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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.5487 0.11896 0.11541 -0.0009 1.0000 0.0176 -10.500 -0.5473 0.11423 0.11071 -0.0042 1.0000 0.0177 -10.250 -0.5457 0.10953 0.10604 -0.0072 1.0000 0.0178 -10.000 -0.5441 0.10478 0.10132 -0.0103 1.0000 0.0179 -9.750 -0.5430 0.10178 0.09834 -0.0079 1.0000 0.0189 -9.500 -0.5390 0.09862 0.09520 -0.0088 1.0000 0.0199 -9.250 -0.5376 0.09450 0.09110 -0.0112 1.0000 0.0210 -5.750 -0.4730 0.03412 0.02842 -0.0245 0.9837 0.0182 -5.500 -0.4464 0.03114 0.02520 -0.0254 0.9764 0.0170 -5.250 -0.4196 0.02806 0.02174 -0.0255 0.9679 0.0168 -5.000 -0.3913 0.02521 0.01838 -0.0254 0.9591 0.0184 -4.750 -0.3606 0.02320 0.01604 -0.0258 0.9501 0.0181 -4.500 -0.3313 0.02156 0.01414 -0.0260 0.9383 0.0178 -4.250 -0.3026 0.01966 0.01201 -0.0260 0.9243 0.0176 -4.000 -0.2745 0.01818 0.01032 -0.0258 0.9064 0.0176 -3.750 -0.2469 0.01695 0.00893 -0.0255 0.8825 0.0177 -3.500 -0.2196 0.01591 0.00775 -0.0251 0.8521 0.0179 -3.250 -0.1949 0.01475 0.00643 -0.0242 0.8180 0.0185 -3.000 -0.1714 0.01397 0.00547 -0.0232 0.7876 0.0193 -2.750 -0.1473 0.01345 0.00480 -0.0225 0.7649 0.0214 -2.500 -0.1225 0.01306 0.00425 -0.0219 0.7480 0.0235 -2.250 -0.0970 0.01271 0.00372 -0.0213 0.7353 0.0248 -2.000 -0.0710 0.01245 0.00338 -0.0210 0.7254 0.0291 -1.750 -0.0443 0.01227 0.00311 -0.0207 0.7171 0.0322 -1.500 -0.0174 0.01214 0.00291 -0.0205 0.7102 0.0436 -1.250 0.0098 0.01206 0.00273 -0.0204 0.7037 0.0533 -1.000 0.0369 0.01198 0.00258 -0.0203 0.6984 0.0660 -0.750 0.0644 0.01192 0.00246 -0.0203 0.6931 0.0722 -0.500 0.0909 0.01171 0.00234 -0.0202 0.6875 0.1254 -0.250 0.1096 0.01031 0.00220 -0.0192 0.6817 0.5129 0.000 0.1338 0.01001 0.00222 -0.0186 0.6760 0.6015 0.250 0.1565 0.00967 0.00226 -0.0173 0.6709 0.6919 0.500 0.1789 0.00944 0.00245 -0.0156 0.6649 0.7991 0.750 0.2053 0.00947 0.00257 -0.0149 0.6593 0.8538 1.000 0.2332 0.00955 0.00267 -0.0146 0.6544 0.8920 1.250 0.2632 0.00962 0.00278 -0.0147 0.6483 0.9236 1.500 0.3047 0.00978 0.00292 -0.0171 0.6403 0.9614 1.750 0.3455 0.00987 0.00298 -0.0198 0.6287 0.9772 2.000 0.3811 0.00993 0.00302 -0.0216 0.6175 0.9823 2.250 0.4156 0.01001 0.00307 -0.0232 0.6082 0.9875 2.500 0.4505 0.01009 0.00312 -0.0249 0.5991 0.9923 2.750 0.4854 0.01015 0.00320 -0.0266 0.5891 0.9971 3.000 0.5164 0.01025 0.00331 -0.0275 0.5790 1.0000 3.250 0.5405 0.01037 0.00341 -0.0269 0.5685 1.0000 