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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5367 0.08409 0.08195 -0.0195 1.0000 0.0115 -8.750 -0.5448 0.07734 0.07520 -0.0270 1.0000 0.0115 -8.500 -0.5556 0.07244 0.07025 -0.0308 1.0000 0.0115 -8.250 -0.5599 0.06806 0.06580 -0.0326 1.0000 0.0116 -8.000 -0.5582 0.06357 0.06121 -0.0345 0.9865 0.0116 -7.500 -0.5436 0.05124 0.04830 -0.0373 0.9257 0.0096 -7.250 -0.5357 0.04797 0.04483 -0.0367 0.9065 0.0094 -7.000 -0.5251 0.04450 0.04112 -0.0358 0.8907 0.0091 -6.750 -0.5121 0.04088 0.03722 -0.0349 0.8775 0.0089 -6.500 -0.4971 0.03714 0.03318 -0.0337 0.8660 0.0088 -6.250 -0.4801 0.03337 0.02907 -0.0325 0.8562 0.0088 -6.000 -0.4614 0.02967 0.02501 -0.0311 0.8475 0.0089 -5.750 -0.4409 0.02623 0.02118 -0.0297 0.8391 0.0091 -5.500 -0.4188 0.02311 0.01769 -0.0286 0.8315 0.0092 -5.250 -0.3949 0.02052 0.01471 -0.0275 0.8244 0.0096 -5.000 -0.3699 0.01881 0.01271 -0.0269 0.8179 0.0098 -4.750 -0.3449 0.01715 0.01080 -0.0263 0.8113 0.0097 -4.500 -0.3194 0.01579 0.00923 -0.0258 0.8052 0.0097 -4.250 -0.2936 0.01466 0.00795 -0.0254 0.7990 0.0097 -4.000 -0.2682 0.01375 0.00689 -0.0249 0.7931 0.0097 -3.750 -0.2427 0.01296 0.00600 -0.0245 0.7867 0.0098 -3.500 -0.2174 0.01231 0.00525 -0.0241 0.7801 0.0099 -3.250 -0.1920 0.01172 0.00459 -0.0237 0.7741 0.0100 -3.000 -0.1667 0.01110 0.00391 -0.0233 0.7678 0.0104 -2.750 -0.1404 0.01075 0.00350 -0.0231 0.7622 0.0111 -2.500 -0.1135 0.01043 0.00316 -0.0231 0.7559 0.0120 -2.250 -0.0865 0.01017 0.00283 -0.0229 0.7500 0.0136 -2.000 -0.0594 0.00988 0.00249 -0.0229 0.7447 0.0162 -1.750 -0.0318 0.00970 0.00228 -0.0229 0.7389 0.0189 -1.250 0.0233 0.00937 0.00195 -0.0230 0.7260 0.0327 -1.000 0.0505 0.00916 0.00180 -0.0230 0.7190 0.0675 -0.750 0.0685 0.00722 0.00145 -0.0223 0.7126 0.5622 -0.500 0.0948 0.00701 0.00145 -0.0220 0.7069 0.6355 -0.250 0.1220 0.00692 0.00144 -0.0219 0.7016 0.6734 0.000 0.1497 0.00686 0.00143 -0.0219 0.6957 0.6981 0.250 0.1771 0.00681 0.00143 -0.0218 0.6905 0.7221 0.500 0.2045 0.00676 0.00144 -0.0217 0.6843 0.7464 0.750 0.2322 0.00675 0.00143 -0.0217 0.6756 0.7583 1.000 0.2603 0.00674 0.00142 -0.0218 0.6659 0.7664 1.250 0.2882 0.00676 0.00142 -0.0218 0.6552 0.7753 1.500 0.3158 0.00677 0.00143 -0.0218 0.6422 0.7844 1.750 0.3433 0.00680 0.00144 -0.0218 0.6275 0.7947 2.000 0.3707 0.00683 0.00147 -0.0217 0.6111 0.8064 2.250 0.3979 0.00687 0.00151 -0.0216 0.5942 0.8190 2.500 0.4249 0.00692 0.00158 -0.0215 0.5767 0.8321 2.750 0.4515 0.00700 0.00164 -0.0213 0.5562 0.8466 3.000 0.4774 0.00714 0.00173 -0.0209 0.5262 0.8623 3.250 0.5026 0.00734 0.00184 -0.0205 0.4875 0.8787 3.500 0.5270 0.00761 0.00201 -0.0199 0.4455 0.8960 3.750 0.5512 0.00795 0.00221 -0.0194 0.3990 0.9141 4.000 0.5757 0.00838 0.00244 -0.0190 0.3420 0.9325 4.250 0.6031 0.00876 0.00268 -0.0192 0.3101 0.9495 4.500 0.6337 0.00905 0.00293 -0.0201 0.2882 0.9642 4.750 0.6653 0.00932 0.00314 -0.0213 