BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 500,000 Max Cl/Cd: 71.21 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737b-il-500000-n5.txt Download as CSV file: xf-b737b-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0059 0.12237 0.11915 0.0096 1.0000 0.0131
-17.750 -1.0447 0.11006 0.10663 0.0024 1.0000 0.0131
-17.500 -1.0720 0.10057 0.09696 -0.0030 1.0000 0.0131
-17.250 -1.0943 0.09234 0.08858 -0.0077 1.0000 0.0131
-17.000 -1.1132 0.08495 0.08104 -0.0119 1.0000 0.0131
-16.750 -1.1294 0.07823 0.07418 -0.0157 1.0000 0.0132
-16.500 -1.1440 0.07207 0.06788 -0.0192 1.0000 0.0132
-16.250 -1.1561 0.06648 0.06216 -0.0222 1.0000 0.0133
-16.000 -1.1661 0.06140 0.05695 -0.0249 1.0000 0.0133
-15.750 -1.1736 0.05677 0.05220 -0.0273 1.0000 0.0134
-15.500 -1.1793 0.05256 0.04786 -0.0294 1.0000 0.0135
-15.250 -1.1828 0.04875 0.04393 -0.0312 1.0000 0.0136
-15.000 -1.1845 0.04532 0.04037 -0.0326 1.0000 0.0137
-14.750 -1.1844 0.04221 0.03714 -0.0338 1.0000 0.0138
-14.500 -1.1827 0.03942 0.03423 -0.0346 1.0000 0.0140
-14.250 -1.1797 0.03691 0.03159 -0.0351 1.0000 0.0141
-14.000 -1.1754 0.03469 0.02925 -0.0352 1.0000 0.0143
-13.750 -1.1697 0.03275 0.02720 -0.0350 1.0000 0.0144
-13.500 -1.1630 0.03106 0.02538 -0.0344 1.0000 0.0146
-13.250 -1.1552 0.02958 0.02379 -0.0335 1.0000 0.0148
-13.000 -1.1461 0.02832 0.02240 -0.0322 1.0000 0.0150
-12.750 -1.1371 0.02712 0.02112 -0.0306 1.0000 0.0152
-12.500 -1.1278 0.02600 0.01994 -0.0288 1.0000 0.0154
-12.250 -1.1137 0.02506 0.01896 -0.0274 1.0000 0.0157
-12.000 -1.0975 0.02421 0.01806 -0.0262 1.0000 0.0159
-11.750 -1.0802 0.02341 0.01720 -0.0251 1.0000 0.0162
-11.500 -1.0621 0.02264 0.01638 -0.0240 1.0000 0.0165
-11.250 -1.0433 0.02190 0.01558 -0.0229 1.0000 0.0168
-11.000 -1.0241 0.02118 0.01480 -0.0218 1.0000 0.0171
-10.750 -1.0043 0.02048 0.01403 -0.0208 1.0000 0.0175
-10.500 -0.9840 0.01982 0.01330 -0.0197 1.0000 0.0178
-10.250 -0.9631 0.01922 0.01263 -0.0187 1.0000 0.0182
-10.000 -0.9434 0.01849 0.01188 -0.0176 1.0000 0.0186
-9.750 -0.9224 0.01791 0.01128 -0.0165 1.0000 0.0190
-9.500 -0.9006 0.01741 0.01076 -0.0156 1.0000 0.0195
-9.250 -0.8787 0.01694 0.01027 -0.0146 1.0000 0.0201
-9.000 -0.8568 0.01648 0.00976 -0.0135 1.0000 0.0207
-8.750 -0.8349 0.01603 0.00928 -0.0124 1.0000 0.0213
-8.500 -0.8135 0.01555 0.00876 -0.0113 1.0000 0.0219
-8.250 -0.7923 0.01504 0.00825 -0.0101 1.0000 0.0225
-8.000 -0.7702 0.01463 0.00783 -0.0090 1.0000 0.0232
-7.750 -0.7478 0.01424 0.00742 -0.0079 1.0000 0.0239
-7.500 -0.7253 0.01388 0.00704 -0.0068 1.0000 0.0248
