BOEING 737 MIDSPAN AIRFOIL (b737c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737c-il) Reynolds number: 100,000 Max Cl/Cd: 47.07 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737c-il-100000-n5.txt Download as CSV file: xf-b737c-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4221 0.08931 0.08480 -0.0204 1.0000 0.0532
-9.000 -0.4262 0.08479 0.08031 -0.0221 1.0000 0.0535
-8.750 -0.4317 0.08007 0.07563 -0.0241 1.0000 0.0537
-8.500 -0.4394 0.07507 0.07067 -0.0268 1.0000 0.0537
-8.250 -0.4519 0.06968 0.06530 -0.0305 1.0000 0.0538
-8.000 -0.4672 0.06509 0.06071 -0.0326 1.0000 0.0538
-7.750 -0.4807 0.06103 0.05662 -0.0328 1.0000 0.0537
-7.500 -0.4896 0.05681 0.05233 -0.0328 1.0000 0.0536
-7.250 -0.4956 0.05261 0.04803 -0.0322 1.0000 0.0532
-6.750 -0.5386 0.05497 0.04928 -0.0277 1.0000 0.0327
-6.500 -0.5321 0.05127 0.04547 -0.0264 1.0000 0.0312
-6.250 -0.5238 0.04794 0.04192 -0.0247 1.0000 0.0302
-6.000 -0.5133 0.04498 0.03870 -0.0228 1.0000 0.0304
-5.750 -0.5012 0.04219 0.03558 -0.0209 1.0000 0.0308
-5.500 -0.4881 0.03939 0.03249 -0.0189 1.0000 0.0305
-5.250 -0.4738 0.03654 0.02934 -0.0168 1.0000 0.0293
-5.000 -0.4577 0.03382 0.02627 -0.0148 1.0000 0.0282
-4.750 -0.4398 0.03126 0.02333 -0.0128 1.0000 0.0273
-4.500 -0.4175 0.02879 0.02046 -0.0115 0.9988 0.0266
-4.250 -0.3811 0.02624 0.01747 -0.0130 0.9923 0.0261
-4.000 -0.3435 0.02411 0.01501 -0.0147 0.9857 0.0261
-3.750 -0.3066 0.02229 0.01297 -0.0163 0.9779 0.0265
-3.500 -0.2697 0.02105 0.01161 -0.0182 0.9691 0.0287
-3.250 -0.2333 0.01988 0.01035 -0.0199 0.9595 0.0314
-3.000 -0.1996 0.01864 0.00905 -0.0209 0.9485 0.0327
-2.750 -0.1685 0.01764 0.00799 -0.0216 0.9352 0.0349
-2.500 -0.1389 0.01700 0.00732 -0.0221 0.9188 0.0401
-2.250 -0.1096 0.01638 0.00654 -0.0223 0.9010 0.0444
-2.000 -0.0799 0.01582 0.00583 -0.0225 0.8833 0.0520
-1.750 -0.0500 0.01532 0.00521 -0.0228 0.8663 0.0708
-1.500 -0.0301 0.01315 0.00474 -0.0222 0.8499 0.5074
-1.250 -0.0046 0.01266 0.00456 -0.0213 0.8352 0.6267
-1.000 0.0206 0.01231 0.00453 -0.0200 0.8224 0.7142
-0.750 0.0492 0.01222 0.00462 -0.0190 0.8114 0.7982
-0.500 0.0804 0.01232 0.00473 -0.0186 0.8009 0.8797
-0.250 0.1143 0.01241 0.00472 -0.0192 0.7909 0.9143
0.000 0.1509 0.01249 0.00468 -0.0207 0.7813 0.9401
0.250 0.2135 0.01259 0.00467 -0.0274 0.7729 0.9770
0.500 0.2609 0.01258 0.00454 -0.0316 0.7624 0.9903
0.750 0.3000 0.01258 0.00443 -0.0342 0.7511 0.9988
1.000 0.3263 0.01263 0.00439 -0.0341 0.7407 1.0000
1.250 0.3504 0.01271 0.00439 -0.0336 0.7307 1.0000
1.500 0.3746 0.01280 0.00444 -0.0331 0.7210 1.0000
1.750 0.3987 0.01291 0.00449 -0.0325 0.7115 1.0000
