BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.7 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737b-il-1000000.txt Download as CSV file: xf-b737b-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.0640 0.11440 0.11186 0.0044 1.0000 0.0135
-18.000 -1.1027 0.10267 0.09993 -0.0025 1.0000 0.0135
-17.750 -1.1307 0.09336 0.09046 -0.0080 1.0000 0.0135
-17.500 -1.1541 0.08521 0.08216 -0.0127 1.0000 0.0135
-17.250 -1.1732 0.07801 0.07481 -0.0168 1.0000 0.0135
-17.000 -1.1895 0.07159 0.06825 -0.0205 1.0000 0.0135
-16.750 -1.2036 0.06578 0.06232 -0.0237 1.0000 0.0136
-16.500 -1.2157 0.06050 0.05690 -0.0264 1.0000 0.0136
-16.250 -1.2244 0.05581 0.05209 -0.0288 1.0000 0.0137
-16.000 -1.2311 0.05153 0.04769 -0.0309 1.0000 0.0137
-15.750 -1.2355 0.04767 0.04372 -0.0326 1.0000 0.0138
-15.500 -1.2381 0.04418 0.04011 -0.0340 1.0000 0.0139
-15.250 -1.2386 0.04105 0.03686 -0.0352 1.0000 0.0140
-15.000 -1.2373 0.03826 0.03396 -0.0359 1.0000 0.0141
-14.750 -1.2346 0.03575 0.03135 -0.0364 1.0000 0.0142
-14.500 -1.2304 0.03355 0.02905 -0.0365 1.0000 0.0144
-14.250 -1.2252 0.03161 0.02699 -0.0362 1.0000 0.0145
-14.000 -1.2187 0.02992 0.02521 -0.0356 1.0000 0.0146
-13.750 -1.2109 0.02848 0.02367 -0.0346 1.0000 0.0148
-13.500 -1.2018 0.02726 0.02235 -0.0333 1.0000 0.0149
-13.250 -1.1913 0.02622 0.02123 -0.0318 1.0000 0.0150
-13.000 -1.1790 0.02538 0.02030 -0.0302 1.0000 0.0151
-12.750 -1.1739 0.02358 0.01840 -0.0279 1.0000 0.0154
-12.500 -1.1607 0.02243 0.01719 -0.0264 1.0000 0.0157
-12.250 -1.1433 0.02162 0.01634 -0.0253 1.0000 0.0159
-12.000 -1.1243 0.02093 0.01562 -0.0242 1.0000 0.0162
-11.750 -1.1044 0.02029 0.01495 -0.0232 1.0000 0.0165
-11.500 -1.0841 0.01967 0.01428 -0.0223 1.0000 0.0168
-11.250 -1.0634 0.01906 0.01363 -0.0213 1.0000 0.0171
-11.000 -1.0422 0.01849 0.01301 -0.0203 1.0000 0.0174
-10.750 -1.0202 0.01799 0.01247 -0.0194 1.0000 0.0178
-10.500 -0.9977 0.01756 0.01199 -0.0186 1.0000 0.0181
-10.250 -0.9787 0.01675 0.01113 -0.0172 1.0000 0.0185
-10.000 -0.9597 0.01597 0.01033 -0.0159 1.0000 0.0190
-9.750 -0.9382 0.01549 0.00983 -0.0148 1.0000 0.0194
-9.500 -0.9162 0.01506 0.00940 -0.0137 1.0000 0.0199
-9.250 -0.8943 0.01465 0.00897 -0.0126 1.0000 0.0204
-9.000 -0.8722 0.01426 0.00855 -0.0115 1.0000 0.0209
-8.750 -0.8497 0.01391 0.00816 -0.0104 1.0000 0.0214
-8.500 -0.8273 0.01355 0.00778 -0.0092 1.0000 0.0217
-8.250 -0.8080 0.01286 0.00707 -0.0077 1.0000 0.0226
-8.000 -0.7857 0.01250 0.00671 -0.0066 1.0000 0.0233
-7.750 -0.7629 0.01221 0.00642 -0.0055 1.0000 0.0241
-7.500 -0.7399 0.01193 0.00613 -0.0045 1.0000 0.0249
-7.250 -0.7166 0.01170 0.00588 -0.0034 1.0000 0.0255
