XFOIL Version 6.96 Calculated polar for: BOEING 737 OUTBOARD 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5163 0.09567 0.09096 -0.0181 1.0000 0.0774 -8.750 -0.5194 0.09108 0.08641 -0.0220 1.0000 0.0798 -8.500 -0.5292 0.08589 0.08127 -0.0279 1.0000 0.0812 -8.250 -0.5436 0.08194 0.07727 -0.0316 1.0000 0.0825 -8.000 -0.5621 0.07962 0.07469 -0.0344 1.0000 0.0838 -7.750 -0.5596 0.07391 0.06902 -0.0349 1.0000 0.0857 -7.500 -0.5419 0.06996 0.06525 -0.0335 1.0000 0.0913 -7.250 -0.5480 0.06775 0.06275 -0.0342 1.0000 0.0975 -7.000 -0.5465 0.06330 0.05828 -0.0336 1.0000 0.1012 -6.750 -0.5378 0.06021 0.05526 -0.0323 1.0000 0.1071 -6.500 -0.5487 0.05882 0.05349 -0.0296 1.0000 0.1144 -6.250 -0.5417 0.05512 0.05001 -0.0276 1.0000 0.1187 -6.000 -0.5524 0.05473 0.04920 -0.0237 1.0000 0.1287 -5.750 -0.5460 0.05089 0.04558 -0.0216 1.0000 0.1336 -5.500 -0.5467 0.04886 0.04338 -0.0190 1.0000 0.1457 -5.250 -0.5435 0.04663 0.04106 -0.0168 1.0000 0.1602 -5.000 -0.5374 0.04417 0.03860 -0.0149 1.0000 0.1772 -4.750 -0.5324 0.04191 0.03627 -0.0131 1.0000 0.2044 -4.500 -0.5243 0.03959 0.03390 -0.0114 1.0000 0.2324 -4.250 -0.5132 0.03725 0.03153 -0.0099 1.0000 0.2604 -4.000 -0.4984 0.03503 0.02923 -0.0086 1.0000 0.2853 -3.750 -0.4718 0.03249 0.02643 -0.0094 0.9982 0.3007 -3.500 -0.3887 0.03090 0.02267 -0.0116 0.9940 0.1150 -3.250 -0.3440 0.02979 0.02082 -0.0119 0.9891 0.0845 -3.000 -0.3054 0.02636 0.01729 -0.0137 0.9861 0.0757 -2.750 -0.2646 0.02571 0.01613 -0.0150 0.9815 0.0697 -2.500 -0.2285 0.02392 0.01427 -0.0164 0.9771 0.0690 -2.250 -0.1906 0.02231 0.01271 -0.0183 0.9733 0.0727 -2.000 -0.1533 0.02125 0.01175 -0.0203 0.9693 0.0786 -1.750 -0.1229 0.02055 0.01100 -0.0208 0.9630 0.0841 -1.500 -0.0865 0.01962 0.01009 -0.0230 0.9582 0.1036 -1.250 -0.0653 0.01672 0.00989 -0.0213 0.9550 0.7459 -1.000 -0.0647 0.01720 0.01077 -0.0113 0.9474 0.8993 -0.750 0.0987 0.01844 0.01151 -0.0326 0.9613 0.9923 -0.500 0.1580 0.01831 0.01120 -0.0399 0.9572 0.9970 -0.250 0.2035 0.01820 0.01099 -0.0447 0.9489 1.0000 0.000 0.2571 0.01797 0.01067 -0.0506 0.9423 1.0000 0.250 0.2883 0.01791 0.01056 -0.0524 0.9311 1.0000 0.500 0.3196 0.01788 0.01049 -0.0541 0.9211 1.0000 0.750 0.3578 0.01775 0.01034 -0.0567 0.9131 1.0000 1.000 0.3774 0.01784 0.01043 -0.0561 0.9012 1.0000 1.250 0.3975 0.01793 0.01052 -0.0554 0.8898 1.0000 1.500 0.4209 