XFOIL Version 6.96 Calculated polar for: BOEING 707 .40 SPAN 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4754 0.09081 0.08837 -0.0265 1.0000 0.0129 -9.250 -0.4751 0.08729 0.08487 -0.0279 1.0000 0.0130 -9.000 -0.4772 0.08330 0.08091 -0.0301 1.0000 0.0130 -8.750 -0.4827 0.07890 0.07654 -0.0333 1.0000 0.0130 -8.500 -0.4984 0.07437 0.07202 -0.0365 1.0000 0.0130 -8.250 -0.5109 0.07099 0.06862 -0.0361 1.0000 0.0130 -8.000 -0.5169 0.06793 0.06552 -0.0354 1.0000 0.0130 -7.750 -0.5056 0.06379 0.06129 -0.0386 0.9943 0.0132 -7.500 -0.4922 0.05981 0.05721 -0.0413 0.9876 0.0133 -7.250 -0.4762 0.05608 0.05336 -0.0436 0.9796 0.0136 -7.000 -0.4569 0.05230 0.04943 -0.0460 0.9712 0.0138 -6.750 -0.4334 0.04861 0.04558 -0.0486 0.9616 0.0143 -6.500 -0.4093 0.04517 0.04195 -0.0505 0.9503 0.0148 -6.250 -0.3764 0.04218 0.03855 -0.0510 0.9376 0.0163 -6.000 -0.3502 0.03889 0.03498 -0.0519 0.9200 0.0163 -5.750 -0.3263 0.03606 0.03188 -0.0523 0.8946 0.0164 -5.500 -0.3129 0.03199 0.02753 -0.0516 0.8619 0.0168 -5.250 -0.2961 0.03041 0.02567 -0.0505 0.8058 0.0171 -5.000 -0.2803 0.02913 0.02400 -0.0487 0.7391 0.0174 -4.750 -0.2623 0.02783 0.02239 -0.0471 0.6930 0.0178 -4.500 -0.2421 0.02660 0.02089 -0.0459 0.6645 0.0186 -4.250 -0.2135 0.02727 0.02122 -0.0444 0.6430 0.0213 -3.750 -0.1748 0.02075 0.01415 -0.0416 0.6169 0.0150 -3.500 -0.1502 0.01773 0.01068 -0.0398 0.6067 0.0129 -3.000 -0.1012 0.01570 0.00820 -0.0381 0.5498 0.0123 -2.750 -0.0776 0.01468 0.00691 -0.0372 0.5018 0.0122 -2.500 -0.0552 0.01401 0.00589 -0.0360 0.4339 0.0121 -2.250 -0.0330 0.01344 0.00504 -0.0349 0.3794 0.0121 -2.000 -0.0149 0.01357 0.00456 -0.0333 0.2139 0.0121 -1.750 0.0084 0.01310 0.00399 -0.0324 0.2006 0.0122 -1.500 0.0318 0.01277 0.00350 -0.0315 0.1731 0.0124 -1.250 0.0534 0.01279 0.00314 -0.0304 0.0392 0.0126 -1.000 0.0780 0.01251 0.00282 -0.0298 0.0336 0.0132 -0.750 0.1035 0.01237 0.00265 -0.0293 0.0304 0.0138 -0.500 0.1292 0.01228 0.00254 -0.0289 0.0284 0.0146 -0.250 0.1551 0.01222 0.00245 -0.0285 0.0273 0.0155 0.000 0.1811 0.01218 0.00242 -0.0281 0.0265 0.0174 0.250 0.2073 0.01217 0.00242 -0.0278 0.0261 0.0206 0.500 0.2334 0.01215 0.00241 -0.0275 0.0256 0.0247 0.750 0.2596 0.01218 0.00242 -0.0272 0.0251 0.0295 1.000 0.2857 0.01220 0.00243 -0.0269 0.0247 0.0347 1.250 0.3119 0.01223 0.00244 -0.0266 0.0233 0.0395 1.500 0.3380 0.01229 0.00245 -0.0263 0.0219 0.0442 1.750 0.3637 0.01226 0.00251 -0.0259 0.0208 0.1012 2.000 0.3887 0.01215 0.00258 -0.0255 0.0199 0.1941 2.250 0.4112 0.01178 0.00272 -0.0248 0.0166 0.4016 2.500 0.4333 0.01152 0.00279 -0.0240 0.0130 0.5019 2.750 0.4525 0.01102 0.00285 -0.0224 0.0122 0.7067 3.000 0.4754 0.01098 0.00300 -0.0214 0.0120 0.7602 3.250 0.4976 0.01098 0.00320 -0.0201 0.0118 