BOEING 737 MIDSPAN AIRFOIL (b737c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737c-il) Reynolds number: 100,000 Max Cl/Cd: 49.35 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737c-il-100000.txt Download as CSV file: xf-b737c-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5573 0.09236 0.08771 -0.0240 1.0000 0.0788
-8.500 -0.5748 0.08902 0.08429 -0.0277 1.0000 0.0793
-8.250 -0.5905 0.08673 0.08178 -0.0297 1.0000 0.0797
-8.000 -0.5528 0.07953 0.07496 -0.0252 1.0000 0.0855
-7.750 -0.5553 0.07564 0.07103 -0.0269 1.0000 0.0889
-7.500 -0.5664 0.07255 0.06770 -0.0294 1.0000 0.0927
-7.250 -0.5693 0.06815 0.06315 -0.0297 1.0000 0.0953
-7.000 -0.5546 0.06407 0.05924 -0.0285 1.0000 0.1001
-6.500 -0.5482 0.05727 0.05211 -0.0273 1.0000 0.1119
-6.250 -0.5481 0.05608 0.05044 -0.0256 1.0000 0.1231
-6.000 -0.5337 0.05115 0.04579 -0.0247 1.0000 0.1284
-5.750 -0.5268 0.04829 0.04279 -0.0231 1.0000 0.1412
-5.500 -0.5181 0.04552 0.03995 -0.0214 1.0000 0.1566
-5.250 -0.5119 0.04314 0.03744 -0.0195 1.0000 0.1824
-4.750 -0.4932 0.03903 0.03313 -0.0153 1.0000 0.2370
-4.500 -0.4807 0.03536 0.02973 -0.0134 1.0000 0.2610
-4.250 -0.4662 0.03312 0.02727 -0.0118 1.0000 0.2786
-4.000 -0.4489 0.03043 0.02451 -0.0104 1.0000 0.2906
-3.750 -0.3813 0.02979 0.02135 -0.0083 1.0000 0.0935
-3.500 -0.3576 0.02684 0.01820 -0.0068 1.0000 0.0773
-3.250 -0.3375 0.02494 0.01607 -0.0053 1.0000 0.0702
-3.000 -0.3197 0.02514 0.01585 -0.0034 0.9993 0.0660
-2.750 -0.2740 0.02262 0.01325 -0.0068 0.9932 0.0646
-2.500 -0.2286 0.02096 0.01149 -0.0101 0.9856 0.0676
-2.250 -0.1861 0.01951 0.01016 -0.0132 0.9774 0.0721
-2.000 -0.1425 0.01846 0.00912 -0.0164 0.9699 0.0776
-1.750 -0.1043 0.01750 0.00807 -0.0188 0.9595 0.0901
-1.500 -0.0794 0.01411 0.00752 -0.0180 0.9555 0.7271
-1.250 -0.0298 0.01463 0.00836 -0.0176 0.9559 0.9529
-1.000 0.0506 0.01476 0.00815 -0.0279 0.9574 0.9825
-0.750 0.1299 0.01460 0.00776 -0.0387 0.9569 1.0000
-0.500 0.1707 0.01453 0.00753 -0.0423 0.9444 1.0000
-0.250 0.2068 0.01451 0.00740 -0.0448 0.9326 1.0000
0.000 0.2409 0.01450 0.00729 -0.0468 0.9213 1.0000
0.250 0.2737 0.01443 0.00714 -0.0481 0.9085 1.0000
0.500 0.3035 0.01436 0.00701 -0.0486 0.8958 1.0000
0.750 0.3313 0.01434 0.00693 -0.0487 0.8845 1.0000
1.000 0.3549 0.01442 0.00698 -0.0482 0.8728 1.0000
1.250 0.3787 0.01450 0.00704 -0.0476 0.8615 1.0000
