0.0349
-10.500 -0.9041 0.03983 0.03110 -0.0276 1.0000 0.0354
-10.250 -0.8882 0.03821 0.02942 -0.0267 1.0000 0.0363
-10.000 -0.8720 0.03666 0.02775 -0.0257 1.0000 0.0374
-9.750 -0.8552 0.03504 0.02594 -0.0246 1.0000 0.0387
-9.500 -0.8372 0.03340 0.02403 -0.0234 1.0000 0.0398
-9.250 -0.8176 0.03183 0.02230 -0.0224 1.0000 0.0408
-9.000 -0.7975 0.03045 0.02095 -0.0215 1.0000 0.0417
-8.750 -0.7775 0.02924 0.01971 -0.0205 1.0000 0.0430
-8.500 -0.7574 0.02812 0.01852 -0.0194 1.0000 0.0448
-8.250 -0.7367 0.02708 0.01732 -0.0183 1.0000 0.0468
-8.000 -0.7178 0.02593 0.01627 -0.0171 1.0000 0.0485
-7.750 -0.6984 0.02493 0.01528 -0.0159 1.0000 0.0503
-7.500 -0.6789 0.02401 0.01430 -0.0146 1.0000 0.0526
-7.250 -0.6600 0.02309 0.01337 -0.0133 1.0000 0.0553
-7.000 -0.6409 0.02224 0.01253 -0.0119 1.0000 0.0587
-6.750 -0.6213 0.02145 0.01169 -0.0106 1.0000 0.0624
-6.500 -0.6025 0.02059 0.01085 -0.0092 1.0000 0.0669
-6.250 -0.5831 0.01979 0.01008 -0.0079 1.0000 0.0740
-6.000 -0.5637 0.01896 0.00932 -0.0065 1.0000 0.0851
-5.750 -0.5450 0.01800 0.00861 -0.0052 1.0000 0.1112
-5.500 -0.5269 0.01700 0.00805 -0.0040 1.0000 0.1765
-5.250 -0.5071 0.01634 0.00768 -0.0028 1.0000 0.2353
-5.000 -0.4862 0.01588 0.00739 -0.0018 1.0000 0.2781
-4.750 -0.4654 0.01547 0.00714 -0.0007 1.0000 0.3158
-4.500 -0.4440 0.01508 0.00697 0.0002 0.9992 0.3609
-4.250 -0.4058 0.01463 0.00694 -0.0022 0.9864 0.4344
-4.000 -0.3670 0.01440 0.00691 -0.0044 0.9731 0.4885
-3.750 -0.3297 0.01422 0.00677 -0.0061 0.9572 0.5201
-3.500 -0.2934 0.01407 0.00664 -0.0075 0.9400 0.5475
-3.250 -0.2571 0.01394 0.00652 -0.0089 0.9226 0.5733
-3.000 -0.2216 0.01381 0.00639 -0.0100 0.9044 0.5975
-2.750 -0.1876 0.01371 0.00627 -0.0107 0.8854 0.6204
-2.250 -0.1236 0.01354 0.00604 -0.0112 0.8470 0.6613
-2.000 -0.0941 0.01349 0.00595 -0.0108 0.8275 0.6798
-1.750 -0.0660 0.01346 0.00586 -0.0102 0.8059 0.6975
-1.500 -0.0386 0.01345 0.00577 -0.0093 0.7833 0.7149
-1.250 -0.0120 0.01345 0.00571 -0.0084 0.7607 0.7317
-1.000 0.0146 0.01346 0.00568 -0.0075 0.7400 0.7486
-0.750 0.0414 0.01347 0.00566 -0.0067 0.7210 0.7659
-0.500 0.0680 0.01350 0.00566 -0.0058 0.7027 0.7838
-0.250 0.0943 0.01353 0.00566 -0.0049 0.6847 0.8026
0.000 0.1206 0.01357 0.00569 -0.0040 0.6667 0.8231
0.250 0.1477 0.01363 0.00574 -0.0031 0.6482 0.8444
0.500 0.1758 0.01369 0.00578 -0.0025 0.6290 0.8661
0.750 0.2055 0.01376 0.00581 -0.0023 0.6088 0.8861
1.000 0.2370 0.01385 0.00582 -0.0025 0.5875 0.9045
1.250 0.2701 0.01395 0.00583 -0.0032 0.5646 0.9220
1.500 0.3048 0.01405 0.00587 -0.0043 0.5383 0.9388
1.750 0.3407 0.01417 0.00588 -0.0058 0.5095 0.9547