0.8112 3.500 0.5212 0.01108 0.00342 -0.0193 0.0118 0.8415 3.750 0.5454 0.01122 0.00365 -0.0185 0.0117 0.8681 4.000 0.5710 0.01138 0.00389 -0.0181 0.0116 0.8948 4.250 0.6031 0.01161 0.00419 -0.0191 0.0116 0.9285 4.500 0.6418 0.01190 0.00451 -0.0218 0.0115 0.9528 4.750 0.6786 0.01222 0.00484 -0.0240 0.0115 0.9706 5.000 0.7140 0.01254 0.00518 -0.0260 0.0115 0.9865 5.250 0.7501 0.01292 0.00556 -0.0282 0.0114 0.9995 5.500 0.7715 0.01330 0.00596 -0.0271 0.0112 1.0000 5.750 0.7916 0.01371 0.00640 -0.0258 0.0109 1.0000 6.000 0.8127 0.01405 0.00675 -0.0246 0.0109 1.0000 6.250 0.8330 0.01447 0.00720 -0.0233 0.0108 1.0000 6.500 0.8536 0.01488 0.00762 -0.0221 0.0108 1.0000 6.750 0.8733 0.01538 0.00814 -0.0208 0.0107 1.0000 7.000 0.8935 0.01583 0.00863 -0.0196 0.0107 1.0000 7.250 0.9123 0.01642 0.00923 -0.0182 0.0106 1.0000 7.500 0.9300 0.01709 0.00992 -0.0167 0.0105 1.0000 7.750 0.9492 0.01764 0.01048 -0.0154 0.0105 1.0000 8.000 0.9664 0.01835 0.01122 -0.0139 0.0104 1.0000 8.250 0.9850 0.01894 0.01186 -0.0125 0.0104 1.0000 8.500 1.0026 0.01961 0.01256 -0.0111 0.0103 1.0000 8.750 1.0199 0.02031 0.01329 -0.0096 0.0103 1.0000 9.000 1.0366 0.02104 0.01408 -0.0081 0.0103 1.0000 9.250 1.0530 0.02181 0.01490 -0.0065 0.0102 1.0000 9.500 1.0688 0.02262 0.01575 -0.0049 0.0102 1.0000 9.750 1.0837 0.02350 0.01671 -0.0032 0.0101 1.0000 10.000 1.0976 0.02433 0.01758 -0.0014 0.0102 1.0000 10.250 1.1101 0.02526 0.01861 0.0007 0.0101 1.0000 10.500 1.1226 0.02621 0.01963 0.0026 0.0101 1.0000 10.750 1.1344 0.02723 0.02074 0.0045 0.0101 1.0000 11.000 1.1458 0.02828 0.02188 0.0064 0.0102 1.0000 11.250 1.1562 0.02948 0.02318 0.0083 0.0101 1.0000 11.500 1.1658 0.03070 0.02451 0.0101 0.0102 1.0000 11.750 1.1744 0.03203 0.02597 0.0119 0.0102 1.0000 12.000 1.1811 0.03352 0.02760 0.0137 0.0102 1.0000 12.250 1.1865 0.03495 0.02917 0.0154 0.0102 1.0000 12.500 1.1892 0.03685 0.03123 0.0172 0.0102 1.0000 12.750 1.1901 0.03867 0.03323 0.0186 0.0101 1.0000 13.000 1.1898 0.04082 0.03555 0.0199 0.0101 1.0000 13.250 1.1871 0.04328 0.03820 0.0208 0.0100 1.0000 13.500 1.1827 0.04609 0.04119 0.0213 0.0100 1.0000 13.750 1.1765 0.04925 0.04454 0.0213 0.0099 1.0000 14.000 1.1701 0.05263 0.04810 0.0208 0.0099 1.0000 14.250 1.1628 0.05635 0.05198 0.0200 0.0100 1.0000 14.500 1.1510 0.06084 0.05666 0.0186 0.0100 1.0000 14.750 1.1363 0.06598 0.06200 0.0166 0.0099 1.0000 15.000 1.1235 0.07115 0.06734 0.0142 0.0099 1.0000 15.250 1.1078 0.07716 0.07352 0.0112 0.0100 1.0000 15.500 1.0898 0.08407 0.08060 0.0074 0.0100 1.0000 15.750 1.0696 0.09205 0.08876 0.0026 0.0100 1.0000 16.000 1.0475 0.10104 0.09792 -0.0029 0.0101 1.0000 16.250 1.0228 0.11162 0.10867 -0.0095 0.0101 1.0000 16.500 0.9863 0.12639 0.12364 -0.0184 0.0102 1.0000