BOEING 737 MIDSPAN AIRFOIL (b737c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737c-il) Reynolds number: 50,000 Max Cl/Cd: 34.1 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737c-il-50000-n5.txt Download as CSV file: xf-b737c-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5570 0.09767 0.09121 -0.0169 1.0000 0.1318
-8.500 -0.5425 0.09408 0.08762 -0.0146 1.0000 0.1376
-8.250 -0.5681 0.08984 0.08350 -0.0206 1.0000 0.1464
-8.000 -0.5531 0.08620 0.07988 -0.0185 1.0000 0.1531
-7.500 -0.4928 0.06058 0.05413 -0.0325 1.0000 0.0576
-7.250 -0.5520 0.06778 0.06070 -0.0293 1.0000 0.0574
-7.000 -0.5462 0.06375 0.05656 -0.0289 1.0000 0.0540
-6.750 -0.5439 0.06078 0.05273 -0.0275 1.0000 0.0475
-6.500 -0.5320 0.05646 0.04848 -0.0268 1.0000 0.0463
-6.250 -0.5218 0.05302 0.04488 -0.0256 1.0000 0.0454
-6.000 -0.5105 0.04985 0.04141 -0.0242 1.0000 0.0445
-5.750 -0.4979 0.04686 0.03814 -0.0227 1.0000 0.0437
-5.500 -0.4838 0.04405 0.03501 -0.0210 1.0000 0.0430
-5.250 -0.4681 0.04142 0.03203 -0.0194 1.0000 0.0426
-5.000 -0.4509 0.03905 0.02930 -0.0178 1.0000 0.0431
-4.750 -0.4323 0.03693 0.02678 -0.0162 1.0000 0.0443
-4.500 -0.4122 0.03497 0.02443 -0.0146 1.0000 0.0455
-4.250 -0.3910 0.03308 0.02220 -0.0132 1.0000 0.0460
-4.000 -0.3688 0.03125 0.02010 -0.0118 1.0000 0.0463
-3.750 -0.3458 0.02963 0.01818 -0.0106 1.0000 0.0468
-3.500 -0.3224 0.02815 0.01655 -0.0094 1.0000 0.0479
-3.250 -0.3004 0.02673 0.01520 -0.0084 1.0000 0.0516
-3.000 -0.2787 0.02572 0.01411 -0.0071 1.0000 0.0552
-2.750 -0.2581 0.02483 0.01308 -0.0056 1.0000 0.0576
-2.500 -0.2394 0.02414 0.01219 -0.0041 1.0000 0.0600
-2.250 -0.2038 0.02299 0.01092 -0.0064 0.9908 0.0658
-2.000 -0.1655 0.02205 0.00979 -0.0091 0.9796 0.0779
-1.750 -0.1283 0.02068 0.00871 -0.0118 0.9687 0.1363
-1.500 -0.1091 0.01813 0.00924 -0.0077 0.9638 0.8186
-1.250 -0.0300 0.01850 0.00928 -0.0151 0.9678 0.9708
-1.000 0.0429 0.01845 0.00883 -0.0247 0.9649 1.0000
-0.750 0.0840 0.01845 0.00856 -0.0284 0.9506 1.0000
-0.500 0.1205 0.01847 0.00838 -0.0311 0.9355 1.0000
-0.250 0.1541 0.01852 0.00827 -0.0330 0.9210 1.0000
0.000 0.1857 0.01858 0.00819 -0.0345 0.9064 1.0000
0.250 0.2161 0.01865 0.00814 -0.0355 0.8928 1.0000
0.500 0.2457 0.01875 0.00814 -0.0364 0.8806 1.0000
0.750 0.2724 0.01888 0.00819 -0.0366 0.8678 1.0000
1.000 0.2993 0.01899 0.00825 -0.0367 0.8549 1.0000
1.250 0.3262 0.01909 0.00829 -0.0367 0.8420 1.0000
1.500 0.3530 0.01917 0.00834 -0.0365 0.8285 1.0000
1.750 0.3790 0.01926 0.00841 -0.0361 0.8153 1.0000
2.000 0.4043 0.01940 0.00856 -0.0356 0.8026 1.0000
2.250 0.4293 0.01955 0.00872 -0.0350 0.7902 1.0000
2.500 0.4540 0.01971 0.00889 -0.0343 0.7772 1.0000
2.750 0.4785 0.01985 0.00907 -0.0334 0.7630 1.0000
3.000 0.5028 0.01998 0.00927 -0.0323 0.7474 1.0000
3.250 0.5277 0.02010 0.00941 -0.0312 0.7307 1.0000
3.500 0.5516 0.02024 0.00960 -0.0299 0.7128 1.0000
3.750 0.5740 0.02045 0.00987 -0.0285 0.6932 1.0000
4.000 0.5975 0.02062 0.01011 -0.0271 0.6737 1.0000
4.250 0.6201 0.02083 0.01045 -0.0257 0.6529 1.0000
4.500 0.6421 0.02104 0.01076 -0.0241 0.6304 1.0000
4.750 0.6640 0.02125 0.01107 -0.0225 0.6065 1.0000
5.000 0.6862 0.02142 0.01133 -0.0209 0.5808 1.0000
5.250 0.7059 0.02167 0.01176 -0.0191 0.5489 1.0000
5.500 0.7221 0.02196 0.01236 -0.0171 0.5011 1.0000
5.750 0.7420 0.02187 0.01208 -0.0147 0.4579 1.0000
6.000 0.7607 0.02231 0.01233 -0.0126 0.4111 1.0000
6.250 0.7782 0.02304 0.01289 -0.0108 0.3630 1.0000
6.500 0.7949 0.02397 0.01370 -0.0090 0.3183 1.0000
6.750 0.8110 0.02502 0.01466 -0.0074 0.2771 1.0000
7.000 0.8265 0.02618 0.01572 -0.0059 0.2390 1.0000
7.250 0.8408 0.02746 0.01687 -0.0043 0.2047 1.0000
7.500 0.8549 0.02883 0.01814 -0.0028 0.1737 1.0000
7.750 0.8691 0.03027 0.01959 -0.0013 0.1470 1.0000
8.000 0.8831 0.03177 0.02111 0.0002 0.1227 1.0000
8.250 0.8970 0.03343 0.02274 0.0017 0.1058 1.0000
8.500 0.9108 0.03515 0.02444 0.0031 0.0912 1.0000
9.000 0.9452 0.03905 0.02880 0.0056 0.0710 1.0000
9.250 0.9592 0.04103 0.03077 0.0067 0.0640 1.0000
9.500 0.9755 0.04348 0.03367 0.0080 0.0583 1.0000
9.750 0.9900 0.04603 0.03644 0.0091 0.0549 1.0000
10.000 1.0037 0.04911 0.03962 0.0101 0.0523 1.0000
10.250 1.0079 0.05264 0.04378 0.0118 0.0504 1.0000
10.500 1.0055 0.05612 0.04773 0.0136 0.0482 1.0000
10.750 0.9986 0.05934 0.05127 0.0154 0.0463 1.0000
11.000 0.9895 0.06265 0.05483 0.0167 0.0448 1.0000
11.250 0.9779 0.06639 0.05879 0.0173 0.0439 1.0000
11.500 0.9626 0.07085 0.06349 0.0167 0.0435 1.0000
11.750 0.9420 0.07647 0.06933 0.0147 0.0436 1.0000
12.000 0.9124 0.08434 0.07745 0.0102 0.0449 1.0000
12.250 0.8776 0.09471 0.08792 0.0034 0.0475 1.0000
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Polar data table (+)
Polar graphs
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