BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 200,000 Max Cl/Cd: 51 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737b-il-200000-n5.txt Download as CSV file: xf-b737b-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8418 0.10418 0.09982 -0.0024 1.0000 0.0213
-14.750 -0.8868 0.09009 0.08551 -0.0121 1.0000 0.0211
-14.500 -0.9194 0.07971 0.07490 -0.0195 1.0000 0.0210
-14.250 -0.9456 0.07141 0.06637 -0.0253 1.0000 0.0210
-14.000 -0.9672 0.06452 0.05924 -0.0299 1.0000 0.0210
-13.750 -0.9850 0.05875 0.05322 -0.0333 1.0000 0.0210
-13.500 -0.9996 0.05386 0.04808 -0.0356 1.0000 0.0211
-13.250 -1.0112 0.04971 0.04367 -0.0369 1.0000 0.0212
-13.000 -1.0200 0.04622 0.03991 -0.0372 1.0000 0.0214
-12.750 -1.0263 0.04327 0.03666 -0.0367 1.0000 0.0216
-12.500 -1.0270 0.04092 0.03411 -0.0355 1.0000 0.0217
-12.250 -1.0213 0.03914 0.03225 -0.0341 1.0000 0.0220
-12.000 -1.0143 0.03757 0.03059 -0.0326 1.0000 0.0222
-11.750 -1.0047 0.03608 0.02900 -0.0312 1.0000 0.0225
-11.500 -0.9928 0.03468 0.02749 -0.0299 1.0000 0.0229
-11.250 -0.9795 0.03334 0.02602 -0.0287 1.0000 0.0234
-11.000 -0.9650 0.03201 0.02455 -0.0275 1.0000 0.0240
-10.750 -0.9494 0.03068 0.02304 -0.0263 1.0000 0.0247
-10.500 -0.9327 0.02938 0.02153 -0.0250 1.0000 0.0253
-10.250 -0.9150 0.02811 0.02019 -0.0239 1.0000 0.0259
-10.000 -0.8965 0.02701 0.01908 -0.0229 1.0000 0.0264
-9.750 -0.8774 0.02602 0.01805 -0.0219 1.0000 0.0269
-9.500 -0.8581 0.02505 0.01703 -0.0208 1.0000 0.0276
-9.250 -0.8385 0.02411 0.01602 -0.0197 1.0000 0.0283
-9.000 -0.8184 0.02325 0.01507 -0.0185 1.0000 0.0293
-8.750 -0.7986 0.02238 0.01415 -0.0174 1.0000 0.0303
-8.500 -0.7789 0.02158 0.01337 -0.0162 1.0000 0.0312
-8.250 -0.7587 0.02085 0.01263 -0.0151 1.0000 0.0324
-8.000 -0.7385 0.02013 0.01187 -0.0139 1.0000 0.0335
-7.750 -0.7180 0.01945 0.01113 -0.0126 1.0000 0.0346
-7.500 -0.6985 0.01872 0.01041 -0.0113 1.0000 0.0358
-7.250 -0.6779 0.01812 0.00982 -0.0101 1.0000 0.0375
-7.000 -0.6569 0.01758 0.00924 -0.0089 1.0000 0.0395
-6.750 -0.6363 0.01699 0.00865 -0.0077 1.0000 0.0414
-6.500 -0.6152 0.01645 0.00810 -0.0065 1.0000 0.0437
-6.250 -0.5935 0.01600 0.00762 -0.0054 1.0000 0.0466
-6.000 -0.5723 0.01548 0.00713 -0.0042 1.0000 0.0505
-5.750 -0.5507 0.01502 0.00668 -0.0031 1.0000 0.0559
-5.500 -0.5155 0.01443 0.00615 -0.0049 0.9935 0.0675
-5.250 -0.4802 0.01356 0.00558 -0.0069 0.9839 0.1101