-7.000 -0.6884 0.01114 0.00531 -0.0036 0.9990 0.0269
-6.750 -0.6515 0.01082 0.00500 -0.0055 0.9965 0.0282
-6.500 -0.6133 0.01053 0.00471 -0.0076 0.9940 0.0296
-6.250 -0.5781 0.01014 0.00432 -0.0092 0.9897 0.0316
-6.000 -0.5408 0.00984 0.00405 -0.0111 0.9857 0.0339
-5.750 -0.5055 0.00952 0.00374 -0.0125 0.9791 0.0367
-5.500 -0.4708 0.00924 0.00347 -0.0138 0.9689 0.0404
-5.250 -0.4370 0.00889 0.00317 -0.0150 0.9526 0.0489
-5.000 -0.4062 0.00841 0.00280 -0.0155 0.9206 0.0780
-4.750 -0.3831 0.00781 0.00241 -0.0145 0.8708 0.1514
-4.500 -0.3587 0.00756 0.00220 -0.0137 0.8338 0.1950
-4.250 -0.3334 0.00736 0.00205 -0.0130 0.8031 0.2322
-4.000 -0.3075 0.00726 0.00193 -0.0125 0.7717 0.2607
-3.750 -0.2812 0.00716 0.00182 -0.0120 0.7439 0.2855
-3.500 -0.2541 0.00705 0.00172 -0.0117 0.7242 0.3105
-3.250 -0.2271 0.00688 0.00161 -0.0113 0.7073 0.3431
-3.000 -0.2003 0.00670 0.00152 -0.0110 0.6913 0.3819
-2.750 -0.1733 0.00651 0.00144 -0.0107 0.6759 0.4263
-2.500 -0.1463 0.00634 0.00139 -0.0104 0.6606 0.4737
-2.250 -0.1188 0.00624 0.00135 -0.0102 0.6458 0.5066
-2.000 -0.0910 0.00619 0.00132 -0.0100 0.6310 0.5305
-1.750 -0.0630 0.00618 0.00129 -0.0098 0.6165 0.5481
-1.500 -0.0349 0.00617 0.00128 -0.0096 0.6017 0.5647
-1.250 -0.0067 0.00616 0.00126 -0.0095 0.5876 0.5798
-1.000 0.0216 0.00617 0.00126 -0.0094 0.5731 0.5931
-0.750 0.0499 0.00620 0.00125 -0.0092 0.5576 0.6070
-0.500 0.0780 0.00622 0.00125 -0.0091 0.5403 0.6212
-0.250 0.1060 0.00623 0.00126 -0.0089 0.5225 0.6351
0.000 0.1341 0.00627 0.00127 -0.0088 0.5024 0.6481
0.750 0.2177 0.00647 0.00134 -0.0083 0.4378 0.6869
1.000 0.2453 0.00659 0.00139 -0.0081 0.4093 0.7000
1.250 0.2727 0.00672 0.00144 -0.0079 0.3780 0.7146
1.500 0.2998 0.00687 0.00152 -0.0077 0.3450 0.7308
1.750 0.3267 0.00702 0.00161 -0.0074 0.3150 0.7477
2.250 0.3806 0.00727 0.00181 -0.0068 0.2727 0.7884
2.500 0.4072 0.00735 0.00192 -0.0064 0.2565 0.8159
2.750 0.4331 0.00741 0.00204 -0.0058 0.2421 0.8501
3.000 0.4587 0.00747 0.00217 -0.0051 0.2296 0.8849
3.250 0.4843 0.00757 0.00230 -0.0044 0.2184 0.9142
3.500 0.5103 0.00771 0.00243 -0.0038 0.2062 0.9383
3.750 0.5387 0.00785 0.00256 -0.0037 0.1955 0.9582
4.000 0.5707 0.00802 0.00270 -0.0044 0.1851 0.9725
4.250 0.6048 0.00823 0.00284 -0.0058 0.1737 0.9824
4.500 0.6405 0.00845 0.00300 -0.0075 0.1632 0.9886
4.750 0.6759 0.00864 0.00316 -0.0091 0.1546 0.9939
5.000 0.7127 0.00889 0.00334 -0.0111 0.1449 0.9972
5.250 0.7475 0.00908 0.00350 -0.0126 0.1384 1.0000
5.500 0.7706 0.00932 0.00369 -0.0117 0.1314 1.0000
5.750 0.7950 0.00947 0.00385 -0.0110 0.1277 1.0000
6.000 0.8190 0.00969 0.00403 -0.0102 0.1225 1.0000
