XFOIL Version 6.96 Calculated polar for: NACA 0010-66 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.500 -0.8461 0.13558 0.13359 -0.0264 0.9986 0.0063 -17.250 -1.2316 0.05315 0.05024 -0.0731 0.9983 0.0047 -17.000 -1.2536 0.04725 0.04414 -0.0751 0.9975 0.0047 -16.750 -1.2668 0.04330 0.04002 -0.0749 0.9968 0.0047 -16.500 -1.2755 0.04024 0.03680 -0.0737 0.9962 0.0048 -16.250 -1.2797 0.03775 0.03416 -0.0722 0.9956 0.0049 -16.000 -1.2806 0.03564 0.03191 -0.0704 0.9951 0.0050 -15.750 -1.2786 0.03380 0.02993 -0.0686 0.9947 0.0050 -15.500 -1.2765 0.03220 0.02820 -0.0662 0.9939 0.0051 -15.250 -1.2732 0.03080 0.02666 -0.0636 0.9927 0.0052 -15.000 -1.2671 0.02950 0.02522 -0.0613 0.9915 0.0053 -14.750 -1.2590 0.02831 0.02391 -0.0592 0.9904 0.0055 -14.500 -1.2490 0.02722 0.02269 -0.0572 0.9895 0.0056 -14.250 -1.2369 0.02622 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0.8941 0.8942 0.250 0.0420 0.00494 0.00176 -0.0031 0.8661 0.9050 0.500 0.0296 0.00587 0.00182 0.0066 0.6379 0.9132 0.750 0.0126 0.00643 0.00195 0.0171 0.5157 0.9235 1.000 0.0466 0.00733 0.00243 0.0155 0.3944 0.9296 1.250 0.0624 0.00765 0.00256 0.0182 0.3393 0.9346 1.500 0.0763 0.00784 0.00262 0.0214 0.2990 0.9388 1.750 0.1101 0.00836 0.00287 0.0197 0.2298 0.9401 2.000 0.1408 0.00875 0.00306 0.0188 0.1768 0.9412 2.250 0.1671 0.00899 0.00317 0.0190 0.1434 0.9420 2.500 0.1922 0.00917 0.00324 0.0194 0.1197 0.9428 2.750 0.2167 0.00934 0.00332 0.0200 0.0999 0.9438 3.000 0.2403 0.00948 0.00340 0.0208 0.0845 0.9450 3.250 0.2608 0.00961 0.00346 0.0223 0.0687 0.9468 3.500 0.2634 0.00959 0.00339 0.0281 0.0568 0.9517 3.750 0.2912 0.00979 0.00353 0.0279 0.0446 0.9521 4.000 0.3189 0.00996 0.00366 0.0277 0.0403 0.9525 4.250 0.3466 0.01015 0.00382 0.0276 0.0364 0.9530 4.500 0.3741 0.01031 0.00399 0.0275 0.0351 0.9535 4.750 0.4013 0.01048 0.00417 0.0274 0.0344 0.9540 5.000 0.4283 0.01065 0.00435 0.0274 0.0337 0.9546 5.250 0.4550 0.01083 0.00454 0.0275 0.0329 0.9552 5.500 0.4813 0.01102 0.00474 0.0276 0.0319 0.9559 5.750 0.5072 0.01122 0.00495 0.0278 0.0309 0.9567 6.000 0.5325 0.01145 0.00518 0.0282 0.0300 0.9577 6.250 0.5564 0.01168 0.00544 0.0289 0.0290 0.9590 6.500 0.5744 0.01192 0.00571 0.0309 0.0278 0.9612 6.750 0.5850 0.01210 0.00592 0.0347 0.0269 0.9643 7.000 0.6126 0.01229 0.00612 0.0344 0.0266 0.9647 7.250 0.6400 0.01250 0.00637 0.0342 0.0261 0.9651 7.500 0.6671 0.01272 0.00661 0.0341 0.0254 0.9656 7.750 0.6939 0.01296 0.00688 0.0340 0.0246 0.9660 8.000 0.7206 0.01319 0.00714 0.0339 0.0236 0.9665 8.250 0.7474 0.01343 0.00738 0.0338 0.0225 0.9671 8.500 0.7738 0.01372 0.00768 0.0338 0.0215 0.9677 8.750 0.7995 0.01411 0.00810 0.0338 0.0202 0.9683 9.000 0.8251 0.01433 0.00835 0.0340 0.0196 0.9691 9.250 0.8493 0.01455 0.00861 0.0344 0.0186 0.9700 9.500 0.8712 0.01478 0.00886 0.0354 0.0174 0.9714 9.750 0.8765 0.01487 0.00896 0.0402 0.0164 0.9755 10.000 0.9027 0.01522 0.00932 0.0401 0.0149 0.9758 10.250 0.9286 0.01560 0.00974 0.0400 0.0139 0.9762 10.500 0.9546 0.01600 0.01017 0.0399 0.0126 0.9765 10.750 0.9802 0.01648 0.01066 0.0398 0.0112 0.9769 11.000 1.0052 0.01696 0.01120 0.0398 0.0105 0.9773 11.250 1.0293 0.01746 0.01176 0.0400 0.0098 0.9778 11.500 1.0523 0.01800 0.01237 0.0404 0.0092 0.9784 11.750 1.0740 0.01860 0.01302 0.0411 0.0086 0.9791 12.000 1.0942 0.01926 0.01375 0.0420 0.0080 0.9799 12.250 1.1137 0.01981 0.01439 0.0431 0.0078 0.9809 12.500 1.1311 0.02039 0.01506 0.0446 0.0075 0.9823 12.750 1.1377 0.02088 0.01563 0.0486 0.0073 0.9855 13.000 1.1584 0.02161 0.01645 0.0491 0.0070 0.9858 13.250 1.1779 0.02238 0.01733 0.0498 0.0067 0.9863 13.500 1.1957 0.02323 0.01826 0.0508 0.0064 0.9867 13.750 1.2114 0.02418 0.01931 0.0521 0.0061 0.9873 14.000 1.2242 0.02530 0.02055 0.0537 0.0058 0.9880 14.250 1.2381 0.02623 0.02159 0.0553 0.0057 0.9887 14.500 1.2502 0.02722 0.02270 0.0570 0.0056 0.9896 14.750 1.2603 0.02831 0.02391 0.0589 0.0055 0.9905 15.000 1.2682 0.02950 0.02522 0.0611 0.0053 0.9916 15.250 1.2745 0.03079 0.02665 0.0634 0.0052 0.9928 15.500 1.2776 0.03220 0.02819 0.0660 0.0051 0.9941 15.750 1.2804 0.03380 0.02993 0.0682 0.0050 0.9947 16.000 1.2824 0.03564 0.03191 0.0701 0.0049 0.9952 16.250 1.2815 0.03776 0.03417 0.0718 0.0049 0.9957 16.500 1.2772 0.04026 0.03682 0.0734 0.0048 0.9963 16.750 1.2688 0.04330 0.04002 0.0745 0.0047 0.9969 17.000 1.2556 0.04725 0.04415 0.0747 0.0047 0.9976 17.250 1.2337 0.05315 0.05025 0.0727 0.0047 0.9984 17.500 0.8466 0.13616 0.13417 0.0256 0.0063 0.9987