XFOIL Version 6.96 Calculated polar for: NACA 65(1)-412 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5193 0.05973 0.05809 -0.0709 0.9980 0.0131 -9.500 -0.6236 0.02484 0.02128 -0.0851 0.9601 0.0116 -9.250 -0.6017 0.02320 0.01935 -0.0854 0.9500 0.0119 -9.000 -0.5931 0.01912 0.01474 -0.0841 0.9370 0.0124 -8.750 -0.5710 0.01840 0.01392 -0.0837 0.9274 0.0128 -8.500 -0.5479 0.01805 0.01350 -0.0833 0.9182 0.0132 -8.250 -0.5251 0.01739 0.01271 -0.0828 0.9099 0.0136 -8.000 -0.5019 0.01675 0.01196 -0.0823 0.9013 0.0141 -7.750 -0.4780 0.01617 0.01126 -0.0819 0.8938 0.0147 -7.500 -0.4535 0.01568 0.01064 -0.0816 0.8857 0.0153 -7.250 -0.4286 0.01527 0.01011 -0.0812 0.8785 0.0156 -7.000 -0.4075 0.01354 0.00819 -0.0805 0.8706 0.0162 -6.750 -0.3834 0.01287 0.00747 -0.0801 0.8637 0.0169 -6.500 -0.3580 0.01250 0.00707 -0.0799 0.8565 0.0176 -6.250 -0.3324 0.01214 0.00664 -0.0797 0.8499 0.0183 -6.000 -0.3066 0.01179 0.00624 -0.0796 0.8428 0.0190 -5.750 -0.2806 0.01150 0.00587 -0.0794 0.8362 0.0198 -5.500 -0.2543 0.01116 0.00549 -0.0793 0.8294 0.0203 -5.250 -0.2306 0.01038 0.00461 -0.0788 0.8229 0.0211 -5.000 -0.2051 0.00986 0.00405 -0.0787 0.8167 0.0222 -4.750 -0.1785 0.00960 0.00376 -0.0786 0.8103 0.0233 -4.500 -0.1515 0.00938 0.00350 -0.0787 0.8044 0.0246 -4.250 -0.1243 0.00915 0.00323 -0.0787 0.7980 0.0257 -4.000 -0.0970 0.00899 0.00300 -0.0787 0.7922 0.0265 -3.750 -0.0701 0.00854 0.00251 -0.0788 0.7865 0.0289 -3.500 -0.0426 0.00835 0.00229 -0.0789 0.7807 0.0314 -3.250 -0.0148 0.00822 0.00211 -0.0790 0.7754 0.0339 -3.000 0.0131 0.00800 0.00188 -0.0791 0.7695 0.0396 -2.750 0.0408 0.00781 0.00171 -0.0793 0.7640 0.0528 -2.500 0.0671 0.00701 0.00145 -0.0797 0.7589 0.2131 -2.250 0.0928 0.00579 0.00117 -0.0805 0.7534 0.4951 -2.000 0.1206 0.00558 0.00115 -0.0807 0.7482 0.5755 -1.750 0.1492 0.00552 0.00113 -0.0810 0.7432 0.6039 -1.500 0.1777 0.00547 0.00114 -0.0812 0.7380 0.6315 -1.250 0.2059 0.00548 0.00116 -0.0813 0.7331 0.6550 -1.000 0.2345 0.00548 0.00120 -0.0815 0.7283 0.6774 -0.750 0.2630 0.00550 0.00123 -0.0816 0.7233 0.6919 -0.500 0.2913 0.00553 0.00124 -0.0818 0.7186 0.7003 -0.250 0.3201 0.00554 0.00125 -0.0820 0.7141 0.7057 0.000 0.3490 0.00556 0.00126 -0.0823 0.7093 0.7105 0.250 0.3773 0.00558 0.00127 -0.0825 0.7048 0.7154 0.500 0.4060 0.00561 0.00130 -0.0828 0.7004 0.7205 0.750 0.4349 0.00563 0.00133 -0.0831 0.6959 0.7256 1.000 0.4632 0.00565 0.00136 -0.0832 0.6914 0.7306 1.250 0.4917 0.00570 0.00140 -0.0835 0.6866 0.7361 1.500 0.5202 0.00571 0.00144 -0.0837 0.6802 0.7414 1.750 0.5481 0.00576 0.00148 -0.0837 0.6731 0.7467 2.000 0.5762 0.00577 0.00152 -0.0839 0.6634 0.7524 2.250 0.6040 0.00581 0.00156 -0.0839 0.6523 0.7579 2.500 0.6314 0.00586 0.00161 -0.0839 0.6394 0.7638 2.750 0.6586 0.00594 0.00165 -0.0838 0.6209 0.7698 3.000 0.6853 0.00603 0.00172 -0.0837 0.6029 0.7755 3.250 