XFOIL Version 6.96 Calculated polar for: BOEING 707 .08 SPAN AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.7996 0.10558 0.09960 -0.0053 1.0000 0.0277 -13.500 -0.8408 0.09306 0.08691 -0.0131 1.0000 0.0273 -13.250 -0.8778 0.08303 0.07668 -0.0193 1.0000 0.0270 -13.000 -0.9076 0.07510 0.06852 -0.0238 1.0000 0.0268 -12.750 -0.9328 0.06844 0.06162 -0.0271 1.0000 0.0267 -12.500 -0.9525 0.06301 0.05594 -0.0292 1.0000 0.0267 -12.250 -0.9677 0.05843 0.05112 -0.0303 1.0000 0.0266 -12.000 -0.9795 0.05450 0.04694 -0.0305 1.0000 0.0267 -11.750 -0.9874 0.05108 0.04328 -0.0301 1.0000 0.0268 -11.500 -0.9919 0.04807 0.04003 -0.0291 1.0000 0.0270 -11.250 -0.9921 0.04545 0.03719 -0.0277 1.0000 0.0272 -11.000 -0.9892 0.04302 0.03452 -0.0261 1.0000 0.0275 -10.750 -0.9826 0.04082 0.03213 -0.0244 1.0000 0.0278 -10.500 -0.9739 0.03890 0.03004 -0.0226 1.0000 0.0282 -10.250 -0.9663 0.03764 0.02873 -0.0206 1.0000 0.0285 -10.000 -0.9580 0.03651 0.02754 -0.0185 1.0000 0.0290 -9.750 -0.9471 0.03539 0.02634 -0.0166 1.0000 0.0299 -9.500 -0.9340 0.03409 0.02493 -0.0149 1.0000 0.0308 -9.250 -0.9202 0.03282 0.02356 -0.0132 1.0000 0.0322 -9.000 -0.9067 0.03196 0.02266 -0.0114 1.0000 0.0332 -8.750 -0.8920 0.03091 0.02153 -0.0097 1.0000 0.0348 -8.500 -0.8767 0.02981 0.02036 -0.0079 1.0000 0.0365 -8.250 -0.8616 0.02891 0.01945 -0.0061 1.0000 0.0383 -8.000 -0.8467 0.02785 0.01831 -0.0041 1.0000 0.0411 -7.750 -0.8316 0.02698 0.01739 -0.0022 1.0000 0.0444 -7.500 -0.8160 0.02616 0.01651 -0.0004 1.0000 0.0487 -7.250 -0.7999 0.02539 0.01568 0.0015 1.0000 0.0533 -7.000 -0.7826 0.02473 0.01491 0.0033 1.0000 0.0582 -6.750 -0.7661 0.02405 0.01423 0.0050 1.0000 0.0630 -6.500 -0.7492 0.02337 0.01353 0.0067 1.0000 0.0678 -6.250 -0.7308 0.02281 0.01289 0.0083 1.0000 0.0728 -6.000 -0.7147 0.02206 0.01218 0.0101 1.0000 0.0774 -5.750 -0.6959 0.02152 0.01156 0.0116 1.0000 0.0819 -5.500 -0.6792 0.02078 0.01085 0.0134 1.0000 0.0860 -5.250 -0.6602 0.02022 0.01025 0.0149 1.0000 0.0906 -5.000 -0.6417 0.01956 0.00959 0.0164 1.0000 0.0958 -4.750 -0.6220 0.01900 0.00901 0.0178 1.0000 0.1019 -4.500 -0.6024 0.01837 0.00843 0.0192 1.0000 0.1088 -4.250 -0.5818 0.01781 0.00790 0.0205 1.0000 0.1169 -4.000 -0.5617 0.01712 0.00734 0.0218 1.0000 0.1345 -3.750 -0.5456 0.01578 0.00653 0.0233 1.0000 0.2450 -3.500 -0.5280 0.01527 0.00668 0.0251 1.0000 0.3834 -3.250 -0.5046 0.01522 0.00659 0.0262 1.0000 0.4083 -3.000 -0.4809 0.01516 0.00646 0.0273 1.0000 0.4248 -2.750 -0.4576 0.01510 0.00640 0.0284 1.0000 0.4400 -2.500 -0.4340 0.01501 0.00633 0.0295 1.0000 0.4503 -2.250 -0.4001 0.01501 0.00625 0.0283 0.9937 0.4638 -2.000 -0.3591 0.01491 0.00623 0.0258 0.9797 0.4731 -1.750 -0.3211 0.01482 0.00609 0.0240 0.9585 0.4832 -1.250 -0.1997 0.01466 0.00565 0.0122 0.7295 0.5085 -1.000 -0.1687 0.01504 0.00557 0.0123 0.6079 0.5194 -0.750 -0.1438 0.01532 0.00551 0.0132 