BOEING 737 MIDSPAN AIRFOIL (b737b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737b-il) Reynolds number: 500,000 Max Cl/Cd: 69.82 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737b-il-500000.txt Download as CSV file: xf-b737b-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8238 0.11702 0.11429 0.0057 1.0000 0.0216
-15.250 -0.8571 0.10518 0.10238 -0.0010 1.0000 0.0213
-15.000 -0.9018 0.09119 0.08822 -0.0105 1.0000 0.0209
-14.750 -0.9402 0.07959 0.07642 -0.0189 1.0000 0.0207
-14.500 -0.9729 0.07010 0.06671 -0.0257 1.0000 0.0205
-14.250 -1.0007 0.06231 0.05869 -0.0310 1.0000 0.0204
-14.000 -1.0237 0.05591 0.05206 -0.0348 1.0000 0.0203
-13.750 -1.0423 0.05069 0.04661 -0.0372 1.0000 0.0203
-13.500 -1.0570 0.04642 0.04210 -0.0383 1.0000 0.0203
-13.250 -1.0681 0.04294 0.03840 -0.0382 1.0000 0.0204
-13.000 -1.0757 0.04010 0.03534 -0.0371 1.0000 0.0205
-12.750 -1.0798 0.03770 0.03273 -0.0352 1.0000 0.0206
-12.500 -1.0796 0.03561 0.03043 -0.0330 1.0000 0.0208
-12.250 -1.0733 0.03366 0.02825 -0.0313 1.0000 0.0211
-12.000 -1.0636 0.03197 0.02634 -0.0297 1.0000 0.0213
-11.750 -1.0513 0.03065 0.02480 -0.0281 1.0000 0.0216
-11.500 -1.0376 0.02845 0.02246 -0.0269 1.0000 0.0220
-11.250 -1.0197 0.02715 0.02114 -0.0260 1.0000 0.0224
-11.000 -1.0011 0.02621 0.02016 -0.0250 1.0000 0.0229
-10.750 -0.9817 0.02529 0.01919 -0.0240 1.0000 0.0233
-10.500 -0.9621 0.02430 0.01812 -0.0230 1.0000 0.0238
-10.250 -0.9422 0.02330 0.01703 -0.0219 1.0000 0.0243
-10.000 -0.9218 0.02237 0.01600 -0.0208 1.0000 0.0248
-9.750 -0.9009 0.02158 0.01511 -0.0197 1.0000 0.0253
-9.500 -0.8810 0.02049 0.01395 -0.0185 1.0000 0.0258
-9.250 -0.8619 0.01939 0.01287 -0.0173 1.0000 0.0265
-9.000 -0.8412 0.01868 0.01217 -0.0161 1.0000 0.0271
-8.750 -0.8201 0.01808 0.01155 -0.0150 1.0000 0.0279
-8.500 -0.7989 0.01752 0.01095 -0.0138 1.0000 0.0288
-8.250 -0.7771 0.01704 0.01041 -0.0126 1.0000 0.0297
-8.000 -0.7586 0.01614 0.00949 -0.0110 1.0000 0.0306
-7.750 -0.7387 0.01547 0.00885 -0.0096 1.0000 0.0315
-7.500 -0.7175 0.01497 0.00834 -0.0084 1.0000 0.0326
-7.250 -0.6960 0.01450 0.00785 -0.0071 1.0000 0.0338
-7.000 -0.6737 0.01413 0.00744 -0.0060 1.0000 0.0348
-6.750 -0.6543 0.01342 0.00676 -0.0045 1.0000 0.0366
-6.500 -0.6323 0.01303 0.00637 -0.0033 1.0000 0.0384
-6.250 -0.6099 0.01269 0.00602 -0.0022 1.0000 0.0402
-6.000 -0.5889 0.01217 0.00552 -0.0010 1.0000 0.0425
-5.750 -0.5577 0.01181 0.00516 -0.0017 0.9981 0.0459
