BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 500,000 Max Cl/Cd: 67.7 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737a-il-500000.txt Download as CSV file: xf-b737a-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.1866 0.08946 0.08451 -0.0080 1.0000 0.0350
-17.750 -1.1902 0.08544 0.08044 -0.0096 1.0000 0.0353
-17.500 -1.1947 0.08127 0.07621 -0.0114 1.0000 0.0356
-17.250 -1.2000 0.07696 0.07184 -0.0132 1.0000 0.0359
-17.000 -1.2062 0.07252 0.06732 -0.0151 1.0000 0.0361
-16.750 -1.2131 0.06797 0.06268 -0.0171 1.0000 0.0364
-16.500 -1.2204 0.06341 0.05803 -0.0192 1.0000 0.0367
-16.250 -1.2269 0.05900 0.05351 -0.0211 1.0000 0.0370
-16.000 -1.2322 0.05477 0.04917 -0.0230 1.0000 0.0373
-15.750 -1.2368 0.05079 0.04509 -0.0247 1.0000 0.0376
-15.500 -1.2463 0.04643 0.04066 -0.0264 1.0000 0.0379
-15.250 -1.2525 0.04259 0.03674 -0.0278 1.0000 0.0382
-15.000 -1.2552 0.03930 0.03337 -0.0287 1.0000 0.0386
-14.750 -1.2550 0.03646 0.03045 -0.0294 1.0000 0.0390
-14.500 -1.2523 0.03400 0.02792 -0.0297 1.0000 0.0395
-14.250 -1.2475 0.03184 0.02568 -0.0298 1.0000 0.0401
-14.000 -1.2403 0.03002 0.02377 -0.0296 1.0000 0.0407
-13.750 -1.2297 0.02857 0.02223 -0.0293 1.0000 0.0414
-13.500 -1.2286 0.02649 0.02010 -0.0285 1.0000 0.0421
-13.250 -1.2228 0.02499 0.01855 -0.0273 1.0000 0.0428
-13.000 -1.2137 0.02386 0.01737 -0.0257 1.0000 0.0437
-12.750 -1.2014 0.02296 0.01641 -0.0240 1.0000 0.0446
-12.500 -1.1843 0.02223 0.01561 -0.0228 1.0000 0.0456
-12.250 -1.1729 0.02099 0.01434 -0.0212 1.0000 0.0468
-12.000 -1.1561 0.02011 0.01342 -0.0199 1.0000 0.0481
-11.750 -1.1367 0.01941 0.01267 -0.0188 1.0000 0.0495
-11.500 -1.1186 0.01854 0.01177 -0.0175 1.0000 0.0512
-11.250 -1.0988 0.01779 0.01098 -0.0164 1.0000 0.0534
-11.000 -1.0793 0.01699 0.01017 -0.0152 1.0000 0.0569
-10.750 -1.0565 0.01647 0.00994 -0.0144 1.0000 0.0862
-10.500 -1.0281 0.01655 0.00999 -0.0140 1.0000 0.0934
-10.250 -1.0005 0.01657 0.00996 -0.0136 1.0000 0.0977
-10.000 -0.9747 0.01645 0.00984 -0.0130 1.0000 0.1012
-9.750 -0.9478 0.01646 0.00977 -0.0124 1.0000 0.1038
-9.500 -0.9256 0.01597 0.00932 -0.0114 1.0000 0.1062
-9.250 -0.9014 0.01572 0.00908 -0.0106 1.0000 0.1085
-9.000 -0.8765 0.01556 0.00888 -0.0098 1.0000 0.1106
-8.750 -0.8529 0.01528 0.00857 -0.0089 1.0000 0.1123
-8.500 -0.8310 0.01480 0.00815 -0.0077 1.0000 0.1141
-8.250 -0.8080 0.01449 0.00786 -0.0066 1.0000 0.1157
-8.000 -0.7845 0.01423 0.00760 -0.0056 1.0000 0.1171
-7.750 -0.7610 0.01400 0.00737 -0.0046 1.0000 0.1183
