XFOIL Version 6.96 Calculated polar for: BOEING 707 .54 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3711 0.08576 0.08362 -0.0319 1.0000 0.0150 -9.250 -0.3722 0.08148 0.07935 -0.0337 1.0000 0.0150 -8.750 -0.4515 0.08300 0.08079 -0.0368 1.0000 0.0149 -8.500 -0.4599 0.07905 0.07683 -0.0401 1.0000 0.0150 -8.250 -0.4653 0.07563 0.07338 -0.0407 1.0000 0.0150 -8.000 -0.4675 0.07211 0.06981 -0.0410 1.0000 0.0150 -7.750 -0.4680 0.06888 0.06653 -0.0406 1.0000 0.0150 -7.500 -0.4847 0.06260 0.06023 -0.0396 1.0000 0.0154 -7.250 -0.4901 0.05984 0.05746 -0.0372 1.0000 0.0156 -7.000 -0.4817 0.05660 0.05418 -0.0377 0.9979 0.0158 -6.750 -0.4581 0.05264 0.05011 -0.0413 0.9934 0.0163 -6.500 -0.4334 0.04880 0.04612 -0.0445 0.9878 0.0169 -6.250 -0.4050 0.04493 0.04208 -0.0478 0.9836 0.0179 -6.000 -0.3768 0.04139 0.03830 -0.0498 0.9773 0.0196 -5.750 -0.3370 0.04016 0.03673 -0.0511 0.9729 0.0214 -5.500 -0.3059 0.03759 0.03386 -0.0528 0.9677 0.0216 -5.250 -0.2793 0.03483 0.03083 -0.0536 0.9591 0.0217 -5.000 -0.2628 0.02795 0.02364 -0.0543 0.9492 0.0229 -4.750 -0.2368 0.02579 0.02135 -0.0550 0.9412 0.0236 -4.500 -0.2140 0.02409 0.01948 -0.0545 0.9299 0.0245 -4.250 -0.1907 0.02255 0.01775 -0.0538 0.9193 0.0261 -4.000 -0.1659 0.02126 0.01623 -0.0530 0.9098 0.0283 -3.750 -0.1370 0.02231 0.01703 -0.0519 0.9004 0.0313 -3.500 -0.1175 0.01841 0.01275 -0.0506 0.8906 0.0330 -3.250 -0.0934 0.01688 0.01114 -0.0502 0.8823 0.0350 -3.000 -0.0685 0.01600 0.01017 -0.0497 0.8733 0.0379 -2.750 -0.0411 0.01684 0.01085 -0.0491 0.8651 0.0436 -2.500 -0.0173 0.01419 0.00808 -0.0487 0.8576 0.0485 -2.250 0.0089 0.01351 0.00733 -0.0482 0.8496 0.0528 -2.000 0.0383 0.01159 0.00518 -0.0467 0.8430 0.0273 -1.750 0.0631 0.01077 0.00431 -0.0459 0.8355 0.0265 -1.500 0.0878 0.01022 0.00369 -0.0451 0.8285 0.0274 -1.250 0.1127 0.00980 0.00323 -0.0445 0.8211 0.0286 -1.000 0.1384 0.00954 0.00291 -0.0440 0.8145 0.0304 -0.750 0.1640 0.00925 0.00260 -0.0435 0.8073 0.0320 -0.500 0.1888 0.00884 0.00208 -0.0428 0.7999 0.0357 -0.250 0.2145 0.00864 0.00183 -0.0423 0.7894 0.0421 0.000 0.2282 0.00689 0.00157 -0.0402 0.7770 0.5747 0.250 0.2402 0.00603 0.00162 -0.0363 0.7634 0.8293 0.500 0.2702 0.00588 0.00169 -0.0360 0.7493 0.9301 0.750 0.3132 0.00596 0.00171 -0.0391 0.7371 0.9597 1.000 0.3614 0.00607 0.00173 -0.0433 0.7185 0.9771 1.250 0.4030 0.00618 0.00166 -0.0463 0.6861 0.9861 1.500 0.4408 0.00625 0.00164 -0.0486 0.6636 0.9915 1.750 0.4782 0.00633 0.00163 -0.0508 0.6406 0.9964 2.000 0.5132 0.00646 0.00160 -0.0527 0.6047 1.0000 2.250 0.5326 0.00665 0.00159 -0.0511 0.5561 1.0000 2.500 0.5491 0.00711 0.00166 -0.0490 0.4659 1.0000 2.750 0.5647 0.00776 0.00188 -0.0470 0.3690 1.0000 3.000 0.5830 0.00826 0.00209 -0.0454 0.3050 1.0000 3.250 0.6032 0.00863 0.00228 -0.0442 0.2642 1.0000 3.500 0.6243 0.00894 0.00247 -0.0430 0.2334 1.0000 3.750 0.6449 0.00932 0.00268 -0.0418 0.1969 1.0000 4.000 0.6656 0.00970 0.00292 -0.0407 0.1615 1.0000 4.250 0.6861 0.01012 0.00318 -0.0395 0.1266 1.0000 4.500 0.7044 0.01074 0.00353 -0.0379 0.0686 1.0000 4.750 0.7256 0.01113 0.00388 -0.0368 0.0551 1.0000 5.000 0.7483 0.01140 0.00419 -0.0359 0.0482 1.0000 5.250 0.7701 0.01176 0.00457 -0.0348 0.0384 1.0000 5.500 0.7918 0.01213 0.00488 -0.0338 0.0289 1.0000 5.750 0.8136 0.01251 0.00527 -0.0328 0.0261 1.0000 6.000 0.8347 0.01299 0.00578 -0.0316 0.0233 1.0000 6.250 0.8543 0.01364 0.00654 -0.0302 0.0207 1.0000 6.500 0.8687 0.01482 0.00784 -0.0279 0.0166 1.0000 6.750 0.8849 0.01583 0.00895 -0.0259 0.0146 1.0000 7.000 0.9034 0.01661 0.00980 -0.0244 0.0134 1.0000 7.250 0.9214 0.01747 0.01072 -0.0229 0.0122 1.0000 7.500 0.9382 0.01851 0.01180 -0.0212 0.0115 1.0000 7.750 0.9533 0.02008 0.01339 -0.0194 0.0109 1.0000 8.000 0.9707 0.02206 0.01552 -0.0179 0.0103 1.0000 8.250 0.9906 0.02350 0.01711 -0.0167 0.0101 1.0000 8.500 1.0099 0.02530 0.01910 -0.0155 0.0100 1.0000 8.750 1.0278 0.02769 0.02171 -0.0142 0.0101 1.0000 9.000 1.0465 0.03230 0.02651 -0.0134 0.0107 1.0000 9.250 1.0620 0.03282 0.02724 -0.0115 0.0110 1.0000 16.500 0.8279 0.19801 0.19559 -0.0557 0.0127 1.0000 16.750 0.8337 0.20191 0.19949 -0.0578 0.0121 1.0000