-5.500 -0.5170 0.01132 0.00471 -0.0045 0.9939 0.0520
-5.250 -0.4785 0.01075 0.00423 -0.0067 0.9877 0.0656
-5.000 -0.4432 0.00953 0.00362 -0.0090 0.9806 0.1741
-4.750 -0.4053 0.00895 0.00335 -0.0113 0.9723 0.2418
-4.500 -0.3706 0.00857 0.00313 -0.0127 0.9576 0.2799
-4.250 -0.3352 0.00825 0.00292 -0.0141 0.9386 0.3135
-4.000 -0.3017 0.00794 0.00271 -0.0150 0.9104 0.3488
-3.750 -0.2730 0.00768 0.00251 -0.0149 0.8755 0.3889
-3.500 -0.2476 0.00753 0.00238 -0.0141 0.8396 0.4333
-3.250 -0.2226 0.00745 0.00230 -0.0131 0.8061 0.4736
-3.000 -0.1972 0.00740 0.00225 -0.0123 0.7790 0.5134
-2.750 -0.1711 0.00734 0.00222 -0.0117 0.7584 0.5463
-2.500 -0.1440 0.00734 0.00218 -0.0113 0.7402 0.5682
-2.250 -0.1168 0.00734 0.00215 -0.0108 0.7231 0.5858
-2.000 -0.0894 0.00734 0.00211 -0.0105 0.7070 0.6019
-1.750 -0.0620 0.00734 0.00208 -0.0101 0.6911 0.6164
-1.500 -0.0344 0.00734 0.00206 -0.0098 0.6754 0.6309
-1.250 -0.0068 0.00734 0.00204 -0.0094 0.6600 0.6456
-1.000 0.0209 0.00735 0.00202 -0.0091 0.6449 0.6607
-0.750 0.0484 0.00734 0.00201 -0.0088 0.6297 0.6754
-0.500 0.0758 0.00734 0.00200 -0.0085 0.6144 0.6894
-0.250 0.1033 0.00736 0.00200 -0.0081 0.5983 0.7035
0.000 0.1307 0.00738 0.00200 -0.0078 0.5813 0.7182
0.500 0.1854 0.00742 0.00203 -0.0071 0.5460 0.7494
0.750 0.2125 0.00744 0.00205 -0.0067 0.5266 0.7666
1.000 0.2395 0.00746 0.00208 -0.0063 0.5052 0.7850
1.250 0.2660 0.00751 0.00213 -0.0057 0.4825 0.8053
1.500 0.2920 0.00758 0.00219 -0.0051 0.4570 0.8276
1.750 0.3174 0.00769 0.00227 -0.0043 0.4276 0.8535
2.000 0.3421 0.00782 0.00238 -0.0034 0.3955 0.8835
2.250 0.3666 0.00802 0.00250 -0.0023 0.3613 0.9139
2.500 0.3936 0.00827 0.00265 -0.0019 0.3286 0.9383
2.750 0.4243 0.00854 0.00281 -0.0023 0.3014 0.9571
3.000 0.4585 0.00881 0.00297 -0.0036 0.2791 0.9710
3.250 0.4957 0.00909 0.00314 -0.0056 0.2592 0.9808
3.500 0.5346 0.00936 0.00331 -0.0080 0.2413 0.9876
3.750 0.5734 0.00961 0.00349 -0.0104 0.2259 0.9940
4.000 0.6136 0.00985 0.00365 -0.0131 0.2111 0.9988
4.250 0.6407 0.01006 0.00382 -0.0131 0.1998 1.0000
4.500 0.6629 0.01031 0.00400 -0.0121 0.1897 1.0000
4.750 0.6862 0.01051 0.00416 -0.0112 0.1805 1.0000
5.000 0.7093 0.01076 0.00438 -0.0104 0.1720 1.0000
5.250 0.7327 0.01101 0.00458 -0.0095 0.1642 1.0000
5.500 0.7561 0.01129 0.00483 -0.0087 0.1572 1.0000
5.750 0.7802 0.01154 0.00506 -0.0080 0.1507 1.0000
6.000 0.8037 0.01189 0.00536 -0.0072 0.1446 1.0000
6.250 0.8288 0.01210 0.00560 -0.0067 0.1396 1.0000
