BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 200,000 Max Cl/Cd: 38.53 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737a-il-200000.txt Download as CSV file: xf-b737a-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2447 0.10035 0.09407 -0.0183 1.0000 0.0494
-19.500 -1.2556 0.09498 0.08852 -0.0215 1.0000 0.0495
-19.250 -1.2646 0.09003 0.08339 -0.0243 1.0000 0.0497
-19.000 -1.2731 0.08528 0.07847 -0.0269 1.0000 0.0498
-18.750 -1.2231 0.09026 0.08379 -0.0194 1.0000 0.0509
-18.500 -1.2100 0.08923 0.08279 -0.0184 1.0000 0.0515
-18.250 -1.2022 0.08722 0.08078 -0.0182 1.0000 0.0521
-18.000 -1.1982 0.08456 0.07806 -0.0187 1.0000 0.0526
-17.750 -1.1959 0.08157 0.07501 -0.0194 1.0000 0.0532
-17.500 -1.1950 0.07836 0.07171 -0.0204 1.0000 0.0537
-17.250 -1.1966 0.07470 0.06794 -0.0218 1.0000 0.0541
-17.000 -1.1788 0.07509 0.06855 -0.0191 1.0000 0.0552
-16.750 -1.1761 0.07259 0.06611 -0.0193 1.0000 0.0560
-16.500 -1.1801 0.06886 0.06235 -0.0205 1.0000 0.0567
-16.250 -1.1872 0.06460 0.05804 -0.0222 1.0000 0.0573
-16.000 -1.1954 0.06018 0.05352 -0.0241 1.0000 0.0579
-15.750 -1.2037 0.05577 0.04900 -0.0259 1.0000 0.0584
-15.500 -1.2130 0.05141 0.04456 -0.0277 1.0000 0.0590
-15.250 -1.2242 0.04699 0.04008 -0.0294 1.0000 0.0596
-15.000 -1.2336 0.04298 0.03599 -0.0308 1.0000 0.0603
-14.750 -1.2402 0.03950 0.03242 -0.0316 1.0000 0.0611
-14.500 -1.2437 0.03651 0.02934 -0.0320 1.0000 0.0622
-14.250 -1.2449 0.03391 0.02667 -0.0319 1.0000 0.0636
-14.000 -1.2448 0.03160 0.02435 -0.0316 1.0000 0.0655
-13.500 -1.2265 0.02900 0.02200 -0.0303 1.0000 0.0753
-13.250 -1.2061 0.02853 0.02131 -0.0294 1.0000 0.0897
-13.000 -1.1891 0.02801 0.02055 -0.0284 1.0000 0.0966
-12.750 -1.1770 0.02732 0.01979 -0.0268 1.0000 0.1016
-12.500 -1.1622 0.02663 0.01899 -0.0254 1.0000 0.1062
-12.250 -1.1460 0.02604 0.01823 -0.0242 1.0000 0.1109
-12.000 -1.1287 0.02527 0.01749 -0.0230 1.0000 0.1152
-11.750 -1.1108 0.02475 0.01678 -0.0218 1.0000 0.1197
-11.500 -1.0913 0.02395 0.01610 -0.0208 1.0000 0.1238
-11.250 -1.0712 0.02346 0.01546 -0.0198 1.0000 0.1278
-11.000 -1.0505 0.02275 0.01485 -0.0189 1.0000 0.1315
-10.750 -1.0291 0.02227 0.01433 -0.0179 1.0000 0.1355
-10.500 -1.0071 0.02173 0.01377 -0.0171 1.0000 0.1386
-10.250 -0.9847 0.02127 0.01335 -0.0162 1.0000 0.1417
-10.000 -0.9616 0.02087 0.01290 -0.0154 1.0000 0.1446
-9.750 -0.9385 0.02042 0.01243 -0.0145 1.0000 0.1472
-9.500 -0.9152 0.02003 0.01209 -0.0137 1.0000 0.1498
-9.250 -0.8915 0.01970 0.01174 -0.0129 1.0000 0.1524
-9.000 -0.8676 0.01935 0.01134 -0.0121 1.0000 0.1550
-8.750 -0.8439 0.01896 0.01096 -0.0112 1.0000 0.1570
