BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.34 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737a-il-1000000-n5.txt Download as CSV file: xf-b737a-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -1.3080 0.08881 0.08467 -0.0078 1.0000 0.0220
-18.750 -1.3623 0.07692 0.07255 -0.0140 1.0000 0.0219
-18.500 -1.4073 0.06634 0.06175 -0.0196 1.0000 0.0219
-18.250 -1.4392 0.05799 0.05321 -0.0240 1.0000 0.0219
-18.000 -1.4597 0.05164 0.04671 -0.0272 1.0000 0.0220
-17.750 -1.4722 0.04674 0.04168 -0.0294 1.0000 0.0221
-17.500 -1.4790 0.04281 0.03764 -0.0308 1.0000 0.0223
-17.250 -1.4819 0.03953 0.03427 -0.0318 1.0000 0.0224
-17.000 -1.4814 0.03675 0.03141 -0.0324 1.0000 0.0226
-16.750 -1.4785 0.03434 0.02892 -0.0327 1.0000 0.0228
-16.500 -1.4733 0.03223 0.02673 -0.0328 1.0000 0.0231
-16.250 -1.4663 0.03038 0.02481 -0.0327 1.0000 0.0233
-16.000 -1.4575 0.02875 0.02311 -0.0325 1.0000 0.0235
-15.750 -1.4493 0.02713 0.02143 -0.0321 1.0000 0.0238
-15.500 -1.4394 0.02572 0.01998 -0.0315 1.0000 0.0241
-15.250 -1.4283 0.02451 0.01873 -0.0308 1.0000 0.0245
-15.000 -1.4161 0.02347 0.01764 -0.0299 1.0000 0.0249
-14.750 -1.4030 0.02258 0.01671 -0.0287 1.0000 0.0253
-14.500 -1.3888 0.02182 0.01591 -0.0273 1.0000 0.0257
-14.250 -1.3735 0.02115 0.01521 -0.0258 1.0000 0.0261
-14.000 -1.3560 0.02056 0.01458 -0.0245 1.0000 0.0265
-13.750 -1.3370 0.01997 0.01396 -0.0234 1.0000 0.0270
-13.500 -1.3175 0.01938 0.01335 -0.0224 1.0000 0.0275
-13.250 -1.2968 0.01884 0.01280 -0.0214 1.0000 0.0281
-13.000 -1.2755 0.01834 0.01229 -0.0205 1.0000 0.0288
-12.750 -1.2534 0.01789 0.01181 -0.0196 1.0000 0.0294
-12.500 -1.2307 0.01746 0.01137 -0.0188 1.0000 0.0300
-12.250 -1.2084 0.01699 0.01090 -0.0179 1.0000 0.0308
-12.000 -1.1855 0.01656 0.01046 -0.0170 1.0000 0.0317
-11.750 -1.1622 0.01617 0.01006 -0.0162 1.0000 0.0326
-11.500 -1.1384 0.01580 0.00968 -0.0154 1.0000 0.0334
-11.250 -1.1149 0.01542 0.00929 -0.0146 1.0000 0.0342
-11.000 -1.0913 0.01504 0.00891 -0.0137 1.0000 0.0352
-10.750 -1.0674 0.01469 0.00857 -0.0128 1.0000 0.0362
-10.500 -1.0434 0.01437 0.00824 -0.0120 1.0000 0.0371
-10.250 -1.0196 0.01404 0.00791 -0.0111 1.0000 0.0381
-10.000 -0.9960 0.01370 0.00758 -0.0101 1.0000 0.0393
-9.750 -0.9693 0.01338 0.00726 -0.0097 0.9982 0.0406
-9.500 -0.9357 0.01304 0.00692 -0.0108 0.9902 0.0420
-9.250 -0.9006 0.01266 0.00655 -0.0122 0.9709 0.0440
-9.000 -0.8598 0.01239 0.00613 -0.0145 0.8825 0.0465
-8.750 -0.8357 0.01220 0.00579 -0.0135 0.8422 0.0497
-8.500 -0.8121 0.01166 0.00539 -0.0128 0.8231 0.0817
