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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5229 0.08769 0.08429 -0.0208 1.0000 0.0227 -8.750 -0.5273 0.08185 0.07848 -0.0266 1.0000 0.0228 -8.500 -0.5358 0.07678 0.07340 -0.0310 1.0000 0.0227 -8.250 -0.5427 0.07267 0.06923 -0.0328 1.0000 0.0228 -8.000 -0.5445 0.06866 0.06515 -0.0341 1.0000 0.0231 -7.750 -0.5436 0.06486 0.06125 -0.0348 1.0000 0.0234 -7.500 -0.5406 0.06124 0.05752 -0.0350 1.0000 0.0237 -7.250 -0.5363 0.05784 0.05399 -0.0345 1.0000 0.0241 -7.000 -0.5277 0.05438 0.05037 -0.0344 0.9951 0.0247 -6.500 -0.4846 0.04419 0.03945 -0.0372 0.9651 0.0188 -6.250 -0.4631 0.04035 0.03531 -0.0380 0.9525 0.0178 -6.000 -0.4400 0.03702 0.03164 -0.0382 0.9406 0.0179 -5.750 -0.4160 0.03415 0.02837 -0.0378 0.9293 0.0189 -5.500 -0.3933 0.03135 0.02524 -0.0373 0.9186 0.0186 -5.000 -0.3469 0.02630 0.01952 -0.0357 0.8990 0.0173 -4.750 -0.3222 0.02406 0.01694 -0.0348 0.8905 0.0168 -4.500 -0.2969 0.02206 0.01461 -0.0339 0.8821 0.0165 -4.250 -0.2711 0.02036 0.01262 -0.0331 0.8744 0.0164 -4.000 -0.2452 0.01896 0.01099 -0.0324 0.8671 0.0165 -3.750 -0.2194 0.01777 0.00965 -0.0318 0.8599 0.0167 -3.500 -0.1941 0.01676 0.00851 -0.0311 0.8530 0.0172 -3.250 -0.1692 0.01587 0.00753 -0.0304 0.8462 0.0179 -3.000 -0.1447 0.01509 0.00666 -0.0297 0.8396 0.0189 -2.750 -0.1200 0.01449 0.00597 -0.0291 0.8334 0.0202 -2.500 -0.0958 0.01385 0.00535 -0.0286 0.8267 0.0237 -2.250 -0.0705 0.01345 0.00485 -0.0281 0.8214 0.0274 -2.000 -0.0450 0.01301 0.00438 -0.0278 0.8143 0.0334 -1.750 -0.0189 0.01271 0.00396 -0.0274 0.8083 0.0391 -1.500 0.0070 0.01233 0.00361 -0.0272 0.8016 0.0593 -1.250 0.0195 0.01009 0.00323 -0.0253 0.7948 0.5804 -1.000 0.0428 0.00986 0.00325 -0.0241 0.7883 0.6773 -0.750 0.0655 0.00972 0.00333 -0.0226 0.7813 0.7470 -0.500 0.0892 0.00967 0.00337 -0.0212 0.7752 0.7877 -0.250 0.1150 0.00965 0.00336 -0.0205 0.7678 0.8077 0.000 0.1418 0.00964 0.00328 -0.0202 0.7615 0.8201 0.250 0.1691 0.00963 0.00325 -0.0200 0.7538 0.8291 0.500 0.1962 0.00963 0.00320 -0.0197 0.7477 0.8393 0.750 0.2235 0.00963 0.00320 -0.0196 0.7397 0.8507 1.000 0.2508 0.00964 0.00319 -0.0194 0.7341 0.8622 1.250 0.2783 0.00965 0.00323 -0.0193 0.7275 0.8742 1.500 0.3061 0.00967 0.00325 -0.0192 0.7205 0.8870 1.750 0.3344 0.00969 0.00328 -0.0192 0.7116 0.9002 2.000 0.3633 0.00970 0.00328 -0.0193 0.7012 0.9137 2.250 0.3932 0.00971 0.00327 -0.0196 0.6875 0.9270 2.500 0.4245 0.00972 0.00328 -0.0203 0.6716 0.9399 2.750 0.4569 0.00975 0.00331 -0.0213 0.6572 0.9523 3.000 0.4904 0.00980 0.00336 -0.0225 0.6436 0.9639 3.250 0.5245 0.00985 0.00344 -0.0240 0.6270 0.9748 