XFOIL Version 6.96 Calculated polar for: FX 63-143 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.2678 0.08649 0.08427 -0.0757 0.8337 0.0125 -10.500 -0.2703 0.08231 0.07971 -0.0777 0.7493 0.0127 -10.250 -0.2753 0.07703 0.07437 -0.0806 0.7291 0.0130 -10.000 -0.2823 0.07107 0.06841 -0.0845 0.7242 0.0129 -9.250 -0.3572 0.03584 0.03270 -0.0894 0.6779 0.0135 -9.000 -0.3777 0.03351 0.03023 -0.0854 0.6701 0.0135 -8.750 -0.4011 0.03059 0.02705 -0.0807 0.6650 0.0136 -8.500 -0.4138 0.02761 0.02377 -0.0768 0.6575 0.0136 -8.250 -0.4247 0.02467 0.02045 -0.0726 0.6503 0.0136 -7.500 -0.3978 0.02897 0.02429 -0.0721 0.6272 0.0139 -7.250 -0.3812 0.02768 0.02292 -0.0711 0.6196 0.0141 -7.000 -0.3652 0.02627 0.02136 -0.0697 0.6121 0.0145 -6.750 -0.3490 0.02451 0.01937 -0.0680 0.6056 0.0148 -6.500 -0.3348 0.02299 0.01724 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3.250 0.6569 0.01215 0.00326 -0.0509 0.0861 0.0432 3.500 0.6838 0.01222 0.00337 -0.0510 0.0859 0.0604 3.750 0.7106 0.01231 0.00348 -0.0510 0.0858 0.0670 4.000 0.7375 0.01237 0.00361 -0.0510 0.0856 0.0971 4.250 0.7642 0.01246 0.00374 -0.0510 0.0856 0.1098 4.500 0.7918 0.01236 0.00389 -0.0514 0.0855 0.2376 4.750 0.8232 0.01183 0.00406 -0.0531 0.0854 0.5138 5.000 0.8590 0.01129 0.00432 -0.0557 0.0835 0.7762 5.250 0.8818 0.01141 0.00468 -0.0548 0.0803 0.8505 5.500 0.9047 0.01166 0.00498 -0.0539 0.0782 0.8725 5.750 0.9288 0.01186 0.00522 -0.0533 0.0773 0.8835 6.000 0.9546 0.01207 0.00544 -0.0531 0.0760 0.8918 6.250 0.9770 0.01230 0.00569 -0.0522 0.0671 0.8975 6.500 0.9953 0.01271 0.00606 -0.0504 0.0611 0.9058 6.750 1.0173 0.01307 0.00641 -0.0496 0.0592 0.9110 7.000 1.0358 0.01334 0.00671 -0.0479 0.0582 0.9148 7.250 1.0544 0.01362 0.00703 -0.0462 0.0572 0.9193 7.500 1.0748 0.01394 0.00736 -0.0450 0.0561 0.9239 7.750 1.0957 0.01425 0.00770 -0.0440 0.0550 0.9275 8.000 1.1116 0.01449 0.00800 -0.0419 0.0543 0.9308 8.250 1.1261 0.01476 0.00833 -0.0395 0.0537 0.9356 8.500 1.1424 0.01509 0.00871 -0.0376 0.0527 0.9407 8.750 1.1493 0.01530 0.00899 -0.0337 0.0515 0.9463 9.000 1.1583 0.01564 0.00940 -0.0305 0.0500 0.9509 9.250 1.1699 0.01615 0.00996 -0.0280 0.0480 0.9545 9.500 1.1913 0.01636 0.01020 -0.0274 0.0452 0.9565 9.750 1.2010 0.01660 0.01035 -0.0245 0.0287 0.9609 10.000 1.2060 0.01725 0.01099 -0.0212 0.0222 0.9650 10.250 1.2112 0.01791 0.01169 -0.0181 0.0195 0.9704 10.500 1.2152 0.01859 0.01242 -0.0150 0.0177 0.9758 10.750 1.2203 0.01939 0.01327 -0.0124 0.0164 0.9821 11.000 1.2333 0.02026 0.01421 -0.0116 0.0160 0.9908 11.250 1.2473 0.02133 0.01535 -0.0114 0.0156 1.0000 11.500 1.2605 0.02253 0.01662 -0.0112 0.0152 1.0000 11.750 1.2725 0.02388 0.01804 -0.0111 0.0149 1.0000 12.000 1.2836 0.02536 0.01959 -0.0110 0.0145 1.0000 12.250 1.2933 0.02700 0.02129 -0.0110 0.0141 1.0000 12.500 1.3017 0.02881 0.02317 -0.0110 0.0138 1.0000 12.750 1.3089 0.03076 0.02519 -0.0111 0.0134 1.0000 13.000 1.3147 0.03288 0.02738 -0.0112 0.0129 1.0000 13.250 1.3201 0.03505 0.02962 -0.0113 0.0127 1.0000 13.500 1.3226 0.03756 0.03221 -0.0114 0.0122 1.0000 13.750 1.3237 0.04024 0.03498 -0.0116 0.0118 1.0000 14.000 1.3229 0.04313 0.03798 -0.0118 0.0115 1.0000 14.500 1.3262 0.04863 0.04366 -0.0127 0.0111 1.0000 14.750 1.3355 0.05062 0.04569 -0.0132 0.0109 1.0000 15.000 1.3431 0.05283 0.04796 -0.0138 0.0106 1.0000 15.250 1.3492 0.05526 0.05046 -0.0145 0.0101 1.0000 15.500 1.3526 0.05803 0.05330 -0.0152 0.0098 1.0000 15.750 1.3577 0.06064 0.05596 -0.0159 0.0092 1.0000 16.000 1.3612 0.06350 0.05888 -0.0168 0.0086 1.0000 16.250 1.3609 0.06688 0.06230 -0.0178 0.0077 1.0000 16.500 1.3633 0.06997 0.06545 -0.0188 0.0071 1.0000 16.750 1.3733 0.07210 0.06764 -0.0197 0.0064 1.0000 17.000 1.3761 0.07524 0.07084 -0.0208 0.0059 1.0000 17.250 1.3815 0.07802 0.07363 -0.0219 0.0049 1.0000 17.500 1.3807 0.08172 0.07737 -0.0232 0.0044 1.0000 17.750 1.3795 0.08553 0.08123 -0.0247 0.0038 1.0000 18.000 1.3788 0.08931 0.08505 -0.0262 0.0034 1.0000 18.250 1.3756 0.09357 0.08938 -0.0279 0.0031 1.0000 18.500 1.3719 0.09795 0.09385 -0.0297 0.0031 1.0000