0.7120 0.00615 0.00182 -0.0835 0.5812 0.7820 3.500 0.7376 0.00634 0.00192 -0.0832 0.5487 0.7882 3.750 0.7602 0.00676 0.00211 -0.0823 0.4850 0.7949 4.000 0.7755 0.00784 0.00259 -0.0804 0.3526 0.8019 4.250 0.7902 0.00897 0.00317 -0.0785 0.2251 0.8091 4.500 0.8055 0.01006 0.00374 -0.0767 0.1117 0.8168 4.750 0.8234 0.01088 0.00424 -0.0752 0.0457 0.8246 5.000 0.8467 0.01126 0.00458 -0.0745 0.0333 0.8324 5.250 0.8703 0.01157 0.00492 -0.0739 0.0289 0.8403 5.500 0.8934 0.01194 0.00533 -0.0731 0.0253 0.8483 5.750 0.9170 0.01222 0.00566 -0.0725 0.0232 0.8569 6.000 0.9387 0.01262 0.00609 -0.0715 0.0210 0.8659 6.250 0.9590 0.01314 0.00669 -0.0703 0.0195 0.8759 6.500 0.9813 0.01341 0.00702 -0.0694 0.0186 0.8861 6.750 1.0022 0.01375 0.00741 -0.0683 0.0176 0.8967 7.000 1.0222 0.01411 0.00782 -0.0670 0.0168 0.9084 7.250 1.0398 0.01457 0.00834 -0.0653 0.0161 0.9220 7.500 1.0508 0.01525 0.00912 -0.0623 0.0153 0.9405 7.750 1.0623 0.01592 0.00992 -0.0595 0.0149 1.0000 8.000 1.0809 0.01645 0.01050 -0.0582 0.0146 1.0000 8.250 1.0987 0.01701 0.01109 -0.0568 0.0143 1.0000 8.500 1.1147 0.01767 0.01181 -0.0551 0.0140 1.0000 8.750 1.1301 0.01839 0.01257 -0.0534 0.0137 1.0000 9.000 1.1465 0.01905 0.01327 -0.0519 0.0133 1.0000 9.250 1.1629 0.01970 0.01396 -0.0505 0.0129 1.0000 9.500 1.1792 0.02035 0.01465 -0.0492 0.0126 1.0000 9.750 1.1941 0.02114 0.01548 -0.0477 0.0122 1.0000 10.000 1.2080 0.02207 0.01644 -0.0461 0.0119 1.0000 10.250 1.2201 0.02334 0.01778 -0.0444 0.0117 1.0000 10.500 1.2330 0.02604 0.02064 -0.0429 0.0112 1.0000 10.750 1.2478 0.02691 0.02160 -0.0415 0.0111 1.0000 11.000 1.2618 0.02784 0.02261 -0.0402 0.0110 1.0000 11.250 1.2756 0.02911 0.02400 -0.0389 0.0109 1.0000 11.500 1.2882 0.03047 0.02549 -0.0375 0.0107 1.0000 11.750 1.2995 0.03183 0.02697 -0.0361 0.0105 1.0000 12.000 1.3094 0.03324 0.02850 -0.0346 0.0103 1.0000 12.250 1.3183 0.03463 0.03000 -0.0332 0.0101 1.0000 12.500 1.3253 0.03632 0.03181 -0.0317 0.0099 1.0000 12.750 1.3307 0.03821 0.03385 -0.0302 0.0097 1.0000 13.000 1.3355 0.03999 0.03574 -0.0289 0.0095 1.0000 13.250 1.3387 0.04195 0.03781 -0.0276 0.0094 1.0000 13.500 1.3409 0.04401 0.04000 -0.0265 0.0092 1.0000 13.750 1.3409 0.04640 0.04252 -0.0255 0.0091 1.0000 14.000 1.3408 0.04882 0.04505 -0.0247 0.0090 1.0000 14.250 1.3387 0.05156 0.04792 -0.0241 0.0089 1.0000 14.500 1.3363 0.05440 0.05086 -0.0238 0.0088 1.0000 14.750 1.3283 0.05820 0.05482 -0.0236 0.0088 1.0000 15.000 1.3209 0.06199 0.05873 -0.0239 0.0086 1.0000 15.250 1.3072 0.06697 0.06389 -0.0246 0.0086 1.0000 15.500 1.2904 0.07271 0.06982 -0.0260 0.0085 1.0000 15.750 1.2677 0.07977 0.07708 -0.0283 0.0085 1.0000 16.000 1.2496 0.08662 0.08411 -0.0312 0.0085 1.0000 16.250 1.2279 0.09469 0.09237 -0.0352 0.0085 1.0000 16.500 1.2049 0.10367 0.10153 -0.0403 0.0085 1.0000 16.750 1.1801 0.11402 0.11208 -0.0466 0.0086 1.0000