BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.75 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737a-il-1000000.txt Download as CSV file: xf-b737a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 737 ROOT AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.2570 0.08953 0.08552 -0.0061 1.0000 0.0273
-18.250 -1.2930 0.08049 0.07633 -0.0106 1.0000 0.0273
-18.000 -1.3299 0.07126 0.06693 -0.0153 1.0000 0.0273
-17.750 -1.3642 0.06235 0.05785 -0.0199 1.0000 0.0273
-17.500 -1.3912 0.05469 0.05001 -0.0240 1.0000 0.0273
-17.250 -1.4105 0.04854 0.04372 -0.0271 1.0000 0.0274
-17.000 -1.4222 0.04379 0.03885 -0.0292 1.0000 0.0276
-16.750 -1.4284 0.04000 0.03496 -0.0305 1.0000 0.0278
-16.500 -1.4296 0.03695 0.03183 -0.0313 1.0000 0.0280
-16.250 -1.4277 0.03438 0.02918 -0.0317 1.0000 0.0283
-16.000 -1.4234 0.03214 0.02687 -0.0319 1.0000 0.0286
-15.750 -1.4169 0.03021 0.02487 -0.0319 1.0000 0.0290
-15.500 -1.4086 0.02851 0.02310 -0.0317 1.0000 0.0293
-15.250 -1.3987 0.02703 0.02156 -0.0313 1.0000 0.0297
-15.000 -1.3871 0.02578 0.02024 -0.0308 1.0000 0.0300
-14.750 -1.3795 0.02430 0.01869 -0.0299 1.0000 0.0304
-14.500 -1.3709 0.02304 0.01738 -0.0287 1.0000 0.0310
-14.250 -1.3586 0.02214 0.01645 -0.0273 1.0000 0.0315
-14.000 -1.3440 0.02143 0.01570 -0.0257 1.0000 0.0320
-13.750 -1.3270 0.02079 0.01504 -0.0244 1.0000 0.0326
-13.500 -1.3077 0.02022 0.01443 -0.0234 1.0000 0.0332
-13.250 -1.2873 0.01969 0.01386 -0.0224 1.0000 0.0338
-13.000 -1.2696 0.01891 0.01305 -0.0212 1.0000 0.0347
-12.750 -1.2489 0.01834 0.01247 -0.0202 1.0000 0.0355
-12.500 -1.2269 0.01787 0.01198 -0.0193 1.0000 0.0363
-12.250 -1.2041 0.01745 0.01153 -0.0184 1.0000 0.0372
-12.000 -1.1824 0.01691 0.01097 -0.0175 1.0000 0.0381
-11.750 -1.1604 0.01638 0.01044 -0.0165 1.0000 0.0392
-11.500 -1.1372 0.01597 0.01001 -0.0157 1.0000 0.0403
-11.250 -1.1133 0.01562 0.00964 -0.0148 1.0000 0.0414
-11.000 -1.0913 0.01507 0.00909 -0.0138 1.0000 0.0427
-10.750 -1.0682 0.01464 0.00864 -0.0129 1.0000 0.0440
-10.500 -1.0445 0.01429 0.00828 -0.0120 1.0000 0.0454
-10.250 -1.0221 0.01380 0.00779 -0.0109 1.0000 0.0471
-10.000 -0.9994 0.01337 0.00735 -0.0098 1.0000 0.0490
-9.750 -0.9771 0.01291 0.00689 -0.0086 1.0000 0.0518
-9.500 -0.9578 0.01217 0.00638 -0.0072 1.0000 0.0799
-9.250 -0.9310 0.01218 0.00642 -0.0065 1.0000 0.0893
-9.000 -0.9050 0.01211 0.00640 -0.0058 1.0000 0.0924
-8.750 -0.8783 0.01212 0.00643 -0.0051 1.0000 0.0950
-8.500 -0.8515 0.01217 0.00647 -0.0045 1.0000 0.0966
-8.250 -0.8195 0.01188 0.00621 -0.0052 0.9978 0.0985
-8.000 -0.7780 0.01172 0.00609 -0.0077 0.9917 0.1004