0.2640 0.9771 5.000 0.6971 0.00970 0.00338 -0.0226 0.2253 0.9881 5.250 0.7279 0.01025 0.00371 -0.0239 0.1807 0.9982 5.500 0.7522 0.01067 0.00401 -0.0237 0.1539 1.0000 5.750 0.7762 0.01098 0.00427 -0.0232 0.1394 1.0000 6.000 0.8000 0.01133 0.00456 -0.0228 0.1219 1.0000 6.250 0.8234 0.01174 0.00488 -0.0223 0.1000 1.0000 6.500 0.8462 0.01223 0.00526 -0.0218 0.0779 1.0000 6.750 0.8693 0.01270 0.00566 -0.0213 0.0606 1.0000 7.000 0.8920 0.01322 0.00610 -0.0207 0.0453 1.0000 7.250 0.9148 0.01374 0.00658 -0.0202 0.0339 1.0000 7.500 0.9379 0.01422 0.00706 -0.0197 0.0278 1.0000 7.750 0.9607 0.01473 0.00758 -0.0192 0.0236 1.0000 8.000 0.9839 0.01518 0.00809 -0.0187 0.0216 1.0000 8.250 1.0064 0.01570 0.00865 -0.0181 0.0199 1.0000 8.500 1.0278 0.01634 0.00934 -0.0174 0.0179 1.0000 8.750 1.0493 0.01694 0.01001 -0.0167 0.0167 1.0000 9.000 1.0712 0.01746 0.01061 -0.0161 0.0158 1.0000 9.250 1.0926 0.01803 0.01124 -0.0155 0.0147 1.0000 9.500 1.1134 0.01862 0.01188 -0.0148 0.0137 1.0000 9.750 1.1322 0.01939 0.01270 -0.0139 0.0127 1.0000 10.000 1.1485 0.02036 0.01378 -0.0126 0.0119 1.0000 10.250 1.1675 0.02103 0.01454 -0.0117 0.0114 1.0000 10.500 1.1851 0.02178 0.01540 -0.0106 0.0108 1.0000 10.750 1.2014 0.02258 0.01628 -0.0094 0.0102 1.0000 11.000 1.2159 0.02335 0.01714 -0.0080 0.0096 1.0000 11.250 1.2297 0.02417 0.01802 -0.0065 0.0091 1.0000 11.500 1.2403 0.02526 0.01918 -0.0048 0.0085 1.0000 11.750 1.2484 0.02657 0.02059 -0.0031 0.0081 1.0000 12.000 1.2597 0.02768 0.02184 -0.0018 0.0078 1.0000 12.250 1.2689 0.02898 0.02328 -0.0005 0.0075 1.0000 12.500 1.2770 0.03044 0.02486 0.0007 0.0071 1.0000 12.750 1.2841 0.03202 0.02656 0.0018 0.0069 1.0000 13.000 1.2905 0.03371 0.02838 0.0027 0.0066 1.0000 13.250 1.2963 0.03553 0.03030 0.0034 0.0064 1.0000 13.500 1.3008 0.03752 0.03241 0.0040 0.0062 1.0000 13.750 1.3038 0.03973 0.03474 0.0045 0.0060 1.0000 14.000 1.3044 0.04227 0.03740 0.0048 0.0059 1.0000 14.250 1.3017 0.04529 0.04055 0.0049 0.0057 1.0000 14.500 1.2953 0.04886 0.04427 0.0046 0.0056 1.0000 14.750 1.2854 0.05302 0.04858 0.0040 0.0055 1.0000 15.000 1.2785 0.05704 0.05276 0.0031 0.0055 1.0000 15.250 1.2697 0.06150 0.05739 0.0018 0.0054 1.0000 15.500 1.2591 0.06654 0.06262 -0.0001 0.0054 1.0000 15.750 1.2469 0.07218 0.06842 -0.0025 0.0053 1.0000 16.000 1.2325 0.07850 0.07491 -0.0055 0.0053 1.0000 16.250 1.2164 0.08548 0.08205 -0.0090 0.0053 1.0000 16.500 1.1987 0.09304 0.08978 -0.0129 0.0053 1.0000 16.750 1.1792 0.10115 0.09804 -0.0171 0.0053 1.0000 17.000 1.1586 0.10963 0.10664 -0.0215 0.0053 1.0000 17.250 1.1376 0.11828 0.11542 -0.0259 0.0053 1.0000 17.500 1.1164 0.12724 0.12450 -0.0306 0.0053 1.0000 17.750 1.0954 0.13645 0.13383 -0.0354 0.0054 1.0000 18.000 1.0746 0.14589 0.14337 -0.0405 0.0054 1.0000 18.250 1.0540 0.15571 0.15330 -0.0458 0.0054 1.0000 18.500 1.0314 0.16670 0.16439 -0.0518 0.0055 1.0000 18.750 1.0005 0.18106 0.17887 -0.0595 0.0055 1.0000