-8.250 -0.7844 0.01159 0.00530 -0.0124 0.8102 0.0867
-8.000 -0.7567 0.01153 0.00519 -0.0120 0.7962 0.0892
-7.750 -0.7290 0.01146 0.00507 -0.0116 0.7795 0.0906
-7.500 -0.7016 0.01136 0.00493 -0.0112 0.7607 0.0920
-7.250 -0.6740 0.01128 0.00480 -0.0108 0.7421 0.0932
-7.000 -0.6462 0.01121 0.00467 -0.0104 0.7259 0.0942
-6.750 -0.6181 0.01111 0.00455 -0.0101 0.7129 0.0951
-6.500 -0.5900 0.01102 0.00441 -0.0098 0.6998 0.0956
-6.250 -0.5618 0.01095 0.00429 -0.0095 0.6851 0.0962
-6.000 -0.5335 0.01089 0.00419 -0.0092 0.6709 0.0967
-5.750 -0.5058 0.01077 0.00401 -0.0088 0.6518 0.0971
-5.500 -0.4783 0.01065 0.00382 -0.0085 0.6282 0.0978
-5.250 -0.4506 0.01056 0.00366 -0.0081 0.6026 0.0984
-5.000 -0.4229 0.01050 0.00352 -0.0078 0.5741 0.0989
-4.750 -0.3953 0.01047 0.00339 -0.0074 0.5432 0.0994
-4.500 -0.3676 0.01046 0.00328 -0.0071 0.5063 0.0999
-4.250 -0.3405 0.01056 0.00319 -0.0067 0.4439 0.1005
-4.000 -0.3140 0.01075 0.00312 -0.0063 0.3668 0.1010
-3.750 -0.2867 0.01087 0.00307 -0.0059 0.3137 0.1016
-3.500 -0.2588 0.01090 0.00301 -0.0056 0.2859 0.1022
-3.250 -0.2307 0.01090 0.00294 -0.0054 0.2662 0.1025
-3.000 -0.2025 0.01089 0.00287 -0.0051 0.2510 0.1027
-2.750 -0.1743 0.01088 0.00281 -0.0049 0.2372 0.1029
-2.500 -0.1460 0.01086 0.00276 -0.0047 0.2264 0.1031
-2.250 -0.1176 0.01085 0.00271 -0.0044 0.2178 0.1033
-2.000 -0.0891 0.01082 0.00266 -0.0042 0.2113 0.1035
-1.750 -0.0607 0.01082 0.00263 -0.0040 0.2044 0.1037
-1.500 -0.0322 0.01080 0.00259 -0.0038 0.1997 0.1039
-1.250 -0.0037 0.01077 0.00256 -0.0036 0.1946 0.1044
-1.000 0.0247 0.01076 0.00253 -0.0034 0.1892 0.1050
-0.750 0.0532 0.01075 0.00251 -0.0032 0.1850 0.1057
-0.500 0.0817 0.01073 0.00250 -0.0030 0.1814 0.1064
-0.250 0.1101 0.01074 0.00249 -0.0028 0.1765 0.1072
0.000 0.1385 0.01076 0.00249 -0.0026 0.1710 0.1080
0.250 0.1671 0.01076 0.00250 -0.0024 0.1679 0.1090
0.500 0.1957 0.01077 0.00251 -0.0023 0.1649 0.1101
0.750 0.2242 0.01080 0.00253 -0.0021 0.1619 0.1114
1.250 0.2810 0.01082 0.00258 -0.0017 0.1565 0.1190
1.500 0.3082 0.01060 0.00258 -0.0015 0.1539 0.1838
1.750 0.3366 0.01064 0.00263 -0.0013 0.1496 0.1935
2.000 0.3648 0.01070 0.00269 -0.0012 0.1451 0.2017
2.250 0.3933 0.01073 0.00275 -0.0010 0.1429 0.2080
2.500 0.4218 0.01077 0.00282 -0.0009 0.1402 0.2154
2.750 0.4501 0.01084 0.00290 -0.0007 0.1371 0.2218
3.000 0.4782 0.01091 0.00299 -0.0006 0.1339 0.2313
3.250 0.5066 0.01095 0.00307 -0.0004 0.1316 0.2410
3.750 0.5625 0.01102 0.00326 -0.0001 0.1245 0.2832
4.000 0.5900 0.01098 0.00335 0.0000 0.1207 0.3331
4.250 0.6155 0.01056 0.00343 0.0003 0.1163 0.5044