-8.500 -0.8202 0.01861 0.01066 -0.0103 1.0000 0.1590
-8.250 -0.7964 0.01829 0.01035 -0.0094 1.0000 0.1610
-8.000 -0.7727 0.01797 0.01002 -0.0085 1.0000 0.1631
-7.750 -0.7490 0.01763 0.00966 -0.0076 1.0000 0.1650
-7.500 -0.7259 0.01729 0.00933 -0.0066 1.0000 0.1668
-7.250 -0.7033 0.01697 0.00909 -0.0055 1.0000 0.1689
-7.000 -0.6810 0.01670 0.00886 -0.0044 1.0000 0.1711
-6.750 -0.6595 0.01643 0.00862 -0.0032 1.0000 0.1733
-6.500 -0.6406 0.01620 0.00841 -0.0017 1.0000 0.1757
-6.250 -0.6272 0.01604 0.00827 0.0005 1.0000 0.1779
-6.000 -0.5855 0.01579 0.00812 -0.0024 0.9930 0.1819
-5.750 -0.5350 0.01549 0.00784 -0.0067 0.9816 0.1876
-5.500 -0.4868 0.01507 0.00751 -0.0104 0.9675 0.1934
-5.250 -0.4436 0.01471 0.00721 -0.0131 0.9510 0.2009
-5.000 -0.4039 0.01435 0.00691 -0.0150 0.9321 0.2098
-4.750 -0.3670 0.01412 0.00665 -0.0162 0.9113 0.2209
-4.500 -0.3349 0.01386 0.00644 -0.0165 0.8881 0.2313
-4.250 -0.3065 0.01373 0.00625 -0.0159 0.8653 0.2408
-4.000 -0.2804 0.01364 0.00613 -0.0150 0.8448 0.2496
-3.750 -0.2539 0.01361 0.00602 -0.0141 0.8272 0.2574
-3.500 -0.2283 0.01348 0.00591 -0.0132 0.8108 0.2650
-3.250 -0.2020 0.01346 0.00581 -0.0123 0.7941 0.2727
-3.000 -0.1762 0.01333 0.00569 -0.0114 0.7759 0.2798
-2.750 -0.1503 0.01319 0.00558 -0.0105 0.7574 0.2865
-2.500 -0.1239 0.01311 0.00545 -0.0097 0.7382 0.2933
-2.250 -0.0981 0.01296 0.00531 -0.0088 0.7170 0.3010
-2.000 -0.0723 0.01281 0.00516 -0.0078 0.6917 0.3091
-1.750 -0.0466 0.01272 0.00498 -0.0068 0.6598 0.3173
-1.500 -0.0221 0.01257 0.00479 -0.0056 0.6124 0.3271
-1.250 0.0008 0.01266 0.00457 -0.0042 0.5183 0.3393
-1.000 0.0204 0.01312 0.00449 -0.0026 0.3865 0.3567
-0.500 0.0667 0.01330 0.00468 -0.0008 0.3156 0.4438
-0.250 0.0886 0.01325 0.00493 0.0005 0.3007 0.5416
0.000 0.1131 0.01332 0.00525 0.0016 0.2892 0.6147
0.250 0.1382 0.01368 0.00557 0.0025 0.2791 0.6546
0.500 0.1646 0.01387 0.00583 0.0033 0.2709 0.6836
0.750 0.1906 0.01416 0.00610 0.0041 0.2635 0.7064
1.000 0.2166 0.01454 0.00643 0.0049 0.2568 0.7248
1.250 0.2434 0.01474 0.00667 0.0055 0.2504 0.7418
1.500 0.2696 0.01500 0.00689 0.0063 0.2442 0.7578
1.750 0.2952 0.01543 0.00727 0.0071 0.2381 0.7717
2.000 0.3216 0.01558 0.00750 0.0078 0.2329 0.7863
2.250 0.3475 0.01581 0.00773 0.0086 0.2277 0.8021
2.500 0.3723 0.01609 0.00801 0.0097 0.2230 0.8175
2.750 0.3971 0.01649 0.00843 0.0107 0.2186 0.8331
3.000 0.4222 0.01664 0.00869 0.0117 0.2142 0.8486
3.250 0.4471 0.01684 0.00891 0.0127 0.2097 0.8641
3.500 0.4714 0.01710 0.00917 0.0138 0.2056 0.8800
3.750 0.4962 0.01762 0.00970 0.0148 0.2016 0.8976
