XFOIL Version 6.96 Calculated polar for: NACA 65(4)-221 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0734 0.08090 0.07659 -0.0584 1.0000 0.0166 -19.500 -1.0720 0.07801 0.07363 -0.0593 1.0000 0.0167 -19.250 -1.0700 0.07520 0.07075 -0.0601 1.0000 0.0168 -19.000 -1.0694 0.07233 0.06782 -0.0608 1.0000 0.0168 -18.750 -1.0666 0.06969 0.06511 -0.0615 1.0000 0.0169 -18.500 -1.0621 0.06731 0.06268 -0.0621 1.0000 0.0169 -18.250 -1.0594 0.06478 0.06008 -0.0626 1.0000 0.0170 -17.750 -1.0461 0.06015 0.05533 -0.0640 0.9698 0.0171 -17.500 -1.0177 0.05694 0.05202 -0.0703 0.9557 0.0172 -17.250 -0.9915 0.05352 0.04850 -0.0768 0.9407 0.0175 -17.000 -0.9706 0.05113 0.04596 -0.0805 0.9124 0.0178 -16.750 -0.9635 0.04928 0.04395 -0.0807 0.8884 0.0177 -16.500 -0.9557 0.04771 0.04229 -0.0805 0.8716 0.0179 -16.250 -0.9490 0.04608 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0.00194 -0.0343 0.5975 0.5725 -1.250 0.0200 0.00722 0.00192 -0.0348 0.5954 0.5748 -1.000 0.0495 0.00721 0.00192 -0.0354 0.5934 0.5768 -0.750 0.0789 0.00721 0.00191 -0.0359 0.5915 0.5786 -0.500 0.1084 0.00722 0.00191 -0.0364 0.5895 0.5805 -0.250 0.1378 0.00723 0.00191 -0.0369 0.5876 0.5825 0.000 0.1671 0.00725 0.00192 -0.0374 0.5857 0.5845 0.250 0.1963 0.00729 0.00193 -0.0379 0.5834 0.5864 0.500 0.2261 0.00730 0.00194 -0.0384 0.5819 0.5880 0.750 0.2557 0.00730 0.00196 -0.0390 0.5801 0.5896 1.000 0.2851 0.00730 0.00198 -0.0395 0.5784 0.5916 1.250 0.3145 0.00731 0.00201 -0.0400 0.5766 0.5936 1.500 0.3439 0.00732 0.00204 -0.0405 0.5747 0.5956 1.750 0.3731 0.00734 0.00207 -0.0410 0.5727 0.5977 2.000 0.4022 0.00737 0.00211 -0.0415 0.5706 0.6000 2.250 0.4312 0.00741 0.00215 -0.0419 0.5684 0.6022 2.500 0.4601 0.00747 0.00220 -0.0423 0.5664 0.6041 2.750 0.4895 0.00750 0.00225 -0.0429 0.5649 0.6058 3.000 0.5188 0.00752 0.00230 -0.0434 0.5629 0.6075 3.250 0.5479 0.00753 0.00236 -0.0438 0.5599 0.6097 3.500 0.5765 0.00755 0.00241 -0.0442 0.5560 0.6119 3.750 0.6044 0.00760 0.00246 -0.0444 0.5513 0.6142 4.000 0.6326 0.00764 0.00252 -0.0447 0.5449 0.6165 4.250 0.6593 0.00772 0.00257 -0.0447 0.5335 0.6190 4.500 0.6868 0.00778 0.00264 -0.0449 0.5234 0.6214 4.750 0.7132 0.00789 0.00273 -0.0449 0.5134 0.6236 5.000 0.7381 0.00803 0.00283 -0.0446 0.4962 0.6257 5.250 0.7584 0.00832 0.00301 -0.0435 0.4641 0.6283 5.500 0.7708 0.00888 0.00335 -0.0410 0.4120 0.6309 5.750 0.7745 0.00969 0.00387 -0.0371 0.3527 0.6336 6.000 0.7756 0.01034 0.00433 -0.0326 0.3085 0.6363 6.250 0.7691 0.01113 0.00492 -0.0269 0.2659 0.6390 