XFOIL Version 6.96 Calculated polar for: RONCZ 1082 VOYAGER ROOT OUTER AFT WING 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.3529 0.09433 0.08951 -0.0757 0.9531 0.0280 -12.000 -0.4055 0.07443 0.06943 -0.0909 0.9385 0.0268 -11.750 -0.4473 0.06203 0.05657 -0.1025 0.9170 0.0261 -11.500 -0.4657 0.05495 0.04900 -0.1085 0.8952 0.0260 -11.250 -0.4731 0.05042 0.04402 -0.1110 0.8727 0.0260 -11.000 -0.4795 0.04698 0.04016 -0.1111 0.8526 0.0262 -10.750 -0.4831 0.04433 0.03715 -0.1098 0.8358 0.0264 -10.500 -0.4844 0.04204 0.03450 -0.1079 0.8221 0.0266 -10.000 -0.4802 0.03843 0.03026 -0.1032 0.8001 0.0277 -9.750 -0.4743 0.03669 0.02812 -0.1009 0.7917 0.0286 -9.500 -0.4637 0.03501 0.02611 -0.0992 0.7833 0.0295 -9.250 -0.4455 0.03374 0.02469 -0.0985 0.7768 0.0302 -9.000 -0.4277 0.03248 0.02328 -0.0976 0.7693 0.0310 -8.750 -0.4069 0.03117 0.02177 -0.0970 0.7630 0.0319 -8.500 -0.3839 0.02988 0.02026 -0.0967 0.7575 0.0330 -8.250 -0.3617 0.02874 0.01892 -0.0961 0.7512 0.0342 -8.000 -0.3418 0.02777 0.01791 -0.0953 0.7458 0.0354 -7.750 -0.3221 0.02698 0.01703 -0.0944 0.7415 0.0374 -7.500 -0.3032 0.02626 0.01618 -0.0933 0.7362 0.0405 -7.250 -0.2866 0.02556 0.01549 -0.0920 0.7315 0.0433 -7.000 -0.2681 0.02487 0.01467 -0.0907 0.7276 0.0470 -6.750 -0.2510 0.02417 0.01394 -0.0893 0.7242 0.0517 -6.500 -0.2355 0.02357 0.01337 -0.0876 0.7197 0.0591 -6.250 -0.2190 0.02300 0.01282 -0.0860 0.7156 0.0706 -6.000 -0.2010 0.02247 0.01230 -0.0846 0.7119 0.0877 -5.750 -0.1827 0.02193 0.01184 -0.0833 0.7088 0.1102 -5.500 -0.1656 0.02145 0.01151 -0.0819 0.7053 0.1412 -5.250 -0.1499 0.02099 0.01125 -0.0802 0.7015 0.1788 -5.000 -0.1344 0.02048 0.01096 -0.0785 0.6983 0.2259 -4.750 -0.1203 0.01991 0.01069 -0.0765 0.6954 0.2897 -4.500 -0.1088 0.01927 0.01044 -0.0740 0.6929 0.3772 -4.250 -0.0964 0.01870 0.01041 -0.0711 0.6907 0.4935 -4.000 -0.0608 0.01931 0.01161 -0.0704 0.6881 0.6184 -3.750 -0.0343 0.02002 0.01233 -0.0690 0.6850 0.6710 -3.500 -0.0207 0.02032 0.01252 -0.0662 0.6818 0.7032 -3.250 -0.0047 0.02063 0.01270 -0.0637 0.6790 0.7278 -3.000 0.0124 0.02092 0.01284 -0.0615 0.6767 0.7482 -2.750 0.0392 0.02140 0.01316 -0.0606 0.6748 0.7634 -2.500 0.0684 0.02195 0.01359 -0.0600 0.6729 0.7765 -2.250 0.0908 0.02251 0.01411 -0.0584 0.6701 0.7900 -2.000 0.1128 0.02300 0.01454 -0.0568 0.6676 0.8040 -1.750 0.1311 0.02334 0.01481 -0.0548 0.6651 0.8176 -1.500 0.1684 0.02372 0.01509 -0.0560 0.6628 0.8241 -1.250 0.1836 0.02378 0.01506 -0.0538 0.6606 0.8345 -1.000 0.2190 0.02393 0.01509 -0.0551 0.6587 0.8386 -0.750 0.2476 0.02400 0.01506 -0.0554 0.6572 0.8441 -0.500 0.2575 0.02415 0.01518 -0.0525 0.6548 0.8521 -0.250 0.2803 0.02443 0.01547 -0.0520 0.6522 0.8563 0.000 0.2953 0.02464 0.01566 -0.0500 0.6494 0.8624 0.250 0.3076 0.02473 0.01573 -0.0476 0.6467 0.8686 0.500 0.3356 0.02485 0.01579 -0.0480 0.6446 0.8718 0.750 0.3607 0.02494 0.01582 -0.0479 0.6428 0.8757 1.000 0.3774 0.02498 0.01582 -0.0462 0.6412 0.8812 1.250 0.4020 0.02502 0.01579 -0.0460 0.6398 0.8848 1.500 0.4056 0.02565 0.01654 -0.0425 0.6353 0.8895 1.750 0.4109 0.02605 0.01697 -0.0391 0.6318 0.8951 2.000 0.4194 0.02627 0.01720 -0.0363 0.6290 0.9002 2.250 0.4466 0.02640 0.01731 -0.0366 0.6269 0.9026 2.500 0.4743 0.02648 0.01736 -0.0370 0.6251 0.9051 2.750 0.5023 0.02653 0.01738 -0.0374 0.6236 0.9079 3.000 0.4664 0.02782 0.01883 -0.0279 0.6163 0.9166 3.250 0.4821 0.02829 0.01932 -0.0266 0.6127 0.9201 3.500 0.5052 0.02848 0.01951 -0.0263 0.6103 0.9233 3.750 0.5327 0.02847 0.01950 -0.0266 0.6085 0.9259 4.000 0.5626 0.02840 0.01941 -0.0272 0.6070 0.9283 4.500 0.5361 0.03088 0.02207 -0.0168 0.5933 0.9428 4.750 0.5678 0.03077 0.02197 -0.0177 0.5917 0.9451 5.000 0.6075 0.03058 0.02180 -0.0198 0.5905 0.9463 5.500 0.6055 0.03350 0.02489 -0.0151 0.5757 0.9602 5.750 0.6456 0.03313 0.02455 -0.0170 0.5745 0.9619 6.000 0.6872 0.03268 0.02415 -0.0190 0.5735 0.9634 6.500 0.7046 0.03551 0.02717 -0.0181 0.5581 0.9762 6.750 0.7467 0.03483 0.02655 -0.0199 0.5572 0.9785 7.000 0.7345 0.03813 0.02998 -0.0193 0.5427 0.9916 7.250 0.7744 0.03737 0.02928 -0.0207 0.5417 0.9987 7.750 0.7656 0.03938 0.03134 -0.0143 0.5257 1.0000 8.250 0.7822 0.04116 0.03321 -0.0117 0.5103 1.0000 8.750 0.7994 0.04322 0.03537 -0.0096 0.4931 1.0000 9.250 0.8320 0.04406 0.03635 -0.0083 0.4785 1.0000 9.500 0.8340 0.04569 0.03804 -0.0072 0.4664 1.0000 10.250 0.8733 0.04782 0.04039 -0.0051 0.4384 1.0000 10.500 0.9064 0.04663 0.03928 -0.0050 0.4342 1.0000 10.750 0.9136 0.04793 0.04067 -0.0041 0.4214 1.0000 11.000 0.9256 0.04881 0.04161 -0.0034 0.4094 1.0000 11.250 0.9476 0.04868 0.04154 -0.0030 0.3991 1.0000 11.500 0.9779 0.04770 0.04061 -0.0026 0.3892 1.0000 11.750 0.9962 0.04794 0.04088 -0.0020 0.3747 1.0000 12.000 1.0157 0.04806 0.04100 -0.0014 0.3592 1.0000 12.250 1.0355 0.04813 0.04103 -0.0007 0.3423 1.0000 12.500 1.0471 0.04910 0.04198 0.0000 0.3235 1.0000 12.750 1.0574 0.05022 0.04305 0.0008 0.3044 1.0000 13.000 1.0659 0.05154 0.04430 0.0015 0.2850 1.0000 13.250 1.0728 0.05305 0.04573 0.0023 0.2662 1.0000 13.500 1.0775 0.05487 0.04747 0.0029 0.2479 1.0000 13.750 1.0809 0.05694 0.04950 0.0034 0.2305 1.0000 14.000 1.0840 0.05908 0.05160 0.0039 0.2143 1.0000 14.250 1.0867 0.06131 0.05379 0.0043 0.1991 1.0000 14.500 1.0891 0.06365 0.05610 0.0045 0.1850 1.0000 14.750 1.0915 0.06604 0.05845 0.0047 0.1722 1.0000 15.000 1.0936 0.06853 0.06093 0.0048 0.1603 1.0000 15.250 1.0962 0.07105 0.06348 0.0048 0.1490 1.0000 15.500 1.0988 0.07358 0.06603 0.0048 0.1392 1.0000 15.750 1.1002 0.07628 0.06869 0.0046 0.1304 1.0000 16.000 1.1031 0.07892 0.07141 0.0044 0.1216 1.0000 16.250 1.1052 0.08165 0.07416 0.0041 0.1140 1.0000 16.500 1.1065 0.08452 0.07707 0.0037 0.1070 1.0000 16.750 1.1090 0.08730 0.07990 0.0033 0.1004 1.0000 17.000 1.1099 0.09034 0.08298 0.0027 0.0944 1.0000 17.250 1.1120 0.09325 0.08596 0.0021 0.0888 1.0000 17.500 1.1126 0.09643 0.08920 0.0013 0.0835 1.0000 17.750 1.1130 0.09961 0.09242 0.0005 0.0787 1.0000 18.000 1.1129 0.10301 0.09594 -0.0006 0.0738 1.0000 18.250 1.1123 0.10639 0.09927 -0.0016 0.0700 1.0000 18.500 1.1121 0.10994 0.10301 -0.0029 0.0655 1.0000 18.750 1.1105 0.11364 0.10677 -0.0043 0.0619 1.0000 19.000 1.1095 0.11729 0.11050 -0.0057 0.0584 1.0000 19.250 1.1086 0.12100 0.11434 -0.0072 0.0551 1.0000