4.000 0.5229 0.01782 0.01003 0.0156 0.1977 0.9170
4.250 0.5543 0.01812 0.01038 0.0153 0.1933 0.9365
4.500 0.5913 0.01854 0.01073 0.0137 0.1890 0.9543
4.750 0.6311 0.01923 0.01142 0.0113 0.1844 0.9697
5.000 0.6728 0.01957 0.01184 0.0085 0.1793 0.9834
5.250 0.7169 0.01993 0.01213 0.0051 0.1746 0.9946
5.500 0.7457 0.02066 0.01274 0.0042 0.1711 1.0000
5.750 0.7606 0.02090 0.01307 0.0060 0.1683 1.0000
6.000 0.7827 0.02126 0.01347 0.0068 0.1648 1.0000
6.250 0.8069 0.02160 0.01377 0.0073 0.1618 1.0000
6.500 0.8322 0.02203 0.01408 0.0076 0.1591 1.0000
6.750 0.8566 0.02279 0.01485 0.0079 0.1565 1.0000
7.000 0.8804 0.02335 0.01553 0.0085 0.1539 1.0000
7.250 0.9046 0.02391 0.01616 0.0090 0.1514 1.0000
7.500 0.9294 0.02437 0.01662 0.0093 0.1491 1.0000
7.750 0.9548 0.02478 0.01696 0.0096 0.1470 1.0000
8.000 0.9801 0.02563 0.01771 0.0097 0.1450 1.0000
8.250 1.0019 0.02630 0.01859 0.0104 0.1430 1.0000
8.500 1.0242 0.02705 0.01947 0.0110 0.1410 1.0000
8.750 1.0469 0.02771 0.02021 0.0116 0.1390 1.0000
9.000 1.0703 0.02823 0.02076 0.0120 0.1372 1.0000
9.250 1.0951 0.02861 0.02107 0.0123 0.1355 1.0000
9.500 1.1203 0.02932 0.02166 0.0124 0.1337 1.0000
9.750 1.1380 0.03019 0.02279 0.0134 0.1319 1.0000
10.000 1.1567 0.03109 0.02387 0.0142 0.1300 1.0000
10.250 1.1762 0.03184 0.02473 0.0149 0.1282 1.0000
10.500 1.1975 0.03232 0.02523 0.0155 0.1265 1.0000
10.750 1.2217 0.03247 0.02530 0.0158 0.1248 1.0000
11.000 1.2448 0.03306 0.02582 0.0161 0.1231 1.0000
11.250 1.2559 0.03425 0.02729 0.0175 0.1213 1.0000
11.500 1.2681 0.03531 0.02854 0.0187 0.1194 1.0000
11.750 1.2837 0.03584 0.02915 0.0197 0.1174 1.0000
12.000 1.3050 0.03588 0.02911 0.0203 0.1155 1.0000
12.250 1.3300 0.03603 0.02909 0.0206 0.1138 1.0000
12.500 1.3264 0.03759 0.03098 0.0230 0.1120 1.0000
12.750 1.3256 0.03903 0.03263 0.0248 0.1101 1.0000
13.000 1.3326 0.03999 0.03366 0.0258 0.1082 1.0000
13.250 1.3497 0.04022 0.03381 0.0263 0.1062 1.0000
13.500 1.3588 0.04129 0.03489 0.0268 0.1044 1.0000
13.750 1.3457 0.04438 0.03829 0.0268 0.1024 1.0000
14.000 1.3439 0.04670 0.04075 0.0263 0.1001 1.0000
14.250 1.3584 0.04740 0.04135 0.0262 0.0978 1.0000
14.500 1.3531 0.05043 0.04451 0.0251 0.0956 1.0000
14.750 1.3329 0.05556 0.04991 0.0226 0.0934 1.0000
15.000 1.3323 0.05845 0.05283 0.0211 0.0908 1.0000
15.250 1.3318 0.06142 0.05578 0.0196 0.0885 1.0000
15.500 1.2854 0.07139 0.06612 0.0136 0.0867 1.0000
16.000 1.2787 0.07901 0.07368 0.0094 0.0819 1.0000
16.250 0.7613 0.20387 0.19957 -0.0566 0.0890 1.0000
16.500 0.7454 0.20987 0.20558 -0.0641 0.0869 1.0000
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