-5.000 -0.4470 0.01276 0.00516 -0.0085 0.9715 0.1831
-4.750 -0.4136 0.01224 0.00487 -0.0099 0.9564 0.2341
-4.500 -0.3791 0.01186 0.00462 -0.0112 0.9390 0.2727
-4.250 -0.3445 0.01147 0.00437 -0.0126 0.9187 0.3126
-4.000 -0.3109 0.01105 0.00415 -0.0138 0.8950 0.3617
-3.750 -0.2794 0.01064 0.00399 -0.0144 0.8706 0.4248
-3.500 -0.2502 0.01042 0.00388 -0.0143 0.8458 0.4709
-3.250 -0.2217 0.01033 0.00375 -0.0140 0.8231 0.4974
-3.000 -0.1944 0.01027 0.00365 -0.0135 0.8024 0.5196
-2.750 -0.1676 0.01024 0.00357 -0.0129 0.7829 0.5404
-2.500 -0.1413 0.01022 0.00350 -0.0122 0.7602 0.5604
-2.250 -0.1152 0.01023 0.00343 -0.0114 0.7354 0.5798
-2.000 -0.0889 0.01024 0.00337 -0.0107 0.7130 0.5981
-1.750 -0.0623 0.01024 0.00332 -0.0101 0.6949 0.6155
-1.500 -0.0354 0.01024 0.00328 -0.0096 0.6781 0.6316
-1.250 -0.0085 0.01024 0.00325 -0.0091 0.6619 0.6471
-1.000 0.0185 0.01024 0.00322 -0.0086 0.6458 0.6621
-0.750 0.0454 0.01025 0.00320 -0.0081 0.6297 0.6769
-0.500 0.0722 0.01025 0.00319 -0.0075 0.6131 0.6915
-0.250 0.0990 0.01026 0.00319 -0.0070 0.5965 0.7062
0.000 0.1257 0.01029 0.00319 -0.0065 0.5793 0.7214
0.250 0.1523 0.01032 0.00321 -0.0059 0.5616 0.7375
0.500 0.1788 0.01035 0.00323 -0.0053 0.5424 0.7548
0.750 0.2050 0.01038 0.00328 -0.0046 0.5211 0.7743
1.000 0.2304 0.01044 0.00333 -0.0038 0.4975 0.7985
1.250 0.2558 0.01051 0.00339 -0.0029 0.4718 0.8242
1.500 0.2816 0.01063 0.00347 -0.0020 0.4448 0.8477
1.750 0.3082 0.01078 0.00356 -0.0015 0.4148 0.8694
2.000 0.3358 0.01098 0.00365 -0.0012 0.3830 0.8909
2.250 0.3647 0.01122 0.00378 -0.0012 0.3515 0.9118
2.500 0.3958 0.01150 0.00392 -0.0018 0.3237 0.9303
2.750 0.4291 0.01178 0.00409 -0.0029 0.2991 0.9470
3.000 0.4633 0.01207 0.00428 -0.0043 0.2781 0.9619
3.250 0.4984 0.01236 0.00447 -0.0059 0.2604 0.9750
3.500 0.5342 0.01264 0.00468 -0.0077 0.2443 0.9867
3.750 0.5709 0.01293 0.00490 -0.0098 0.2294 0.9969
4.000 0.5981 0.01320 0.00511 -0.0099 0.2180 1.0000
4.250 0.6205 0.01350 0.00533 -0.0089 0.2077 1.0000
4.500 0.6436 0.01375 0.00557 -0.0081 0.1979 1.0000
4.750 0.6664 0.01407 0.00583 -0.0073 0.1891 1.0000
5.000 0.6900 0.01436 0.00610 -0.0065 0.1806 1.0000
5.250 0.7133 0.01470 0.00640 -0.0058 0.1730 1.0000
5.500 0.7372 0.01501 0.00670 -0.0051 0.1654 1.0000
5.750 0.7607 0.01539 0.00704 -0.0044 0.1590 1.0000
6.000 0.7849 0.01572 0.00739 -0.0039 0.1526 1.0000