1.500 0.4028 0.01455 0.00707 -0.0468 0.8505 1.0000
1.750 0.4269 0.01455 0.00705 -0.0458 0.8387 1.0000
2.000 0.4501 0.01453 0.00701 -0.0445 0.8256 1.0000
2.250 0.4725 0.01453 0.00700 -0.0430 0.8114 1.0000
2.500 0.4947 0.01456 0.00705 -0.0415 0.7966 1.0000
2.750 0.5168 0.01463 0.00712 -0.0399 0.7815 1.0000
3.000 0.5391 0.01474 0.00723 -0.0384 0.7660 1.0000
3.250 0.5613 0.01486 0.00737 -0.0369 0.7498 1.0000
3.500 0.5837 0.01500 0.00755 -0.0354 0.7328 1.0000
3.750 0.6062 0.01514 0.00769 -0.0338 0.7150 1.0000
4.000 0.6282 0.01530 0.00788 -0.0322 0.6953 1.0000
4.250 0.6498 0.01543 0.00802 -0.0303 0.6726 1.0000
4.500 0.6709 0.01554 0.00818 -0.0284 0.6474 1.0000
4.750 0.6922 0.01561 0.00825 -0.0266 0.6207 1.0000
5.000 0.7136 0.01568 0.00833 -0.0247 0.5922 1.0000
5.250 0.7344 0.01575 0.00843 -0.0228 0.5590 1.0000
5.500 0.7537 0.01570 0.00857 -0.0209 0.5084 1.0000
5.750 0.7724 0.01565 0.00824 -0.0185 0.4532 1.0000
6.000 0.7892 0.01643 0.00871 -0.0163 0.3916 1.0000
6.250 0.8054 0.01733 0.00928 -0.0144 0.3350 1.0000
6.500 0.8217 0.01832 0.01003 -0.0126 0.2822 1.0000
6.750 0.8378 0.01940 0.01085 -0.0109 0.2365 1.0000
7.000 0.8540 0.02060 0.01188 -0.0093 0.1956 1.0000
7.250 0.8699 0.02189 0.01299 -0.0077 0.1588 1.0000
7.500 0.8856 0.02328 0.01424 -0.0060 0.1271 1.0000
7.750 0.9024 0.02493 0.01579 -0.0044 0.1042 1.0000
8.000 0.9206 0.02659 0.01741 -0.0031 0.0883 1.0000
8.250 0.9421 0.02879 0.01967 -0.0020 0.0788 1.0000
8.500 0.9641 0.03117 0.02195 -0.0014 0.0708 1.0000
8.750 0.9836 0.03309 0.02429 0.0000 0.0649 1.0000
9.000 1.0038 0.03554 0.02695 0.0010 0.0608 1.0000
9.250 1.0198 0.03898 0.03063 0.0021 0.0571 1.0000
9.500 1.0302 0.04159 0.03382 0.0043 0.0539 1.0000
9.750 1.0377 0.04521 0.03797 0.0064 0.0526 1.0000
10.000 1.0408 0.04892 0.04213 0.0086 0.0515 1.0000
10.250 1.0504 0.05156 0.04488 0.0098 0.0489 1.0000
10.500 1.0516 0.05595 0.04940 0.0110 0.0470 1.0000
10.750 1.0421 0.06092 0.05470 0.0129 0.0466 1.0000
11.000 1.0306 0.06484 0.05894 0.0149 0.0467 1.0000
11.250 1.0147 0.06781 0.06218 0.0172 0.0470 1.0000
11.500 0.9907 0.07118 0.06585 0.0183 0.0477 1.0000
11.750 0.9137 0.08297 0.07815 0.0112 0.0545 1.0000
12.000 0.8914 0.09051 0.08575 0.0067 0.0560 1.0000
12.250 0.8739 0.09806 0.09334 0.0026 0.0571 1.0000
12.500 0.8630 0.10519 0.10046 -0.0003 0.0579 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING 737 MIDSPAN AIRFOIL (b737c-il)