6.500 0.7688 0.01195 0.00558 -0.0227 0.2316 0.6416 6.750 0.7686 0.01285 0.00634 -0.0187 0.1983 0.6442 7.000 0.7714 0.01372 0.00711 -0.0155 0.1708 0.6477 7.250 0.7773 0.01456 0.00786 -0.0128 0.1488 0.6512 7.500 0.7835 0.01544 0.00868 -0.0103 0.1284 0.6547 7.750 0.7890 0.01642 0.00957 -0.0079 0.1080 0.6579 8.250 0.8014 0.01847 0.01146 -0.0036 0.0723 0.6640 8.500 0.8074 0.01956 0.01250 -0.0016 0.0559 0.6676 8.750 0.8158 0.02057 0.01347 0.0001 0.0445 0.6714 9.000 0.8255 0.02155 0.01442 0.0016 0.0360 0.6751 9.250 0.8374 0.02244 0.01531 0.0028 0.0320 0.6787 9.500 0.8503 0.02328 0.01616 0.0038 0.0293 0.6826 9.750 0.8634 0.02413 0.01704 0.0048 0.0274 0.6872 10.000 0.8761 0.02502 0.01795 0.0058 0.0259 0.6916 10.250 0.8899 0.02588 0.01883 0.0067 0.0246 0.6959 10.750 0.9162 0.02771 0.02072 0.0083 0.0227 0.7039 11.000 0.9287 0.02871 0.02175 0.0091 0.0217 0.7086 11.250 0.9427 0.02963 0.02271 0.0098 0.0212 0.7133 11.500 0.9561 0.03061 0.02372 0.0104 0.0206 0.7176 11.750 0.9687 0.03164 0.02480 0.0111 0.0199 0.7229 12.000 0.9816 0.03267 0.02587 0.0118 0.0194 0.7288 12.250 0.9926 0.03388 0.02710 0.0125 0.0185 0.7339 12.500 1.0054 0.03498 0.02824 0.0130 0.0183 0.7390 12.750 1.0187 0.03602 0.02934 0.0135 0.0179 0.7449 13.000 1.0307 0.03722 0.03059 0.0140 0.0176 0.7508 13.250 1.0429 0.03841 0.03183 0.0144 0.0173 0.7561 13.500 1.0552 0.03959 0.03306 0.0149 0.0170 0.7621 13.750 1.0663 0.04091 0.03444 0.0153 0.0167 0.7690 14.000 1.0775 0.04225 0.03582 0.0157 0.0163 0.7754 14.250 1.0885 0.04357 0.03720 0.0160 0.0161 0.7828 14.500 1.0985 0.04505 0.03873 0.0164 0.0159 0.7908 14.750 1.1072 0.04664 0.04038 0.0168 0.0156 0.7982 15.000 1.1164 0.04821 0.04202 0.0171 0.0154 0.8065 15.500 1.1363 0.05131 0.04526 0.0175 0.0151 0.8228 15.750 1.1454 0.05296 0.04699 0.0176 0.0150 0.8316 16.000 1.1544 0.05462 0.04873 0.0178 0.0147 0.8419 16.250 1.1626 0.05637 0.05057 0.0179 0.0147 0.8524 16.500 1.1702 0.05818 0.05248 0.0181 0.0145 0.8667 16.750 1.1769 0.06003 0.05444 0.0183 0.0144 0.8828 17.000 1.1825 0.06187 0.05641 0.0187 0.0143 0.9096 17.250 1.1960 0.06398 0.05869 0.0171 0.0140 0.9507 17.500 1.2091 0.06640 0.06117 0.0151 0.0138 1.0000 17.750 1.2157 0.06862 0.06344 0.0147 0.0137 1.0000 18.000 1.2210 0.07102 0.06589 0.0143 0.0136 1.0000 18.250 1.2265 0.07342 0.06834 0.0139 0.0135 1.0000 18.500 1.2294 0.07616 0.07113 0.0133 0.0133 1.0000 18.750 1.2343 0.07870 0.07372 0.0126 0.0131 1.0000 19.000 1.2363 0.08166 0.07673 0.0119 0.0130 1.0000 19.250 1.2381 0.08468 0.07982 0.0110 0.0129 1.0000