3.500 0.5591 0.00992 0.00352 -0.0256 0.6077 0.9851 3.750 0.5939 0.01002 0.00358 -0.0273 0.5829 0.9946 4.000 0.6249 0.01015 0.00365 -0.0282 0.5497 1.0000 4.250 0.6465 0.01038 0.00376 -0.0271 0.5093 1.0000 4.500 0.6667 0.01077 0.00390 -0.0258 0.4556 1.0000 4.750 0.6864 0.01128 0.00415 -0.0246 0.4015 1.0000 5.000 0.7062 0.01185 0.00448 -0.0235 0.3471 1.0000 5.250 0.7267 0.01241 0.00487 -0.0225 0.3125 1.0000 5.500 0.7486 0.01289 0.00527 -0.0218 0.2858 1.0000 5.750 0.7711 0.01333 0.00565 -0.0211 0.2556 1.0000 6.000 0.7922 0.01390 0.00605 -0.0203 0.2161 1.0000 6.250 0.8127 0.01456 0.00653 -0.0195 0.1802 1.0000 6.500 0.8342 0.01515 0.00702 -0.0189 0.1543 1.0000 6.750 0.8559 0.01571 0.00751 -0.0182 0.1318 1.0000 7.000 0.8779 0.01627 0.00802 -0.0176 0.1088 1.0000 7.250 0.8986 0.01694 0.00860 -0.0169 0.0845 1.0000 7.500 0.9183 0.01774 0.00932 -0.0160 0.0626 1.0000 7.750 0.9378 0.01858 0.01009 -0.0151 0.0474 1.0000 8.000 0.9574 0.01939 0.01094 -0.0141 0.0395 1.0000 8.250 0.9761 0.02028 0.01186 -0.0131 0.0344 1.0000 8.500 0.9944 0.02118 0.01285 -0.0120 0.0314 1.0000 8.750 1.0130 0.02201 0.01381 -0.0109 0.0285 1.0000 9.000 1.0300 0.02296 0.01484 -0.0098 0.0262 1.0000 9.250 1.0426 0.02431 0.01627 -0.0081 0.0244 1.0000 9.500 1.0580 0.02538 0.01747 -0.0067 0.0234 1.0000 9.750 1.0734 0.02642 0.01865 -0.0054 0.0219 1.0000 10.000 1.0871 0.02747 0.01982 -0.0039 0.0204 1.0000 10.250 1.0986 0.02865 0.02110 -0.0022 0.0193 1.0000 10.500 1.1084 0.03003 0.02260 -0.0005 0.0184 1.0000 10.750 1.1147 0.03190 0.02455 0.0014 0.0175 1.0000 11.000 1.1240 0.03354 0.02635 0.0029 0.0167 1.0000 11.250 1.1338 0.03502 0.02804 0.0043 0.0158 1.0000 11.500 1.1417 0.03669 0.02991 0.0056 0.0149 1.0000 11.750 1.1477 0.03862 0.03202 0.0068 0.0143 1.0000 12.000 1.1521 0.04071 0.03427 0.0080 0.0138 1.0000 12.250 1.1550 0.04294 0.03666 0.0089 0.0134 1.0000 12.500 1.1563 0.04536 0.03925 0.0097 0.0130 1.0000 12.750 1.1555 0.04807 0.04211 0.0103 0.0127 1.0000 13.000 1.1523 0.05118 0.04538 0.0107 0.0124 1.0000 13.250 1.1455 0.05485 0.04924 0.0108 0.0122 1.0000 13.500 1.1344 0.05924 0.05385 0.0106 0.0120 1.0000 13.750 1.1234 0.06372 0.05858 0.0096 0.0119 1.0000 14.000 1.1110 0.06863 0.06373 0.0081 0.0118 1.0000 14.250 1.0967 0.07412 0.06945 0.0058 0.0117 1.0000 14.500 1.0805 0.08032 0.07586 0.0028 0.0117 1.0000 14.750 1.0631 0.08729 0.08304 -0.0010 0.0117 1.0000 15.000 1.0444 0.09510 0.09100 -0.0056 0.0117 1.0000 15.250 1.0245 0.10378 0.09986 -0.0108 0.0118 1.0000 15.500 1.0036 0.11318 0.10941 -0.0165 0.0119 1.0000 15.750 0.9816 0.12327 0.11962 -0.0225 0.0120 1.0000 16.000 0.6852 0.13329 0.13007 -0.0133 0.0157 1.0000