6.250 0.8084 0.01613 0.00776 -0.0032 0.1468 1.0000
6.500 0.8325 0.01650 0.00815 -0.0027 0.1416 1.0000
6.750 0.8565 0.01688 0.00856 -0.0021 0.1363 1.0000
7.250 0.9036 0.01775 0.00945 -0.0009 0.1271 1.0000
7.500 0.9272 0.01818 0.00991 -0.0004 0.1225 1.0000
7.750 0.9496 0.01873 0.01041 0.0003 0.1182 1.0000
8.000 0.9734 0.01914 0.01091 0.0008 0.1140 1.0000
8.250 0.9966 0.01960 0.01142 0.0013 0.1095 1.0000
8.500 1.0182 0.02019 0.01197 0.0020 0.1055 1.0000
8.750 1.0413 0.02066 0.01254 0.0025 0.1017 1.0000
9.000 1.0636 0.02117 0.01312 0.0031 0.0977 1.0000
9.250 1.0844 0.02179 0.01373 0.0039 0.0943 1.0000
9.500 1.1060 0.02236 0.01439 0.0045 0.0909 1.0000
9.750 1.1272 0.02294 0.01506 0.0052 0.0872 1.0000
10.000 1.1468 0.02360 0.01573 0.0060 0.0841 1.0000
10.250 1.1661 0.02430 0.01650 0.0068 0.0810 1.0000
10.500 1.1855 0.02496 0.01727 0.0076 0.0777 1.0000
10.750 1.2031 0.02571 0.01806 0.0086 0.0747 1.0000
11.000 1.2192 0.02655 0.01896 0.0096 0.0720 1.0000
11.250 1.2355 0.02737 0.01991 0.0107 0.0692 1.0000
11.500 1.2484 0.02825 0.02085 0.0121 0.0666 1.0000
11.750 1.2580 0.02933 0.02196 0.0136 0.0646 1.0000
12.000 1.2696 0.03040 0.02317 0.0148 0.0622 1.0000
12.250 1.2793 0.03162 0.02450 0.0159 0.0600 1.0000
12.500 1.2866 0.03306 0.02601 0.0168 0.0582 1.0000
12.750 1.2910 0.03485 0.02784 0.0175 0.0568 1.0000
13.000 1.2977 0.03666 0.02982 0.0178 0.0551 1.0000
13.250 1.3024 0.03873 0.03203 0.0178 0.0535 1.0000
13.500 1.3054 0.04108 0.03449 0.0175 0.0520 1.0000
13.750 1.3062 0.04380 0.03729 0.0169 0.0509 1.0000
14.000 1.3042 0.04693 0.04048 0.0159 0.0499 1.0000
14.250 1.3032 0.05012 0.04384 0.0149 0.0488 1.0000
14.500 1.3000 0.05367 0.04755 0.0136 0.0478 1.0000
14.750 1.2947 0.05758 0.05161 0.0120 0.0469 1.0000
15.000 1.2874 0.06186 0.05602 0.0101 0.0461 1.0000
15.250 1.2782 0.06651 0.06080 0.0080 0.0454 1.0000
15.500 1.2675 0.07149 0.06589 0.0056 0.0448 1.0000
15.750 1.2556 0.07672 0.07121 0.0031 0.0442 1.0000
16.000 1.2437 0.08212 0.07669 0.0005 0.0437 1.0000
16.250 1.2291 0.08820 0.08292 -0.0026 0.0432 1.0000
16.500 1.2114 0.09509 0.08998 -0.0062 0.0427 1.0000
16.750 1.1915 0.10253 0.09760 -0.0102 0.0422 1.0000
17.000 1.1692 0.11061 0.10584 -0.0145 0.0417 1.0000
17.250 1.1439 0.11953 0.11493 -0.0194 0.0412 1.0000
17.500 1.1109 0.13031 0.12588 -0.0254 0.0407 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING 737 MIDSPAN AIRFOIL (b737b-il)