-7.250 -0.6986 0.01352 0.00665 -0.0067 0.9987 0.0257
-7.000 -0.6637 0.01306 0.00622 -0.0083 0.9942 0.0272
-6.750 -0.6301 0.01270 0.00584 -0.0095 0.9883 0.0286
-6.500 -0.5960 0.01236 0.00548 -0.0108 0.9814 0.0300
-6.250 -0.5624 0.01197 0.00511 -0.0120 0.9720 0.0321
-6.000 -0.5289 0.01166 0.00480 -0.0131 0.9589 0.0345
-5.750 -0.4941 0.01131 0.00446 -0.0145 0.9394 0.0380
-5.500 -0.4589 0.01100 0.00413 -0.0158 0.9077 0.0429
-5.250 -0.4299 0.01076 0.00381 -0.0158 0.8673 0.0507
-5.000 -0.4045 0.01052 0.00352 -0.0151 0.8336 0.0655
-4.750 -0.3802 0.01010 0.00320 -0.0144 0.8068 0.1051
-4.500 -0.3556 0.00970 0.00293 -0.0138 0.7850 0.1534
-4.250 -0.3299 0.00942 0.00274 -0.0133 0.7662 0.1908
-4.000 -0.3037 0.00920 0.00258 -0.0129 0.7488 0.2249
-3.750 -0.2772 0.00900 0.00244 -0.0125 0.7328 0.2561
-3.500 -0.2508 0.00882 0.00231 -0.0121 0.7133 0.2866
-3.250 -0.2247 0.00869 0.00218 -0.0117 0.6881 0.3151
-3.000 -0.1989 0.00847 0.00205 -0.0112 0.6637 0.3604
-2.750 -0.1729 0.00821 0.00195 -0.0108 0.6469 0.4136
-2.500 -0.1460 0.00808 0.00189 -0.0104 0.6318 0.4481
-2.250 -0.1186 0.00801 0.00183 -0.0102 0.6170 0.4734
-1.750 -0.0633 0.00795 0.00175 -0.0097 0.5876 0.5124
-1.500 -0.0356 0.00792 0.00172 -0.0094 0.5731 0.5302
-1.250 -0.0079 0.00791 0.00170 -0.0092 0.5589 0.5483
-1.000 0.0199 0.00790 0.00169 -0.0090 0.5439 0.5664
-0.750 0.0476 0.00791 0.00169 -0.0088 0.5273 0.5829
-0.500 0.0754 0.00794 0.00169 -0.0086 0.5088 0.5971
-0.250 0.1031 0.00799 0.00169 -0.0083 0.4874 0.6102
0.000 0.1306 0.00807 0.00170 -0.0081 0.4635 0.6233
0.250 0.1580 0.00815 0.00173 -0.0079 0.4384 0.6352
0.500 0.1853 0.00825 0.00176 -0.0076 0.4109 0.6473
1.000 0.2396 0.00854 0.00187 -0.0071 0.3489 0.6726
1.250 0.2666 0.00869 0.00195 -0.0069 0.3229 0.6858
1.500 0.2937 0.00883 0.00205 -0.0067 0.2992 0.7001
1.750 0.3206 0.00896 0.00215 -0.0064 0.2790 0.7179
2.000 0.3472 0.00904 0.00226 -0.0060 0.2634 0.7427
2.500 0.4000 0.00921 0.00251 -0.0051 0.2363 0.7935
3.000 0.4528 0.00942 0.00279 -0.0042 0.2134 0.8398
3.250 0.4787 0.00953 0.00294 -0.0036 0.2035 0.8647
3.500 0.5047 0.00967 0.00309 -0.0030 0.1927 0.8898
3.750 0.5316 0.00980 0.00325 -0.0026 0.1837 0.9135
4.000 0.5603 0.00999 0.00342 -0.0027 0.1745 0.9350
4.250 0.5920 0.01017 0.00359 -0.0034 0.1653 0.9530
4.500 0.6249 0.01039 0.00378 -0.0045 0.1570 0.9670
4.750 0.6584 0.01062 0.00397 -0.0057 0.1489 0.9786
5.000 0.6923 0.01085 0.00418 -0.0071 0.1418 0.9886
5.250 0.7262 0.01110 0.00440 -0.0085 0.1349 0.9966
5.500 0.7552 0.01135 0.00461 -0.0088 0.1296 1.0000