-7.750 -0.7354 0.01158 0.00596 -0.0104 0.9725 0.1021
-7.500 -0.6885 0.01157 0.00577 -0.0137 0.8847 0.1033
-7.250 -0.6630 0.01168 0.00568 -0.0127 0.8385 0.1038
-7.000 -0.6376 0.01143 0.00535 -0.0120 0.8170 0.1049
-6.750 -0.6110 0.01120 0.00508 -0.0115 0.8015 0.1059
-6.500 -0.5838 0.01104 0.00488 -0.0111 0.7876 0.1066
-6.250 -0.5565 0.01090 0.00470 -0.0107 0.7740 0.1074
-6.000 -0.5287 0.01076 0.00454 -0.0103 0.7618 0.1083
-5.750 -0.5011 0.01064 0.00437 -0.0099 0.7480 0.1088
-5.500 -0.4733 0.01051 0.00420 -0.0096 0.7339 0.1094
-5.250 -0.4453 0.01039 0.00405 -0.0092 0.7210 0.1099
-5.000 -0.4174 0.01028 0.00389 -0.0089 0.7071 0.1103
-4.750 -0.3892 0.01016 0.00375 -0.0086 0.6945 0.1107
-4.500 -0.3611 0.01007 0.00361 -0.0083 0.6805 0.1111
-4.250 -0.3328 0.00998 0.00349 -0.0080 0.6646 0.1114
-4.000 -0.3048 0.00988 0.00334 -0.0076 0.6462 0.1119
-3.750 -0.2772 0.00975 0.00315 -0.0073 0.6253 0.1127
-3.500 -0.2495 0.00966 0.00299 -0.0069 0.5999 0.1136
-3.250 -0.2220 0.00964 0.00286 -0.0065 0.5670 0.1140
-3.000 -0.1947 0.00967 0.00276 -0.0061 0.5217 0.1143
-2.750 -0.1686 0.00987 0.00268 -0.0055 0.4355 0.1147
-2.500 -0.1429 0.01018 0.00266 -0.0050 0.3413 0.1152
-2.250 -0.1157 0.01031 0.00263 -0.0047 0.2966 0.1157
-2.000 -0.0879 0.01036 0.00259 -0.0044 0.2713 0.1163
-1.750 -0.0599 0.01039 0.00255 -0.0041 0.2533 0.1170
-1.500 -0.0318 0.01042 0.00253 -0.0039 0.2385 0.1178
-1.250 -0.0034 0.01043 0.00250 -0.0036 0.2290 0.1186
-1.000 0.0248 0.01046 0.00249 -0.0034 0.2194 0.1194
-0.750 0.0533 0.01045 0.00247 -0.0032 0.2136 0.1208
-0.500 0.0815 0.01046 0.00246 -0.0030 0.2065 0.1235
-0.250 0.1097 0.01043 0.00245 -0.0027 0.2007 0.1278
0.000 0.1368 0.01018 0.00241 -0.0025 0.1960 0.1855
0.250 0.1649 0.01018 0.00245 -0.0022 0.1908 0.2000
0.500 0.1932 0.01024 0.00251 -0.0020 0.1859 0.2092
0.750 0.2218 0.01022 0.00255 -0.0019 0.1836 0.2184
1.000 0.2503 0.01023 0.00259 -0.0017 0.1806 0.2276
1.250 0.2787 0.01026 0.00264 -0.0015 0.1773 0.2365
1.500 0.3067 0.01031 0.00271 -0.0013 0.1728 0.2494
1.750 0.3351 0.01031 0.00276 -0.0012 0.1696 0.2634
2.000 0.3635 0.01026 0.00280 -0.0010 0.1665 0.2851
2.250 0.3912 0.01017 0.00284 -0.0009 0.1634 0.3271
2.500 0.4177 0.00993 0.00288 -0.0006 0.1601 0.4240
2.750 0.4439 0.00969 0.00297 -0.0002 0.1571 0.5275
3.000 0.4714 0.00956 0.00307 0.0001 0.1552 0.5978
3.250 0.4994 0.00956 0.00318 0.0003 0.1526 0.6330
3.500 0.5274 0.00963 0.00330 0.0005 0.1495 0.6592
3.750 0.5551 0.00976 0.00345 0.0007 0.1457 0.6796
4.000 0.5837 0.00983 0.00356 0.0009 0.1432 0.6953
4.250 0.6119 0.00990 0.00368 0.0011 0.1400 0.7104