6.250 0.8431 0.00992 0.00424 -0.0095 0.1171 1.0000
6.500 0.8682 0.01010 0.00442 -0.0090 0.1133 1.0000
6.750 0.8930 0.01035 0.00463 -0.0084 0.1089 1.0000
7.000 0.9178 0.01061 0.00488 -0.0079 0.1047 1.0000
7.250 0.9437 0.01080 0.00508 -0.0075 0.1022 1.0000
7.500 0.9693 0.01103 0.00531 -0.0071 0.0987 1.0000
7.750 0.9941 0.01136 0.00560 -0.0067 0.0942 1.0000
8.000 1.0201 0.01156 0.00583 -0.0064 0.0918 1.0000
8.250 1.0459 0.01180 0.00607 -0.0061 0.0889 1.0000
8.500 1.0711 0.01210 0.00635 -0.0057 0.0853 1.0000
8.750 1.0962 0.01241 0.00667 -0.0053 0.0820 1.0000
9.000 1.1220 0.01265 0.00692 -0.0051 0.0791 1.0000
9.250 1.1468 0.01298 0.00723 -0.0047 0.0756 1.0000
9.500 1.1715 0.01333 0.00759 -0.0043 0.0723 1.0000
9.750 1.1967 0.01362 0.00789 -0.0040 0.0695 1.0000
10.000 1.2207 0.01402 0.00827 -0.0036 0.0658 1.0000
10.250 1.2452 0.01436 0.00864 -0.0032 0.0628 1.0000
10.500 1.2691 0.01476 0.00903 -0.0028 0.0595 1.0000
10.750 1.2922 0.01522 0.00949 -0.0023 0.0562 1.0000
11.000 1.3157 0.01562 0.00991 -0.0018 0.0533 1.0000
11.250 1.3372 0.01621 0.01048 -0.0012 0.0498 1.0000
11.500 1.3603 0.01661 0.01092 -0.0007 0.0476 1.0000
11.750 1.3814 0.01719 0.01149 0.0000 0.0449 1.0000
12.000 1.4022 0.01777 0.01210 0.0007 0.0428 1.0000
12.250 1.4232 0.01829 0.01266 0.0014 0.0411 1.0000
12.500 1.4424 0.01895 0.01333 0.0023 0.0394 1.0000
12.750 1.4598 0.01971 0.01412 0.0034 0.0376 1.0000
13.000 1.4791 0.02026 0.01473 0.0042 0.0366 1.0000
13.250 1.4964 0.02092 0.01544 0.0053 0.0355 1.0000
13.500 1.5099 0.02169 0.01625 0.0068 0.0345 1.0000
13.750 1.5196 0.02267 0.01727 0.0087 0.0334 1.0000
14.000 1.5285 0.02372 0.01838 0.0104 0.0325 1.0000
14.250 1.5407 0.02461 0.01935 0.0116 0.0319 1.0000
14.500 1.5511 0.02569 0.02050 0.0127 0.0313 1.0000
14.750 1.5596 0.02700 0.02189 0.0136 0.0307 1.0000
15.000 1.5662 0.02860 0.02356 0.0142 0.0301 1.0000
15.250 1.5705 0.03058 0.02561 0.0145 0.0295 1.0000
15.500 1.5710 0.03312 0.02823 0.0143 0.0289 1.0000
15.750 1.5653 0.03654 0.03176 0.0136 0.0282 1.0000
16.000 1.5682 0.03913 0.03445 0.0128 0.0279 1.0000
16.250 1.5691 0.04205 0.03748 0.0119 0.0276 1.0000
16.500 1.5667 0.04542 0.04096 0.0108 0.0273 1.0000
16.750 1.5609 0.04932 0.04498 0.0093 0.0270 1.0000
17.000 1.5513 0.05378 0.04955 0.0075 0.0267 1.0000
17.250 1.5380 0.05886 0.05475 0.0054 0.0265 1.0000
17.500 1.5206 0.06461 0.06063 0.0030 0.0263 1.0000
17.750 1.4993 0.07112 0.06727 0.0000 0.0261 1.0000
18.000 1.4749 0.07832 0.07461 -0.0033 0.0260 1.0000
18.250 1.4479 0.08615 0.08258 -0.0070 0.0259 1.0000
18.500 1.4191 0.09437 0.09094 -0.0109 0.0258 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING 737 MIDSPAN AIRFOIL (b737b-il)