5.750 0.7796 0.01157 0.00483 -0.0082 0.1247 1.0000
6.000 0.8038 0.01184 0.00506 -0.0075 0.1199 1.0000
6.250 0.8285 0.01208 0.00531 -0.0070 0.1161 1.0000
6.500 0.8535 0.01232 0.00556 -0.0065 0.1120 1.0000
6.750 0.8782 0.01262 0.00583 -0.0060 0.1075 1.0000
7.000 0.9032 0.01290 0.00610 -0.0055 0.1034 1.0000
7.250 0.9283 0.01317 0.00638 -0.0051 0.0993 1.0000
7.500 0.9530 0.01350 0.00669 -0.0046 0.0954 1.0000
7.750 0.9779 0.01380 0.00701 -0.0042 0.0922 1.0000
8.000 1.0030 0.01409 0.00732 -0.0038 0.0889 1.0000
8.250 1.0276 0.01443 0.00766 -0.0034 0.0856 1.0000
8.500 1.0519 0.01481 0.00803 -0.0030 0.0823 1.0000
8.750 1.0767 0.01512 0.00838 -0.0026 0.0792 1.0000
9.000 1.1009 0.01549 0.00876 -0.0022 0.0758 1.0000
9.250 1.1246 0.01591 0.00918 -0.0017 0.0728 1.0000
9.500 1.1487 0.01628 0.00959 -0.0013 0.0699 1.0000
9.750 1.1721 0.01670 0.01003 -0.0008 0.0666 1.0000
10.000 1.1951 0.01717 0.01050 -0.0002 0.0636 1.0000
10.250 1.2181 0.01761 0.01097 0.0003 0.0605 1.0000
10.500 1.2400 0.01813 0.01151 0.0009 0.0576 1.0000
10.750 1.2620 0.01863 0.01205 0.0015 0.0551 1.0000
11.000 1.2834 0.01917 0.01262 0.0021 0.0523 1.0000
11.250 1.3035 0.01980 0.01326 0.0029 0.0497 1.0000
11.500 1.3240 0.02036 0.01388 0.0036 0.0474 1.0000
11.750 1.3430 0.02101 0.01457 0.0045 0.0452 1.0000
12.000 1.3606 0.02175 0.01533 0.0055 0.0433 1.0000
12.250 1.3784 0.02242 0.01608 0.0064 0.0417 1.0000
12.500 1.3936 0.02318 0.01689 0.0077 0.0400 1.0000
12.750 1.4058 0.02406 0.01780 0.0093 0.0385 1.0000
13.000 1.4172 0.02500 0.01881 0.0108 0.0374 1.0000
13.250 1.4285 0.02598 0.01987 0.0121 0.0363 1.0000
13.500 1.4381 0.02713 0.02111 0.0133 0.0353 1.0000
13.750 1.4461 0.02851 0.02256 0.0142 0.0344 1.0000
14.000 1.4523 0.03017 0.02429 0.0148 0.0336 1.0000
14.250 1.4560 0.03223 0.02643 0.0150 0.0328 1.0000
14.500 1.4618 0.03422 0.02853 0.0150 0.0321 1.0000
14.750 1.4660 0.03651 0.03094 0.0146 0.0315 1.0000
15.000 1.4681 0.03916 0.03370 0.0139 0.0309 1.0000
15.250 1.4678 0.04220 0.03685 0.0130 0.0303 1.0000
15.500 1.4648 0.04567 0.04043 0.0117 0.0299 1.0000
15.750 1.4589 0.04963 0.04450 0.0102 0.0295 1.0000
16.000 1.4495 0.05414 0.04913 0.0083 0.0291 1.0000
16.250 1.4363 0.05930 0.05441 0.0060 0.0288 1.0000
16.500 1.4192 0.06515 0.06039 0.0034 0.0285 1.0000
16.750 1.3987 0.07164 0.06702 0.0004 0.0283 1.0000
17.000 1.3763 0.07866 0.07418 -0.0030 0.0281 1.0000
17.250 1.3558 0.08560 0.08126 -0.0063 0.0280 1.0000
17.500 1.3339 0.09287 0.08866 -0.0098 0.0278 1.0000
17.750 1.3124 0.10018 0.09611 -0.0133 0.0277 1.0000
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