4.500 0.6423 0.01049 0.00357 0.0006 0.1127 0.5824
4.750 0.6699 0.01055 0.00373 0.0008 0.1090 0.6221
5.000 0.6973 0.01068 0.00391 0.0010 0.1050 0.6473
5.250 0.7250 0.01081 0.00408 0.0013 0.1014 0.6683
5.500 0.7523 0.01098 0.00428 0.0015 0.0974 0.6841
5.750 0.7799 0.01115 0.00447 0.0017 0.0942 0.6982
6.000 0.8072 0.01133 0.00467 0.0019 0.0909 0.7120
6.250 0.8344 0.01152 0.00489 0.0021 0.0882 0.7244
6.500 0.8617 0.01172 0.00510 0.0023 0.0854 0.7376
6.750 0.8885 0.01194 0.00534 0.0026 0.0826 0.7489
7.000 0.9158 0.01215 0.00557 0.0028 0.0807 0.7586
7.250 0.9427 0.01234 0.00580 0.0031 0.0785 0.7687
7.500 0.9693 0.01259 0.00606 0.0033 0.0762 0.7801
7.750 0.9957 0.01280 0.00632 0.0036 0.0742 0.7949
8.000 1.0222 0.01302 0.00658 0.0039 0.0717 0.8072
8.250 1.0480 0.01329 0.00687 0.0043 0.0687 0.8204
8.500 1.0735 0.01353 0.00716 0.0047 0.0648 0.8386
9.000 1.1153 0.01475 0.00849 0.0067 0.0347 0.9537
9.250 1.1462 0.01524 0.00898 0.0057 0.0326 1.0000
9.500 1.1705 0.01567 0.00942 0.0062 0.0316 1.0000
9.750 1.1949 0.01607 0.00983 0.0066 0.0310 1.0000
10.000 1.2189 0.01650 0.01028 0.0071 0.0304 1.0000
10.250 1.2424 0.01696 0.01075 0.0076 0.0299 1.0000
10.500 1.2655 0.01745 0.01125 0.0081 0.0294 1.0000
10.750 1.2882 0.01795 0.01177 0.0086 0.0290 1.0000
11.000 1.3103 0.01848 0.01233 0.0092 0.0286 1.0000
11.250 1.3318 0.01904 0.01291 0.0099 0.0283 1.0000
11.500 1.3533 0.01957 0.01346 0.0105 0.0281 1.0000
11.750 1.3743 0.02011 0.01404 0.0112 0.0280 1.0000
12.000 1.3945 0.02068 0.01464 0.0119 0.0278 1.0000
12.250 1.4137 0.02129 0.01529 0.0127 0.0277 1.0000
12.500 1.4312 0.02193 0.01598 0.0138 0.0276 1.0000
12.750 1.4464 0.02262 0.01671 0.0150 0.0274 1.0000
13.000 1.4603 0.02340 0.01754 0.0163 0.0273 1.0000
13.250 1.4729 0.02427 0.01847 0.0175 0.0272 1.0000
13.500 1.4844 0.02528 0.01953 0.0186 0.0271 1.0000
13.750 1.4947 0.02646 0.02077 0.0194 0.0269 1.0000
14.000 1.5039 0.02784 0.02222 0.0199 0.0268 1.0000
14.250 1.5118 0.02945 0.02389 0.0201 0.0267 1.0000
14.500 1.5183 0.03129 0.02581 0.0201 0.0266 1.0000
14.750 1.5231 0.03340 0.02800 0.0198 0.0265 1.0000
15.000 1.5255 0.03586 0.03055 0.0193 0.0265 1.0000
15.250 1.5251 0.03874 0.03353 0.0185 0.0264 1.0000
15.500 1.5212 0.04216 0.03706 0.0172 0.0263 1.0000
15.750 1.5125 0.04636 0.04138 0.0155 0.0263 1.0000
16.000 1.4968 0.05173 0.04690 0.0129 0.0262 1.0000
16.250 1.4688 0.05927 0.05463 0.0090 0.0262 1.0000
16.500 1.4071 0.07280 0.06846 0.0016 0.0263 1.0000
16.750 1.2802 0.09663 0.09273 -0.0103 0.0266 1.0000
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