0.5388 0.5285 -0.500 -0.1175 0.01544 0.00550 0.0138 0.4919 0.5357 -0.250 -0.0903 0.01553 0.00543 0.0141 0.4458 0.5410 0.000 -0.0630 0.01565 0.00533 0.0143 0.4080 0.5450 0.250 -0.0357 0.01577 0.00527 0.0146 0.3853 0.5486 0.500 -0.0087 0.01589 0.00528 0.0149 0.3699 0.5525 0.750 0.0184 0.01603 0.00535 0.0152 0.3573 0.5567 1.000 0.0456 0.01617 0.00545 0.0155 0.3466 0.5611 1.250 0.0726 0.01641 0.00558 0.0158 0.3366 0.5659 1.500 0.0999 0.01653 0.00575 0.0161 0.3263 0.5708 1.750 0.1269 0.01672 0.00597 0.0165 0.3162 0.5766 2.000 0.1539 0.01697 0.00619 0.0168 0.3056 0.5838 2.250 0.1809 0.01709 0.00640 0.0171 0.2927 0.5920 2.500 0.2078 0.01714 0.00658 0.0175 0.2789 0.6024 2.750 0.2348 0.01706 0.00674 0.0179 0.2616 0.6151 3.000 0.2617 0.01693 0.00683 0.0184 0.2409 0.6321 3.250 0.2874 0.01679 0.00678 0.0191 0.2265 0.6544 3.500 0.3123 0.01675 0.00677 0.0200 0.2136 0.6846 3.750 0.3370 0.01684 0.00696 0.0209 0.2012 0.7243 4.000 0.3627 0.01702 0.00729 0.0216 0.1892 0.7743 4.250 0.3955 0.01727 0.00774 0.0211 0.1775 0.8346 4.500 0.4420 0.01767 0.00828 0.0176 0.1648 0.8991 4.750 0.4851 0.01808 0.00875 0.0145 0.1524 0.9497 5.000 0.5246 0.01849 0.00917 0.0121 0.1392 0.9818 5.250 0.5605 0.01892 0.00959 0.0103 0.1270 1.0000 5.500 0.5821 0.01934 0.01001 0.0114 0.1181 1.0000 5.750 0.6034 0.01981 0.01046 0.0126 0.1105 1.0000 6.000 0.6246 0.02028 0.01090 0.0137 0.1043 1.0000 6.250 0.6462 0.02076 0.01143 0.0149 0.0975 1.0000 6.500 0.6674 0.02125 0.01192 0.0160 0.0927 1.0000 6.750 0.6889 0.02179 0.01254 0.0172 0.0884 1.0000 7.000 0.7100 0.02231 0.01307 0.0183 0.0853 1.0000 7.250 0.7314 0.02288 0.01374 0.0194 0.0818 1.0000 7.500 0.7526 0.02342 0.01432 0.0205 0.0786 1.0000 7.750 0.7734 0.02403 0.01498 0.0216 0.0764 1.0000 8.000 0.7941 0.02470 0.01577 0.0228 0.0743 1.0000 8.250 0.8145 0.02533 0.01648 0.0239 0.0719 1.0000 8.500 0.8344 0.02601 0.01720 0.0250 0.0696 1.0000 8.750 0.8540 0.02680 0.01815 0.0262 0.0676 1.0000 9.000 0.8731 0.02759 0.01904 0.0273 0.0657 1.0000 9.250 0.8913 0.02838 0.01988 0.0285 0.0633 1.0000 9.500 0.9091 0.02934 0.02102 0.0298 0.0607 1.0000 9.750 0.9256 0.03027 0.02204 0.0310 0.0583 1.0000 10.000 0.9409 0.03138 0.02333 0.0323 0.0553 1.0000 10.250 0.9545 0.03250 0.02453 0.0337 0.0522 1.0000 10.500 0.9668 0.03387 0.02615 0.0351 0.0484 1.0000 10.750 0.9768 0.03530 0.02776 0.0366 0.0457 1.0000 11.000 0.9845 0.03692 0.02961 0.0382 0.0427 1.0000 11.250 0.9880 0.03885 0.03180 0.0398 0.0397 1.0000 11.500 0.9864 0.04085 0.03397 0.0417 0.0376 1.0000 11.750 0.9758 0.04354 0.03688 0.0437 0.0364 1.0000 12.000 0.9578 0.04744 0.04101 0.0437 0.0352 1.0000 12.250 0.9250 0.05532 0.04913 0.0377 0.0362 1.0000 12.500 0.8870 0.06624 0.06020 0.0292 0.0374 1.0000 12.750 0.8384 0.07818 0.07233 0.0217 0.0386 1.0000 13.000 0.7552 0.09773 0.09205 0.0104 0.0395 1.0000 13.250 0.7204 0.10881 0.10312 0.0046 0.0378 1.0000