BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 200,000 Max Cl/Cd: 47.32 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737b-il-200000.txt Download as CSV file: xf-b737b-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6342 0.10618 0.10244 0.0011 1.0000 0.0848
-11.250 -0.9058 0.05399 0.04888 -0.0330 1.0000 0.0457
-11.000 -0.9086 0.04987 0.04455 -0.0319 1.0000 0.0445
-10.750 -0.9190 0.04479 0.03898 -0.0298 1.0000 0.0427
-10.500 -0.9322 0.04009 0.03327 -0.0262 1.0000 0.0408
-10.250 -0.9190 0.03741 0.03030 -0.0248 1.0000 0.0409
-10.000 -0.9028 0.03484 0.02754 -0.0237 1.0000 0.0411
-9.750 -0.8828 0.03296 0.02563 -0.0230 1.0000 0.0420
-9.500 -0.8628 0.03148 0.02410 -0.0221 1.0000 0.0430
-9.250 -0.8435 0.02989 0.02233 -0.0210 1.0000 0.0440
-9.000 -0.8234 0.02829 0.02052 -0.0198 1.0000 0.0448
-8.750 -0.8024 0.02679 0.01881 -0.0186 1.0000 0.0456
-8.500 -0.7807 0.02554 0.01736 -0.0174 1.0000 0.0464
-8.250 -0.7583 0.02397 0.01572 -0.0165 1.0000 0.0475
-8.000 -0.7362 0.02276 0.01459 -0.0156 1.0000 0.0492
-7.750 -0.7141 0.02185 0.01367 -0.0146 1.0000 0.0512
-7.500 -0.6920 0.02098 0.01273 -0.0134 1.0000 0.0530
-7.250 -0.6708 0.01989 0.01164 -0.0121 1.0000 0.0547
-7.000 -0.6510 0.01887 0.01073 -0.0107 1.0000 0.0569
-6.750 -0.6304 0.01815 0.01003 -0.0094 1.0000 0.0600
-6.500 -0.6106 0.01732 0.00920 -0.0079 1.0000 0.0632
-6.250 -0.5913 0.01651 0.00846 -0.0065 1.0000 0.0671
-6.000 -0.5711 0.01582 0.00778 -0.0050 1.0000 0.0720
-5.750 -0.5515 0.01508 0.00709 -0.0036 1.0000 0.0803
-5.500 -0.5324 0.01419 0.00637 -0.0022 1.0000 0.0979
-5.250 -0.5171 0.01265 0.00568 -0.0008 1.0000 0.2267
-5.000 -0.4966 0.01214 0.00545 0.0003 1.0000 0.2943
-4.750 -0.4756 0.01180 0.00529 0.0013 1.0000 0.3341
-4.500 -0.4550 0.01155 0.00521 0.0022 1.0000 0.3706
-4.250 -0.4144 0.01127 0.00514 -0.0007 0.9936 0.4191
-4.000 -0.3686 0.01102 0.00509 -0.0045 0.9839 0.4743
-3.750 -0.3243 0.01082 0.00509 -0.0077 0.9731 0.5278
-3.500 -0.2822 0.01069 0.00511 -0.0102 0.9606 0.5744
-3.250 -0.2434 0.01057 0.00502 -0.0120 0.9449 0.6049
-3.000 -0.2062 0.01041 0.00491 -0.0134 0.9275 0.6273
-2.750 -0.1708 0.01027 0.00479 -0.0143 0.9086 0.6478
-2.500 -0.1389 0.01015 0.00464 -0.0143 0.8849 0.6669
-2.250 -0.1109 0.01008 0.00451 -0.0134 0.8584 0.6851
-2.000 -0.0844 0.01006 0.00443 -0.0124 0.8348 0.7026
-1.750 -0.0588 0.01007 0.00439 -0.0113 0.8130 0.7199
-1.500 -0.0331 0.01009 0.00436 -0.0103 0.7932 0.7367
-1.250 -0.0074 0.01010 0.00434 -0.0093 0.7747 0.7535
-1.000 0.0183 0.01012 0.00432 -0.0083 0.7570 0.7702
-0.750 0.0439 0.01014 0.00431 -0.0073 0.7400 0.7871
-0.500 0.0694 0.01017 0.00431 -0.0063 0.7231 0.8042
-0.250 0.0948 0.01019 0.00432 -0.0052 0.7066 0.8216
0.000 0.1201 0.01022 0.00433 -0.0041 0.6899 0.8397
0.250 0.1453 0.01025 0.00434 -0.0030 0.6731 0.8583
0.500 0.1706 0.01029 0.00437 -0.0018 0.6556 0.8776
0.750 0.1970 0.01035 0.00440 -0.0008 0.6372 0.8974
1.000 0.2257 0.01042 0.00446 -0.0003 0.6170 0.9182
1.250 0.2586 0.01053 0.00451 -0.0006 0.5946 0.9383
