XFOIL Version 6.96 Calculated polar for: BOEING 707 .99 SPAN 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4604 0.08815 0.08464 -0.0359 1.0000 0.0242 -8.500 -0.4659 0.08422 0.08074 -0.0388 1.0000 0.0242 -8.250 -0.4743 0.08108 0.07759 -0.0393 1.0000 0.0243 -6.750 -0.4889 0.05863 0.05486 -0.0358 1.0000 0.0258 -6.500 -0.4803 0.05571 0.05193 -0.0355 0.9983 0.0267 -6.250 -0.4572 0.05191 0.04799 -0.0384 0.9911 0.0279 -6.000 -0.4318 0.04816 0.04403 -0.0411 0.9835 0.0292 -5.750 -0.4069 0.04472 0.04032 -0.0429 0.9739 0.0310 -5.500 -0.3704 0.04447 0.03945 -0.0436 0.9644 0.0353 -5.250 -0.3428 0.04158 0.03622 -0.0448 0.9560 0.0355 -5.000 -0.3243 0.03563 0.02997 -0.0457 0.9446 0.0365 -4.750 -0.3007 0.03234 0.02671 -0.0472 0.9350 0.0387 -4.500 -0.2720 0.03033 0.02453 -0.0484 0.9262 0.0422 -4.250 -0.2369 0.03159 0.02518 -0.0482 0.9156 0.0484 -4.000 -0.2082 0.02937 0.02268 -0.0486 0.9057 0.0485 -3.500 -0.1470 0.02111 0.01366 -0.0484 0.8892 0.0241 -3.250 -0.1171 0.01954 0.01185 -0.0488 0.8807 0.0240 -3.000 -0.0867 0.01828 0.01036 -0.0492 0.8727 0.0241 -2.750 -0.0583 0.01715 0.00903 -0.0492 0.8642 0.0251 -2.500 -0.0302 0.01586 0.00767 -0.0494 0.8570 0.0267 -2.250 -0.0030 0.01509 0.00679 -0.0491 0.8494 0.0264 -2.000 0.0242 0.01440 0.00601 -0.0489 0.8428 0.0262 -1.750 0.0496 0.01382 0.00539 -0.0484 0.8352 0.0260 -1.500 0.0752 0.01330 0.00482 -0.0479 0.8290 0.0260 -1.250 0.0994 0.01285 0.00436 -0.0472 0.8220 0.0260 -1.000 0.1245 0.01247 0.00391 -0.0467 0.8163 0.0262 -0.750 0.1491 0.01216 0.00356 -0.0461 0.8097 0.0267 -0.500 0.1748 0.01194 0.00326 -0.0457 0.8037 0.0274 -0.250 0.2007 0.01179 0.00305 -0.0453 0.7979 0.0287 0.000 0.2266 0.01168 0.00288 -0.0449 0.7914 0.0310 0.250 0.2528 0.01160 0.00274 -0.0445 0.7845 0.0351 0.500 0.2662 0.01000 0.00265 -0.0423 0.7765 0.5465 0.750 0.2839 0.00909 0.00288 -0.0392 0.7678 0.8393 1.000 0.3408 0.00901 0.00291 -0.0447 0.7519 0.9375 1.250 0.3924 0.00900 0.00268 -0.0491 0.7048 0.9774 1.500 0.4252 0.00903 0.00251 -0.0501 0.6649 0.9866 1.750 0.4588 0.00913 0.00242 -0.0514 0.6294 0.9948 2.000 0.4888 0.00927 0.00238 -0.0520 0.5885 1.0000 2.250 0.5080 0.00948 0.00237 -0.0503 0.5377 1.0000 2.500 0.5233 0.00996 0.00240 -0.0479 0.4468 1.0000 2.750 0.5394 0.01052 0.00259 -0.0459 0.3717 1.0000 3.000 0.5563 0.01109 0.00286 -0.0440 0.3027 1.0000 3.250 0.5744 0.01161 0.00312 -0.0424 0.2527 1.0000 3.500 0.5937 0.01206 0.00338 -0.0410 0.2109 1.0000 3.750 0.6142 0.01243 0.00363 -0.0397 0.1802 1.0000 4.000 0.6347 0.01281 0.00389 -0.0385 0.1521 1.0000 4.250 0.6518 0.01350 0.00429 -0.0368 0.0897 1.0000 4.500 0.6701 0.01412 0.00471 -0.0352 0.0517 1.0000 4.750 0.6916 0.01446 0.00505 -0.0341 0.0491 1.0000 5.000 0.7133 0.01480 0.00541 -0.0331 0.0469 1.0000 5.250 0.7345 0.01520 0.00584 -0.0319 0.0429 1.0000 5.500 0.7553 0.01564 0.00638 -0.0308 0.0387 1.0000 5.750 0.7763 0.01609 0.00690 -0.0297 0.0367 1.0000 6.000 0.7966 0.01660 0.00750 -0.0285 0.0343 1.0000 6.250 0.8170 0.01711 0.00809 -0.0273 0.0309 1.0000 6.500 0.8385 0.01752 0.00861 -0.0263 0.0277 1.0000 6.750 0.8584 0.01808 0.00929 -0.0251 0.0249 1.0000 7.000 0.8789 0.01860 0.00995 -0.0240 0.0211 1.0000 7.250 0.8989 0.01917 0.01067 -0.0227 0.0165 1.0000 7.500 0.9192 0.01969 0.01124 -0.0215 0.0138 1.0000 8.000 0.9566 0.02102 0.01258 -0.0189 0.0106 1.0000 8.250 0.9720 0.02199 0.01367 -0.0171 0.0100 1.0000 8.500 0.9866 0.02303 0.01487 -0.0152 0.0097 1.0000 8.750 0.9999 0.02422 0.01618 -0.0132 0.0092 1.0000 9.000 1.0125 0.02552 0.01760 -0.0111 0.0089 1.0000 9.250 1.0243 0.02699 0.01921 -0.0090 0.0086 1.0000 9.500 1.0359 0.02864 0.02102 -0.0069 0.0085 1.0000 9.750 1.0468 0.03046 0.02302 -0.0048 0.0083 1.0000 10.000 1.0559 0.03276 0.02557 -0.0026 0.0082 1.0000 10.250 1.0631 0.03510 0.02819 -0.0003 0.0081 1.0000 10.500 1.0672 0.03752 0.03093 0.0023 0.0081 1.0000 10.750 1.0665 0.04027 0.03399 0.0051 0.0081 1.0000 11.000 1.0621 0.04313 0.03715 0.0079 0.0080 1.0000 11.250 1.0561 0.04593 0.04022 0.0103 0.0081 1.0000 11.500 1.0448 0.04930 0.04388 0.0124 0.0080 1.0000 11.750 1.0346 0.05257 0.04739 0.0137 0.0081 1.0000 12.000 1.0207 0.05645 0.05151 0.0143 0.0081 1.0000 12.250 1.0065 0.06059 0.05587 0.0141 0.0081 1.0000 12.500 0.9897 0.06550 0.06099 0.0130 0.0081 1.0000 12.750 0.9741 0.07071 0.06640 0.0110 0.0082 1.0000 13.000 0.9542 0.07720 0.07307 0.0076 0.0081 1.0000 13.250 0.9374 0.08407 0.08011 0.0033 0.0082 1.0000 13.500 0.9156 0.09337 0.08960 -0.0028 0.0083 1.0000