-7.500 -0.7376 0.01381 0.00717 -0.0035 1.0000 0.1192
-7.250 -0.7078 0.01352 0.00689 -0.0039 0.9976 0.1202
-7.000 -0.6642 0.01302 0.00645 -0.0071 0.9857 0.1217
-6.750 -0.6193 0.01262 0.00608 -0.0104 0.9604 0.1231
-6.500 -0.5729 0.01229 0.00571 -0.0138 0.9139 0.1245
-6.250 -0.5425 0.01215 0.00543 -0.0138 0.8712 0.1255
-6.000 -0.5163 0.01205 0.00522 -0.0131 0.8462 0.1262
-5.750 -0.4897 0.01194 0.00502 -0.0124 0.8278 0.1269
-5.500 -0.4630 0.01183 0.00484 -0.0118 0.8119 0.1275
-5.250 -0.4362 0.01173 0.00467 -0.0112 0.7954 0.1281
-5.000 -0.4095 0.01153 0.00446 -0.0107 0.7802 0.1292
-4.750 -0.3827 0.01134 0.00425 -0.0101 0.7665 0.1307
-4.500 -0.3558 0.01118 0.00405 -0.0096 0.7518 0.1321
-4.250 -0.3283 0.01102 0.00389 -0.0092 0.7380 0.1334
-4.000 -0.3008 0.01091 0.00373 -0.0087 0.7250 0.1343
-3.750 -0.2730 0.01079 0.00359 -0.0083 0.7105 0.1354
-3.500 -0.2453 0.01068 0.00346 -0.0079 0.6952 0.1367
-3.250 -0.2178 0.01057 0.00332 -0.0074 0.6772 0.1390
-3.000 -0.1905 0.01045 0.00319 -0.0069 0.6561 0.1431
-2.750 -0.1638 0.01026 0.00307 -0.0064 0.6314 0.1611
-2.500 -0.1369 0.01018 0.00300 -0.0059 0.5985 0.1872
-2.250 -0.1102 0.01023 0.00293 -0.0053 0.5504 0.1981
-2.000 -0.0850 0.01051 0.00289 -0.0046 0.4583 0.2058
-1.750 -0.0610 0.01097 0.00294 -0.0038 0.3447 0.2133
-1.500 -0.0343 0.01123 0.00300 -0.0034 0.2988 0.2201
-1.250 -0.0070 0.01133 0.00304 -0.0031 0.2756 0.2268
-0.750 0.0486 0.01151 0.00313 -0.0025 0.2487 0.2394
-0.500 0.0759 0.01159 0.00319 -0.0022 0.2384 0.2471
-0.250 0.1041 0.01162 0.00323 -0.0020 0.2320 0.2550
0.000 0.1318 0.01167 0.00328 -0.0017 0.2254 0.2637
0.250 0.1593 0.01175 0.00337 -0.0014 0.2188 0.2737
0.500 0.1873 0.01171 0.00340 -0.0012 0.2136 0.2878
0.750 0.2147 0.01170 0.00344 -0.0009 0.2081 0.3088
1.000 0.2410 0.01171 0.00355 -0.0005 0.2024 0.3487
1.250 0.2669 0.01131 0.00356 -0.0001 0.1995 0.4544
1.500 0.2925 0.01103 0.00366 0.0004 0.1959 0.5565
1.750 0.3191 0.01102 0.00383 0.0009 0.1923 0.6135
2.000 0.3460 0.01118 0.00402 0.0014 0.1884 0.6458
2.250 0.3733 0.01134 0.00424 0.0018 0.1851 0.6691
2.500 0.4012 0.01141 0.00438 0.0021 0.1823 0.6880
2.750 0.4290 0.01149 0.00452 0.0024 0.1787 0.7039
3.000 0.4566 0.01164 0.00465 0.0027 0.1747 0.7193
3.250 0.4834 0.01188 0.00489 0.0032 0.1706 0.7344
3.500 0.5114 0.01193 0.00501 0.0035 0.1675 0.7476
3.750 0.5394 0.01205 0.00514 0.0037 0.1643 0.7596
4.000 0.5664 0.01218 0.00530 0.0041 0.1611 0.7708
4.250 0.5930 0.01249 0.00557 0.0045 0.1574 0.7823
4.500 0.6205 0.01253 0.00571 0.0049 0.1548 0.7942
4.750 0.6480 0.01262 0.00585 0.0052 0.1515 0.8066