4.500 0.6399 0.01002 0.00380 0.0013 0.1367 0.7228
4.750 0.6678 0.01018 0.00397 0.0015 0.1333 0.7341
5.000 0.6961 0.01026 0.00409 0.0016 0.1306 0.7443
5.250 0.7240 0.01039 0.00423 0.0018 0.1271 0.7561
5.500 0.7515 0.01057 0.00440 0.0020 0.1232 0.7663
5.750 0.7794 0.01068 0.00455 0.0022 0.1203 0.7779
6.000 0.8068 0.01083 0.00472 0.0025 0.1167 0.7890
6.250 0.8341 0.01101 0.00491 0.0027 0.1133 0.8007
6.500 0.8612 0.01113 0.00508 0.0030 0.1100 0.8142
6.750 0.8880 0.01132 0.00528 0.0033 0.1066 0.8276
7.000 0.9147 0.01148 0.00549 0.0037 0.1038 0.8430
7.250 0.9408 0.01161 0.00569 0.0041 0.1011 0.8638
7.500 0.9646 0.01171 0.00592 0.0051 0.0983 0.9064
7.750 1.0060 0.01189 0.00620 0.0024 0.0954 1.0000
8.000 1.0324 0.01213 0.00642 0.0027 0.0931 1.0000
8.250 1.0583 0.01242 0.00668 0.0030 0.0907 1.0000
8.500 1.0843 0.01269 0.00694 0.0034 0.0883 1.0000
8.750 1.1104 0.01295 0.00720 0.0037 0.0861 1.0000
9.000 1.1360 0.01326 0.00749 0.0040 0.0835 1.0000
9.250 1.1616 0.01357 0.00779 0.0043 0.0812 1.0000
9.500 1.1873 0.01385 0.00807 0.0047 0.0786 1.0000
9.750 1.2120 0.01424 0.00843 0.0051 0.0754 1.0000
10.000 1.2373 0.01455 0.00874 0.0054 0.0717 1.0000
10.250 1.2616 0.01496 0.00912 0.0058 0.0671 1.0000
10.500 1.2844 0.01551 0.00960 0.0064 0.0574 1.0000
10.750 1.3004 0.01672 0.01065 0.0076 0.0397 1.0000
11.000 1.3220 0.01735 0.01128 0.0082 0.0379 1.0000
11.250 1.3432 0.01797 0.01192 0.0089 0.0367 1.0000
11.500 1.3639 0.01861 0.01257 0.0097 0.0357 1.0000
11.750 1.3851 0.01916 0.01316 0.0103 0.0353 1.0000
12.000 1.4056 0.01974 0.01378 0.0111 0.0349 1.0000
12.250 1.4250 0.02037 0.01445 0.0119 0.0345 1.0000
12.500 1.4434 0.02105 0.01517 0.0128 0.0342 1.0000
12.750 1.4594 0.02177 0.01594 0.0140 0.0339 1.0000
13.000 1.4730 0.02256 0.01678 0.0154 0.0336 1.0000
13.250 1.4850 0.02346 0.01773 0.0168 0.0334 1.0000
13.500 1.4954 0.02451 0.01884 0.0181 0.0332 1.0000
13.750 1.5043 0.02574 0.02013 0.0192 0.0330 1.0000
14.000 1.5118 0.02720 0.02167 0.0198 0.0328 1.0000
14.250 1.5177 0.02896 0.02350 0.0202 0.0326 1.0000
14.500 1.5218 0.03102 0.02565 0.0201 0.0324 1.0000
14.750 1.5237 0.03342 0.02814 0.0198 0.0323 1.0000
15.000 1.5228 0.03625 0.03107 0.0192 0.0321 1.0000
15.250 1.5179 0.03970 0.03463 0.0181 0.0320 1.0000
15.500 1.5092 0.04378 0.03884 0.0165 0.0320 1.0000
15.750 1.4953 0.04880 0.04400 0.0142 0.0319 1.0000
16.000 1.4730 0.05530 0.05066 0.0109 0.0319 1.0000
16.250 1.4395 0.06396 0.05952 0.0063 0.0319 1.0000
16.500 1.3870 0.07610 0.07192 0.0000 0.0321 1.0000
16.750 1.3197 0.09032 0.08640 -0.0070 0.0323 1.0000
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