0.01795 0.01055 -0.0549 0.8790 1.0000 1.750 0.4480 0.01788 0.01048 -0.0548 0.8693 1.0000 2.000 0.4626 0.01806 0.01069 -0.0527 0.8569 1.0000 2.250 0.4793 0.01823 0.01087 -0.0509 0.8450 1.0000 2.500 0.5000 0.01822 0.01087 -0.0492 0.8321 1.0000 2.750 0.5222 0.01802 0.01069 -0.0473 0.8174 1.0000 3.000 0.5441 0.01778 0.01049 -0.0451 0.8023 1.0000 3.250 0.5655 0.01764 0.01037 -0.0432 0.7881 1.0000 3.500 0.5873 0.01753 0.01030 -0.0413 0.7743 1.0000 3.750 0.6096 0.01739 0.01021 -0.0395 0.7599 1.0000 4.000 0.6322 0.01722 0.01012 -0.0377 0.7445 1.0000 4.250 0.6554 0.01698 0.00993 -0.0358 0.7278 1.0000 4.500 0.6794 0.01666 0.00966 -0.0340 0.7101 1.0000 4.750 0.7017 0.01641 0.00949 -0.0321 0.6877 1.0000 5.000 0.7254 0.01605 0.00919 -0.0302 0.6631 1.0000 5.250 0.7472 0.01577 0.00897 -0.0282 0.6298 1.0000 5.500 0.7689 0.01554 0.00873 -0.0261 0.5864 1.0000 5.750 0.7892 0.01552 0.00856 -0.0239 0.5277 1.0000 6.000 0.8072 0.01597 0.00867 -0.0216 0.4580 1.0000 6.250 0.8237 0.01685 0.00913 -0.0195 0.3947 1.0000 6.500 0.8403 0.01782 0.00979 -0.0178 0.3419 1.0000 6.750 0.8571 0.01890 0.01059 -0.0162 0.2983 1.0000 7.000 0.8742 0.01980 0.01137 -0.0148 0.2571 1.0000 7.250 0.8905 0.02068 0.01213 -0.0134 0.2171 1.0000 7.500 0.9046 0.02198 0.01319 -0.0117 0.1754 1.0000 7.750 0.9171 0.02361 0.01456 -0.0097 0.1342 1.0000 8.000 0.9318 0.02528 0.01607 -0.0080 0.1066 1.0000 8.250 0.9495 0.02692 0.01765 -0.0066 0.0907 1.0000 8.500 0.9690 0.02867 0.01941 -0.0055 0.0801 1.0000 8.750 0.9918 0.03067 0.02134 -0.0049 0.0732 1.0000 9.000 1.0146 0.03293 0.02385 -0.0041 0.0678 1.0000 9.250 1.0347 0.03480 0.02585 -0.0033 0.0626 1.0000 9.500 1.0580 0.03861 0.02975 -0.0031 0.0598 1.0000 9.750 1.0716 0.04123 0.03292 -0.0012 0.0582 1.0000 10.000 1.0809 0.04402 0.03624 0.0009 0.0559 1.0000 10.250 1.0880 0.04698 0.03961 0.0028 0.0539 1.0000 10.500 1.0893 0.05070 0.04377 0.0051 0.0534 1.0000 10.750 1.0835 0.05478 0.04830 0.0076 0.0536 1.0000 11.000 1.0704 0.05899 0.05292 0.0103 0.0541 1.0000 11.250 1.0508 0.06297 0.05720 0.0131 0.0547 1.0000 11.500 1.0287 0.06730 0.06179 0.0146 0.0553 1.0000 11.750 1.0051 0.07213 0.06684 0.0148 0.0560 1.0000 12.000 0.9803 0.07761 0.07250 0.0136 0.0567 1.0000 12.250 0.9549 0.08388 0.07891 0.0110 0.0574 1.0000 12.500 0.9302 0.09099 0.08613 0.0074 0.0582 1.0000 12.750 0.9095 0.09858 0.09375 0.0033 0.0590 1.0000