5.000 0.6748 0.01275 0.00600 0.0056 0.1482 0.8193
5.250 0.7004 0.01300 0.00626 0.0062 0.1448 0.8330
5.500 0.7273 0.01305 0.00641 0.0066 0.1420 0.8482
5.750 0.7537 0.01313 0.00656 0.0071 0.1388 0.8646
6.000 0.7788 0.01326 0.00673 0.0079 0.1357 0.8864
6.250 0.8039 0.01342 0.00700 0.0087 0.1327 0.9216
6.500 0.8442 0.01358 0.00723 0.0063 0.1293 0.9711
6.750 0.8809 0.01381 0.00744 0.0044 0.1259 1.0000
7.000 0.9060 0.01415 0.00771 0.0048 0.1230 1.0000
7.250 0.9325 0.01436 0.00795 0.0051 0.1207 1.0000
7.500 0.9586 0.01461 0.00819 0.0054 0.1183 1.0000
7.750 0.9843 0.01489 0.00845 0.0057 0.1160 1.0000
8.000 1.0088 0.01530 0.00880 0.0062 0.1138 1.0000
8.250 1.0349 0.01555 0.00910 0.0065 0.1120 1.0000
8.500 1.0605 0.01583 0.00941 0.0068 0.1100 1.0000
8.750 1.0859 0.01613 0.00971 0.0072 0.1080 1.0000
9.000 1.1103 0.01650 0.01004 0.0076 0.1059 1.0000
9.250 1.1348 0.01687 0.01043 0.0080 0.1041 1.0000
9.500 1.1600 0.01717 0.01078 0.0084 0.1024 1.0000
9.750 1.1847 0.01750 0.01113 0.0087 0.1005 1.0000
10.000 1.2087 0.01788 0.01150 0.0092 0.0986 1.0000
10.250 1.2312 0.01836 0.01197 0.0097 0.0968 1.0000
10.500 1.2558 0.01866 0.01234 0.0101 0.0948 1.0000
10.750 1.2795 0.01903 0.01275 0.0106 0.0928 1.0000
11.000 1.3021 0.01947 0.01319 0.0111 0.0907 1.0000
11.250 1.3235 0.01997 0.01370 0.0118 0.0887 1.0000
11.500 1.3465 0.02035 0.01414 0.0123 0.0862 1.0000
11.750 1.3674 0.02085 0.01464 0.0129 0.0832 1.0000
12.000 1.3878 0.02138 0.01520 0.0136 0.0806 1.0000
12.250 1.4077 0.02191 0.01577 0.0144 0.0775 1.0000
12.500 1.4241 0.02256 0.01644 0.0155 0.0745 1.0000
12.750 1.4411 0.02318 0.01711 0.0166 0.0708 1.0000
13.000 1.4560 0.02395 0.01790 0.0177 0.0668 1.0000
13.250 1.4690 0.02488 0.01885 0.0187 0.0617 1.0000
13.500 1.4791 0.02606 0.02003 0.0198 0.0554 1.0000
13.750 1.4856 0.02762 0.02159 0.0206 0.0505 1.0000
14.000 1.4902 0.02947 0.02347 0.0210 0.0478 1.0000
14.250 1.4939 0.03153 0.02559 0.0212 0.0464 1.0000
14.500 1.4958 0.03389 0.02803 0.0210 0.0453 1.0000
14.750 1.4948 0.03667 0.03090 0.0205 0.0445 1.0000
15.000 1.4908 0.03994 0.03427 0.0196 0.0439 1.0000
15.250 1.4844 0.04365 0.03810 0.0183 0.0435 1.0000
15.500 1.4748 0.04797 0.04255 0.0164 0.0432 1.0000
15.750 1.4588 0.05337 0.04811 0.0139 0.0431 1.0000
16.000 1.4341 0.06040 0.05532 0.0102 0.0430 1.0000
16.250 1.3952 0.07006 0.06521 0.0050 0.0430 1.0000
16.500 1.3395 0.08258 0.07799 -0.0015 0.0432 1.0000
16.750 1.2829 0.09513 0.09075 -0.0079 0.0434 1.0000
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