6.500 0.8529 0.01244 0.00589 -0.0061 0.1340 1.0000
6.750 0.8774 0.01276 0.00622 -0.0055 0.1293 1.0000
7.000 0.9027 0.01300 0.00647 -0.0051 0.1244 1.0000
7.250 0.9265 0.01342 0.00683 -0.0045 0.1193 1.0000
7.500 0.9515 0.01372 0.00717 -0.0041 0.1156 1.0000
7.750 0.9768 0.01399 0.00746 -0.0037 0.1117 1.0000
8.000 1.0008 0.01440 0.00785 -0.0032 0.1076 1.0000
8.250 1.0246 0.01483 0.00829 -0.0027 0.1040 1.0000
8.500 1.0499 0.01509 0.00861 -0.0023 0.1006 1.0000
8.750 1.0741 0.01546 0.00898 -0.0019 0.0968 1.0000
9.000 1.0965 0.01602 0.00952 -0.0012 0.0930 1.0000
9.250 1.1215 0.01630 0.00986 -0.0009 0.0900 1.0000
9.500 1.1455 0.01666 0.01025 -0.0005 0.0865 1.0000
9.750 1.1667 0.01730 0.01085 0.0003 0.0826 1.0000
10.000 1.1914 0.01758 0.01122 0.0006 0.0796 1.0000
10.250 1.2144 0.01800 0.01165 0.0011 0.0761 1.0000
10.500 1.2346 0.01868 0.01232 0.0019 0.0726 1.0000
10.750 1.2577 0.01907 0.01279 0.0024 0.0695 1.0000
11.000 1.2784 0.01964 0.01336 0.0031 0.0662 1.0000
11.250 1.2977 0.02032 0.01408 0.0040 0.0631 1.0000
11.500 1.3182 0.02087 0.01468 0.0047 0.0602 1.0000
11.750 1.3342 0.02173 0.01553 0.0059 0.0574 1.0000
12.000 1.3513 0.02248 0.01636 0.0070 0.0552 1.0000
12.250 1.3675 0.02318 0.01712 0.0081 0.0530 1.0000
12.500 1.3789 0.02410 0.01806 0.0098 0.0511 1.0000
12.750 1.3863 0.02532 0.01933 0.0117 0.0494 1.0000
13.000 1.3985 0.02627 0.02038 0.0129 0.0480 1.0000
13.250 1.4084 0.02743 0.02163 0.0140 0.0466 1.0000
13.500 1.4160 0.02886 0.02312 0.0149 0.0454 1.0000
13.750 1.4191 0.03082 0.02512 0.0156 0.0443 1.0000
14.000 1.4199 0.03318 0.02757 0.0158 0.0433 1.0000
14.250 1.4270 0.03511 0.02963 0.0157 0.0425 1.0000
14.500 1.4318 0.03737 0.03200 0.0153 0.0415 1.0000
14.750 1.4345 0.03995 0.03469 0.0147 0.0407 1.0000
15.000 1.4351 0.04287 0.03770 0.0138 0.0400 1.0000
15.250 1.4328 0.04620 0.04111 0.0127 0.0393 1.0000
15.500 1.4269 0.05003 0.04502 0.0114 0.0387 1.0000
15.750 1.4170 0.05433 0.04940 0.0099 0.0382 1.0000
16.000 1.4083 0.05859 0.05377 0.0084 0.0377 1.0000
16.250 1.4014 0.06286 0.05817 0.0066 0.0373 1.0000
16.500 1.3925 0.06744 0.06290 0.0047 0.0368 1.0000
16.750 1.3823 0.07237 0.06795 0.0025 0.0364 1.0000
17.000 1.3713 0.07752 0.07322 0.0001 0.0360 1.0000
17.250 1.3596 0.08293 0.07874 -0.0025 0.0356 1.0000
17.500 1.3475 0.08846 0.08438 -0.0051 0.0352 1.0000
17.750 1.3356 0.09404 0.09006 -0.0078 0.0348 1.0000
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