XFOIL Version 6.96 Calculated polar for: BOEING HSNLF 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5442 0.09251 0.08742 -0.0403 1.0014 0.0184 -9.500 -0.5509 0.08723 0.08220 -0.0429 1.0014 0.0180 -9.250 -0.5617 0.08167 0.07667 -0.0459 1.0014 0.0177 -9.000 -0.5772 0.07699 0.07202 -0.0476 1.0014 0.0175 -8.750 -0.5971 0.07337 0.06840 -0.0474 1.0014 0.0173 -8.500 -0.6194 0.07063 0.06565 -0.0453 1.0014 0.0172 -8.250 -0.6356 0.06738 0.06234 -0.0434 1.0014 0.0169 -8.000 -0.6484 0.06402 0.05887 -0.0414 1.0014 0.0166 -7.750 -0.6577 0.06047 0.05515 -0.0393 1.0014 0.0162 -7.500 -0.6632 0.05671 0.05117 -0.0372 1.0014 0.0157 -7.250 -0.6649 0.05276 0.04694 -0.0351 1.0014 0.0152 -7.000 -0.6627 0.04854 0.04232 -0.0329 1.0014 0.0145 -6.750 -0.6558 0.04443 0.03769 -0.0307 1.0014 0.0138 -6.500 -0.6440 0.04135 0.03418 -0.0289 1.0014 0.0135 -6.250 -0.6298 0.03859 0.03100 -0.0274 1.0014 0.0134 -6.000 -0.6135 0.03593 0.02793 -0.0260 1.0014 0.0133 -5.750 -0.5954 0.03325 0.02484 -0.0249 1.0014 0.0133 -5.500 -0.5754 0.03066 0.02187 -0.0239 1.0014 0.0134 -5.250 -0.5538 0.02832 0.01922 -0.0230 1.0014 0.0137 -5.000 -0.5314 0.02637 0.01705 -0.0222 1.0014 0.0142 -4.750 -0.5085 0.02484 0.01531 -0.0215 1.0014 0.0151 -4.500 -0.4855 0.02373 0.01406 -0.0208 1.0014 0.0175 -4.250 -0.4620 0.02283 0.01297 -0.0201 1.0014 0.0206 -4.000 -0.4394 0.02149 0.01167 -0.0198 1.0014 0.0273 -3.750 -0.4150 0.02021 0.01024 -0.0194 1.0014 0.0331 -3.500 -0.3900 0.01927 0.00921 -0.0192 1.0014 0.0454 -3.250 -0.3636 0.01822 0.00823 -0.0195 1.0014 0.0793 -3.000 -0.3373 0.01553 0.00805 -0.0209 1.0014 0.5922 -2.750 -0.3202 0.01605 0.00869 -0.0177 1.0014 0.6878 -2.500 -0.3009 0.01668 0.00940 -0.0143 0.9984 0.7465 -2.250 -0.2702 0.01679 0.00928 -0.0149 0.9960 0.7586 -2.000 -0.2397 0.01677 0.00907 -0.0158 0.9930 0.7638 -1.750 -0.2079 0.01679 0.00892 -0.0171 0.9901 0.7693 -1.500 -0.1739 0.01683 0.00879 -0.0190 0.9873 0.7749 -1.250 -0.1419 0.01688 0.00871 -0.0202 0.9843 0.7796 -1.000 -0.1113 0.01689 0.00862 -0.0213 0.9802 0.7850 -0.750 -0.0785 0.01695 0.00860 -0.0229 0.9765 0.7901 -0.500 -0.0446 0.01704 0.00864 -0.0246 0.9735 0.7951 -0.250 -0.0140 0.01709 0.00862 -0.0257 0.9695 0.8009 0.000 0.0156 0.01714 0.00867 -0.0265 0.9652 0.8058 0.250 0.0486 0.01723 0.00876 -0.0280 0.9617 0.8116 0.500 0.0808 0.01733 0.00887 -0.0294 0.9582 0.8174 0.750 0.1083 0.01739 0.00898 -0.0298 0.9529 0.8231 1.000 0.1419 0.01749 0.00912 -0.0314 0.9491 0.8298 1.250 0.1721 0.01757 0.00928 -0.0322 0.9443 0.8358 1.500 0.2021 0.01763 0.00942 -0.0331 0.9381 0.8431 1.750 0.2374 0.01769 0.00961 -0.0348 0.9340 0.8496 2.000 0.2628 0.01774 0.00978 -0.0347 0.9262 0.8583 2.250 0.2968 0.01776 0.00995 -0.0361 0.9212 0.8662 2.500 0.3249 0.01770 0.01006 -0.0362 0.9115 0.8756 2.750 0.3583 0.01754 0.01013 -0.0372 0.9019 0.8858 3.000 0.3970 0.01721 0.01003 -0.0389 0.8926 0.8959 3.250 0.4359 0.01617 0.00922 -0.0394 0.8671 0.9061 3.500 0.4675 0.01508 0.00837 -0.0381 0.8295 0.9196 3.750 0.5010 0.01439 0.00789 -0.0379 0.7856 0.9369 4.000 0.5590 0.01382 0.00653 -0.0407 0.5475 0.9385 4.250 0.5746 0.01582 0.00705 -0.0389 0.2588 0.9650 4.500 0.5957 0.01731 0.00785 -0.0387 0.1266 0.9986 4.750 0.6167 0.01835 0.00868 -0.0379 0.0885 0.9986 5.000 0.6382 0.01936 0.00965 -0.0371 0.0667 0.9986 5.250 0.6597 0.02037 0.01064 -0.0363 0.0458 0.9986 5.500 0.6813 0.02144 0.01170 -0.0355 0.0316 0.9986 5.750 0.7025 0.02276 0.01308 -0.0345 0.0249 0.9986 6.000 0.7251 0.02423 0.01472 -0.0337 0.0218 0.9986 6.250 0.7487 0.02588 0.01647 -0.0331 0.0200 0.9986 6.500 0.7735 0.02844 0.01919 -0.0327 0.0188 0.9986 6.750 0.7993 0.03084 0.02192 -0.0321 0.0182 0.9986 7.000 0.8224 0.03361 0.02513 -0.0311 0.0178 0.9986 7.250 0.8416 0.03670 0.02872 -0.0295 0.0176 0.9986 7.500 0.8566 0.04010 0.03263 -0.0275 0.0174 0.9986 7.750 0.8674 0.04374 0.03677 -0.0250 0.0174 0.9986 8.000 0.8743 0.04754 0.04109 -0.0223 0.0172 0.9986 8.250 0.8777 0.05144 0.04544 -0.0194 0.0168 0.9986 8.500 0.8775 0.05545 0.04983 -0.0166 0.0165 0.9986 8.750 0.8737 0.05953 0.05425 -0.0138 0.0161 0.9986 9.000 0.8663 0.06362 0.05860 -0.0112 0.0159 0.9986 9.250 0.8540 0.06754 0.06273 -0.0085 0.0158 0.9986 9.500 0.8385 0.07156 0.06692 -0.0063 0.0159 0.9986 9.750 0.8215 0.07600 0.07149 -0.0054 0.0160 0.9986 10.000 0.8039 0.08114 0.07675 -0.0062 0.0162 0.9986 10.250 0.7878 0.08702 0.08270 -0.0089 0.0167 0.9986