2.000 0.3775 0.01432 0.00589 -0.0075 0.4774 0.9698
2.250 0.4158 0.01451 0.00592 -0.0097 0.4421 0.9832
2.500 0.4556 0.01474 0.00598 -0.0124 0.4044 0.9954
2.750 0.4828 0.01501 0.00607 -0.0126 0.3729 1.0000
3.000 0.5032 0.01530 0.00620 -0.0115 0.3469 1.0000
3.250 0.5238 0.01565 0.00638 -0.0103 0.3246 1.0000
3.500 0.5449 0.01601 0.00661 -0.0093 0.3049 1.0000
3.750 0.5662 0.01639 0.00689 -0.0082 0.2878 1.0000
4.000 0.5878 0.01680 0.00719 -0.0072 0.2724 1.0000
4.250 0.6099 0.01721 0.00752 -0.0063 0.2583 1.0000
4.500 0.6325 0.01762 0.00789 -0.0055 0.2455 1.0000
4.750 0.6550 0.01806 0.00828 -0.0046 0.2341 1.0000
5.000 0.6774 0.01854 0.00867 -0.0038 0.2236 1.0000
5.250 0.7007 0.01898 0.00913 -0.0031 0.2133 1.0000
5.500 0.7233 0.01949 0.00957 -0.0023 0.2048 1.0000
5.750 0.7467 0.01997 0.01007 -0.0016 0.1958 1.0000
6.000 0.7694 0.02052 0.01058 -0.0009 0.1884 1.0000
6.250 0.7928 0.02103 0.01114 -0.0003 0.1807 1.0000
6.500 0.8153 0.02164 0.01166 0.0004 0.1745 1.0000
6.750 0.8387 0.02219 0.01232 0.0010 0.1675 1.0000
7.000 0.8611 0.02279 0.01290 0.0017 0.1618 1.0000
7.250 0.8839 0.02345 0.01361 0.0023 0.1561 1.0000
7.500 0.9065 0.02407 0.01430 0.0029 0.1503 1.0000
7.750 0.9283 0.02478 0.01495 0.0036 0.1458 1.0000
8.000 0.9506 0.02550 0.01582 0.0042 0.1404 1.0000
8.250 0.9722 0.02619 0.01656 0.0049 0.1354 1.0000
8.500 0.9931 0.02698 0.01729 0.0056 0.1313 1.0000
8.750 1.0140 0.02779 0.01832 0.0063 0.1262 1.0000
9.000 1.0342 0.02856 0.01916 0.0070 0.1216 1.0000
9.250 1.0538 0.02940 0.01994 0.0078 0.1178 1.0000
9.500 1.0726 0.03035 0.02115 0.0086 0.1132 1.0000
9.750 1.0907 0.03122 0.02211 0.0095 0.1089 1.0000
10.000 1.1083 0.03210 0.02295 0.0103 0.1055 1.0000
10.250 1.1241 0.03327 0.02438 0.0113 0.1015 1.0000
10.500 1.1391 0.03434 0.02558 0.0124 0.0977 1.0000
10.750 1.1536 0.03531 0.02657 0.0134 0.0947 1.0000
11.000 1.1657 0.03665 0.02805 0.0146 0.0917 1.0000
11.250 1.1749 0.03808 0.02972 0.0159 0.0884 1.0000
11.500 1.1824 0.03936 0.03110 0.0175 0.0857 1.0000
11.750 1.1904 0.04061 0.03235 0.0188 0.0836 1.0000
12.000 1.1937 0.04249 0.03442 0.0200 0.0814 1.0000
12.250 1.1933 0.04477 0.03695 0.0209 0.0790 1.0000
12.500 1.1933 0.04705 0.03941 0.0213 0.0770 1.0000
12.750 1.1944 0.04930 0.04175 0.0214 0.0752 1.0000
13.000 1.1975 0.05143 0.04389 0.0213 0.0737 1.0000
13.250 1.1906 0.05499 0.04766 0.0204 0.0722 1.0000
13.500 1.1761 0.05976 0.05272 0.0186 0.0709 1.0000
13.750 1.1589 0.06520 0.05842 0.0161 0.0697 1.0000
14.000 1.1371 0.07168 0.06512 0.0126 0.0688 1.0000
14.250 1.1041 0.08045 0.07414 0.0074 0.0682 1.0000
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