3.500 0.5643 0.01045 0.00353 -0.0262 0.5533 1.0000 3.750 0.5882 0.01046 0.00364 -0.0255 0.5294 1.0000 4.000 0.6103 0.01049 0.00358 -0.0244 0.4677 1.0000 4.250 0.6309 0.01080 0.00365 -0.0231 0.4356 1.0000 4.500 0.6532 0.01110 0.00391 -0.0222 0.3979 1.0000 4.750 0.6739 0.01152 0.00415 -0.0211 0.3558 1.0000 5.000 0.6946 0.01197 0.00446 -0.0200 0.3188 1.0000 5.250 0.7159 0.01241 0.00482 -0.0191 0.2827 1.0000 5.500 0.7366 0.01292 0.00519 -0.0180 0.2466 1.0000 5.750 0.7574 0.01346 0.00560 -0.0171 0.2118 1.0000 6.000 0.7786 0.01399 0.00604 -0.0162 0.1825 1.0000 6.250 0.7999 0.01454 0.00652 -0.0154 0.1545 1.0000 6.500 0.8209 0.01515 0.00701 -0.0145 0.1244 1.0000 6.750 0.8417 0.01580 0.00754 -0.0137 0.0975 1.0000 7.000 0.8624 0.01648 0.00813 -0.0129 0.0783 1.0000 7.250 0.8838 0.01710 0.00878 -0.0121 0.0634 1.0000 7.500 0.9046 0.01779 0.00948 -0.0112 0.0504 1.0000 7.750 0.9244 0.01862 0.01029 -0.0102 0.0405 1.0000 8.000 0.9448 0.01937 0.01117 -0.0092 0.0351 1.0000 8.250 0.9631 0.02035 0.01222 -0.0081 0.0309 1.0000 8.500 0.9807 0.02140 0.01338 -0.0068 0.0281 1.0000 8.750 0.9996 0.02226 0.01439 -0.0057 0.0256 1.0000 9.000 1.0176 0.02321 0.01547 -0.0046 0.0234 1.0000 9.250 1.0326 0.02444 0.01677 -0.0033 0.0207 1.0000 9.500 1.0489 0.02554 0.01802 -0.0020 0.0188 1.0000 9.750 1.0662 0.02647 0.01910 -0.0009 0.0167 1.0000 10.000 1.0814 0.02755 0.02029 0.0003 0.0151 1.0000 10.250 1.0915 0.02910 0.02195 0.0020 0.0138 1.0000 10.500 1.0981 0.03100 0.02402 0.0042 0.0129 1.0000 10.750 1.1063 0.03266 0.02591 0.0062 0.0122 1.0000 11.000 1.1123 0.03456 0.02802 0.0082 0.0115 1.0000 11.250 1.1165 0.03661 0.03028 0.0101 0.0109 1.0000 11.500 1.1196 0.03869 0.03258 0.0116 0.0104 1.0000 11.750 1.1216 0.04079 0.03485 0.0128 0.0099 1.0000 12.000 1.1226 0.04301 0.03722 0.0135 0.0094 1.0000 12.250 1.1207 0.04574 0.04009 0.0138 0.0091 1.0000 12.500 1.1130 0.04944 0.04397 0.0136 0.0087 1.0000 12.750 1.1046 0.05353 0.04829 0.0129 0.0085 1.0000 13.000 1.0975 0.05766 0.05267 0.0115 0.0083 1.0000 13.250 1.0872 0.06246 0.05771 0.0096 0.0082 1.0000 13.500 1.0742 0.06789 0.06336 0.0072 0.0081 1.0000 13.750 1.0590 0.07394 0.06962 0.0042 0.0080 1.0000 14.000 1.0419 0.08086 0.07674 0.0003 0.0080 1.0000 14.250 1.0235 0.08857 0.08462 -0.0043 0.0081 1.0000 14.500 1.0036 0.09713 0.09334 -0.0094 0.0082 1.0000 14.750 0.9828 0.10639 0.10274 -0.0148 0.0083 1.0000 15.000 0.9610 0.11630 0.11274 -0.0204 0.0085 1.0000