2.000 0.4226 0.01303 0.00458 -0.0317 0.7004 1.0000
2.250 0.4461 0.01316 0.00467 -0.0310 0.6874 1.0000
2.500 0.4694 0.01329 0.00478 -0.0301 0.6739 1.0000
2.750 0.4928 0.01343 0.00491 -0.0293 0.6605 1.0000
3.000 0.5162 0.01358 0.00510 -0.0285 0.6472 1.0000
3.250 0.5396 0.01373 0.00526 -0.0276 0.6339 1.0000
3.500 0.5630 0.01388 0.00544 -0.0267 0.6198 1.0000
3.750 0.5862 0.01404 0.00563 -0.0258 0.6049 1.0000
4.000 0.6092 0.01420 0.00585 -0.0248 0.5884 1.0000
4.250 0.6320 0.01439 0.00604 -0.0237 0.5695 1.0000
4.500 0.6539 0.01453 0.00628 -0.0226 0.5428 1.0000
4.750 0.6760 0.01458 0.00658 -0.0216 0.4902 1.0000
5.000 0.6952 0.01477 0.00637 -0.0196 0.4490 1.0000
5.250 0.7159 0.01521 0.00675 -0.0184 0.4065 1.0000
5.500 0.7356 0.01576 0.00715 -0.0170 0.3590 1.0000
5.750 0.7551 0.01639 0.00764 -0.0158 0.3177 1.0000
6.000 0.7746 0.01706 0.00819 -0.0146 0.2767 1.0000
6.250 0.7940 0.01777 0.00882 -0.0134 0.2389 1.0000
6.500 0.8127 0.01857 0.00947 -0.0122 0.2034 1.0000
6.750 0.8320 0.01935 0.01018 -0.0112 0.1712 1.0000
7.000 0.8513 0.02017 0.01093 -0.0101 0.1420 1.0000
7.250 0.8702 0.02105 0.01174 -0.0091 0.1152 1.0000
7.500 0.8882 0.02206 0.01268 -0.0080 0.0921 1.0000
7.750 0.9057 0.02314 0.01375 -0.0067 0.0743 1.0000
8.000 0.9227 0.02427 0.01492 -0.0055 0.0606 1.0000
8.250 0.9383 0.02555 0.01619 -0.0041 0.0519 1.0000
8.500 0.9546 0.02680 0.01765 -0.0026 0.0461 1.0000
8.750 0.9689 0.02824 0.01917 -0.0010 0.0421 1.0000
9.000 0.9826 0.02997 0.02101 0.0007 0.0394 1.0000
9.250 0.9987 0.03150 0.02278 0.0020 0.0361 1.0000
9.500 1.0132 0.03293 0.02437 0.0033 0.0326 1.0000
9.750 1.0256 0.03488 0.02644 0.0048 0.0305 1.0000
10.000 1.0375 0.03723 0.02902 0.0062 0.0283 1.0000
10.250 1.0487 0.03911 0.03124 0.0078 0.0257 1.0000
10.500 1.0569 0.04143 0.03385 0.0094 0.0241 1.0000
10.750 1.0609 0.04363 0.03628 0.0114 0.0227 1.0000
11.000 1.0621 0.04573 0.03852 0.0132 0.0215 1.0000
11.250 1.0588 0.04863 0.04155 0.0148 0.0204 1.0000
11.500 1.0515 0.05196 0.04518 0.0161 0.0196 1.0000
11.750 1.0431 0.05536 0.04891 0.0168 0.0191 1.0000
12.000 1.0317 0.05940 0.05327 0.0166 0.0186 1.0000
12.250 1.0178 0.06410 0.05825 0.0153 0.0184 1.0000
12.500 1.0016 0.06950 0.06390 0.0131 0.0183 1.0000
12.750 0.9834 0.07565 0.07028 0.0100 0.0183 1.0000
13.000 0.9636 0.08256 0.07738 0.0060 0.0185 1.0000
13.250 0.9424 0.09048 0.08545 0.0010 0.0187 1.0000
13.500 0.9209 0.09930 0.09439 -0.0047 0.0192 1.0000
13.750 0.8998 0.10869 0.10386 -0.0104 0.0196 1.0000
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Polar data table (+)
Polar graphs
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