1.500 0.2962 0.01065 0.00454 -0.0021 0.5704 0.9549
1.750 0.3375 0.01077 0.00456 -0.0046 0.5425 0.9676
2.000 0.3820 0.01089 0.00455 -0.0080 0.5093 0.9779
2.250 0.4270 0.01105 0.00454 -0.0115 0.4699 0.9881
2.500 0.4722 0.01128 0.00454 -0.0153 0.4244 0.9976
2.750 0.4986 0.01150 0.00457 -0.0156 0.3860 1.0000
3.000 0.5181 0.01177 0.00464 -0.0144 0.3559 1.0000
3.250 0.5382 0.01209 0.00479 -0.0132 0.3299 1.0000
3.500 0.5586 0.01246 0.00500 -0.0121 0.3085 1.0000
3.750 0.5796 0.01285 0.00524 -0.0109 0.2902 1.0000
4.000 0.6012 0.01324 0.00551 -0.0099 0.2738 1.0000
4.250 0.6232 0.01360 0.00580 -0.0089 0.2587 1.0000
4.500 0.6456 0.01397 0.00612 -0.0080 0.2451 1.0000
4.750 0.6681 0.01440 0.00648 -0.0070 0.2331 1.0000
5.000 0.6904 0.01490 0.00685 -0.0061 0.2223 1.0000
5.250 0.7141 0.01523 0.00721 -0.0054 0.2119 1.0000
5.500 0.7373 0.01574 0.00765 -0.0046 0.2031 1.0000
5.750 0.7610 0.01614 0.00803 -0.0039 0.1946 1.0000
6.000 0.7846 0.01668 0.00854 -0.0033 0.1871 1.0000
6.250 0.8087 0.01709 0.00896 -0.0026 0.1799 1.0000
6.500 0.8323 0.01773 0.00952 -0.0020 0.1737 1.0000
6.750 0.8565 0.01813 0.01001 -0.0015 0.1672 1.0000
7.000 0.8802 0.01872 0.01051 -0.0009 0.1616 1.0000
7.250 0.9041 0.01929 0.01116 -0.0003 0.1560 1.0000
7.500 0.9279 0.01975 0.01165 0.0002 0.1504 1.0000
7.750 0.9513 0.02058 0.01237 0.0007 0.1452 1.0000
8.000 0.9745 0.02099 0.01296 0.0013 0.1401 1.0000
8.250 0.9977 0.02148 0.01345 0.0019 0.1350 1.0000
8.500 1.0204 0.02235 0.01428 0.0024 0.1303 1.0000
8.750 1.0427 0.02285 0.01494 0.0031 0.1254 1.0000
9.000 1.0652 0.02340 0.01549 0.0037 0.1209 1.0000
9.250 1.0869 0.02438 0.01647 0.0043 0.1166 1.0000
9.500 1.1077 0.02497 0.01723 0.0051 0.1121 1.0000
9.750 1.1290 0.02558 0.01783 0.0058 0.1081 1.0000
10.000 1.1494 0.02669 0.01895 0.0064 0.1041 1.0000
10.250 1.1679 0.02737 0.01984 0.0074 0.0999 1.0000
10.500 1.1875 0.02803 0.02049 0.0082 0.0962 1.0000
10.750 1.2062 0.02928 0.02174 0.0089 0.0926 1.0000
11.000 1.2213 0.03017 0.02287 0.0102 0.0891 1.0000
11.250 1.2382 0.03093 0.02367 0.0112 0.0858 1.0000
11.500 1.2563 0.03227 0.02490 0.0119 0.0827 1.0000
11.750 1.2659 0.03339 0.02633 0.0136 0.0800 1.0000
12.000 1.2771 0.03452 0.02759 0.0150 0.0774 1.0000
12.250 1.2894 0.03546 0.02853 0.0164 0.0752 1.0000
12.500 1.3024 0.03710 0.03013 0.0173 0.0729 1.0000
12.750 1.3019 0.03870 0.03201 0.0195 0.0713 1.0000
13.000 1.3025 0.04049 0.03401 0.0210 0.0695 1.0000
13.250 1.3058 0.04222 0.03586 0.0220 0.0679 1.0000
13.500 1.3129 0.04381 0.03747 0.0226 0.0664 1.0000
13.750 1.3244 0.04555 0.03915 0.0232 0.0649 1.0000
14.000 1.3171 0.04863 0.04248 0.0235 0.0639 1.0000
14.250 1.3057 0.05219 0.04631 0.0230 0.0630 1.0000
14.500 1.2935 0.05619 0.05055 0.0219 0.0622 1.0000
14.750 1.2802 0.06061 0.05519 0.0203 0.0613 1.0000
15.000 1.2643 0.06563 0.06042 0.0180 0.0606 1.0000
15.250 1.2455 0.07135 0.06634 0.0151 0.0601 1.0000
15.500 1.2193 0.07854 0.07375 0.0111 0.0597 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING 737 MIDSPAN AIRFOIL (b737b-il)