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 = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.5373 0.10856 0.10190 -0.0173 1.0000 0.1258 -9.250 -0.5181 0.10461 0.09793 -0.0146 1.0000 0.1309 -9.000 -0.5372 0.10086 0.09430 -0.0208 1.0000 0.1386 -8.750 -0.5249 0.09661 0.09009 -0.0192 1.0000 0.1436 -8.500 -0.5258 0.09277 0.08630 -0.0211 1.0000 0.1502 -8.250 -0.5328 0.08860 0.08223 -0.0233 1.0000 0.1591 -7.250 -0.5381 0.06778 0.06057 -0.0345 1.0000 0.0641 -7.000 -0.5307 0.06372 0.05649 -0.0338 1.0000 0.0598 -6.750 -0.5292 0.06149 0.05345 -0.0317 1.0000 0.0514 -6.500 -0.5196 0.05725 0.04933 -0.0307 1.0000 0.0498 -6.250 -0.5133 0.05419 0.04616 -0.0290 1.0000 0.0486 -6.000 -0.5070 0.05145 0.04323 -0.0269 1.0000 0.0474 -5.750 -0.5001 0.04890 0.04041 -0.0246 1.0000 0.0463 -5.500 -0.4921 0.04651 0.03775 -0.0222 1.0000 0.0454 -5.250 -0.4826 0.04431 0.03526 -0.0199 1.0000 0.0452 -5.000 -0.4714 0.04227 0.03291 -0.0178 1.0000 0.0456 -4.750 -0.4583 0.04035 0.03066 -0.0159 1.0000 0.0464 -4.500 -0.4433 0.03850 0.02848 -0.0141 1.0000 0.0471 -4.250 -0.4263 0.03670 0.02636 -0.0125 1.0000 0.0475 -4.000 -0.3994 0.03469 0.02398 -0.0125 0.9970 0.0475 -3.750 -0.3645 0.03266 0.02154 -0.0138 0.9915 0.0476 -3.500 -0.3283 0.03088 0.01943 -0.0151 0.9866 0.0484 -3.250 -0.2933 0.02967 0.01788 -0.0160 0.9809 0.0512 -3.000 -0.2588 0.02800 0.01626 -0.0171 0.9766 0.0556 -2.750 -0.2254 0.02690 0.01501 -0.0178 0.9712 0.0588 -2.500 -0.1930 0.02600 0.01390 -0.0186 0.9656 0.0639 -2.250 -0.1614 0.02499 0.01281 -0.0199 0.9596 0.0733 -2.000 -0.1317 0.02420 0.01181 -0.0207 0.9526 0.0822 -1.500 -0.0909 0.02042 0.01086 -0.0183 0.9407 0.7122 -1.250 -0.0017 0.02165 0.01219 -0.0212 0.9504 0.9638 -1.000 0.0454 0.02159 0.01178 -0.0260 0.9451 0.9719 -0.750 0.0909 0.02154 0.01148 -0.0306 0.9389 0.9803 -0.500 0.1375 0.02149 0.01124 -0.0354 0.9332 0.9887 -0.250 0.1820 0.02145 0.01104 -0.0398 0.9264 0.9977 0.000 0.2118 0.02148 0.01096 -0.0414 0.9176 1.0000 0.250 0.2407 0.02152 0.01091 -0.0427 0.9093 1.0000 0.500 0.2597 0.02165 0.01098 -0.0420 0.8981 1.0000 0.750 0.2815 0.02178 0.01105 -0.0418 0.8879 1.0000 1.000 0.3115 0.02184 0.01107 -0.0427 0.8794 1.0000 1.250 0.3306 0.02202 0.01121 -0.0417 0.8673 1.0000 1.500 0.3518 0.02218 0.01135 -0.0408 0.8554 1.0000 1.750 0.3753 0.02232 0.01148 -0.0403 0.8437 1.0000 2.000 0.4006 0.02243 0.01159 -0.0399 0.8322 1.0000 2.250 0.4284 0.02248 0.01164 -0.0397 0.8209 1.0000 2.500 0.4517 0.02260 0.01181 -0.0387 0.8081 1.0000 2.750 0.4733 0.02278 0.01203 -0.0376 0.7951 1.0000 3.000 0.4955 0.02298 0.01228 -0.0366 0.7827 1.0000 3.250 0.5190 0.02315 0.01253 -0.0356 0.7703 1.0000 3.500 0.5432 0.02324 0.01273 -0.0347 0.7567 1.0000 3.750 0.5673 0.02318 0.01276 -0.0333 0.7399 1.0000 4.000 0.5925 0.02296 0.01263 -0.0318 0.7212 1.0000 4.250 0.6160 0.02277 0.01254 -0.0301 0.7008 1.0000 4.500 0.6378 0.02270 0.01262 -0.0283 0.6789 1.0000 4.750 0.6617 0.02254 0.01258 -0.0267 0.6577 1.0000 5.000 0.6828 0.02252 0.01270 -0.0250 0.6321 1.0000 5.250 0.7044 0.02248 0.01279 -0.0232 0.6030 1.0000 5.500 0.7265 0.02242 0.01287 -0.0214 0.5691 1.0000 5.750 0.7481 0.02242 0.01291 -0.0195 0.5281 1.0000 6.000 0.7692 0.02256 0.01296 -0.0175 0.4801 1.0000 6.250 0.7885 0.02300 0.01319 -0.0155 0.4292 1.0000 6.500 0.8056 0.02376 0.01376 -0.0136 0.3808 1.0000 6.750 0.8213 0.02473 0.01451 -0.0118 0.3378 1.0000 7.000 0.8366 0.02584 0.01545 -0.0101 0.3013 1.0000 7.250 0.8518 0.02697 0.01654 -0.0086 0.2658 1.0000 7.500 0.8658 0.02808 0.01760 -0.0070 0.2317 1.0000 7.750 0.8785 0.02931 0.01873 -0.0055 0.1982 1.0000 8.000 0.8902 0.03070 0.02006 -0.0039 0.1670 1.0000 8.250 0.9020 0.03223 0.02152 -0.0023 0.1387 1.0000 8.500 0.9139 0.03382 0.02307 -0.0008 0.1153 1.0000 8.750 0.9277 0.03552 0.02479 0.0006 0.0982 1.0000 9.000 0.9416 0.03723 0.02654 0.0019 0.0851 1.0000 9.250 0.9566 0.03906 0.02843 0.0032 0.0759 1.0000 9.500 0.9745 0.04104 0.03059 0.0042 0.0695 1.0000 9.750 0.9925 0.04328 0.03300 0.0052 0.0642 1.0000 10.000 1.0060 0.04543 0.03543 0.0063 0.0588 1.0000 10.250 1.0193 0.04771 0.03772 0.0073 0.0553 1.0000 10.500 1.0320 0.05083 0.04125 0.0085 0.0532 1.0000 10.750 1.0365 0.05410 0.04498 0.0102 0.0516 1.0000 11.000 1.0346 0.05739 0.04865 0.0119 0.0500 1.0000 11.250 1.0292 0.06071 0.05227 0.0134 0.0486 1.0000 11.500 1.0210 0.06415 0.05597 0.0144 0.0473 1.0000 11.750 1.0112 0.06782 0.05986 0.0148 0.0462 1.0000 12.000 0.9995 0.07188 0.06411 0.0146 0.0454 1.0000 12.250 0.9840 0.07666 0.06911 0.0137 0.0451 1.0000 12.500 0.9580 0.08332 0.07604 0.0110 0.0456 1.0000 12.750 0.9117 0.09485 0.08786 0.0040 0.0483 1.0000