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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.0993 0.10262 0.09895 -0.0948 0.8632 0.0694 -12.250 -0.0981 0.09859 0.09484 -0.0971 0.8492 0.0720 -12.000 -0.1558 0.08831 0.08462 -0.1069 0.8488 0.0754 -11.750 -0.1399 0.08491 0.08113 -0.1058 0.8342 0.0764 -11.500 -0.1244 0.08281 0.07893 -0.1049 0.8217 0.0774 -11.250 -0.1168 0.07999 0.07603 -0.1050 0.8121 0.0785 -11.000 -0.2147 0.07626 0.07247 -0.1176 0.8601 0.0779 -10.750 -0.2139 0.07164 0.06772 -0.1211 0.8411 0.0792 -10.500 -0.4354 0.04624 0.04092 -0.1182 0.8254 0.0396 -10.250 -0.4426 0.04381 0.03827 -0.1148 0.8132 0.0390 -10.000 -0.4503 0.04144 0.03566 -0.1111 0.8028 0.0383 -9.750 -0.4880 0.03662 0.02977 -0.1027 0.7944 0.0347 -9.500 -0.4809 0.03503 0.02784 -0.1000 0.7862 0.0344 -9.250 -0.4659 0.03269 0.02525 -0.0987 0.7796 0.0342 -9.000 -0.4506 0.03077 0.02301 -0.0972 0.7736 0.0342 -8.750 -0.4331 0.02911 0.02108 -0.0958 0.7672 0.0343 -8.500 -0.4107 0.02740 0.01910 -0.0952 0.7621 0.0346 -8.250 -0.3814 0.02567 0.01728 -0.0959 0.7575 0.0353 -8.000 -0.3560 0.02457 0.01615 -0.0958 0.7521 0.0363 -7.750 -0.3301 0.02361 0.01509 -0.0957 0.7472 0.0374 -7.500 -0.3055 0.02290 0.01423 -0.0953 0.7431 0.0395 -7.250 -0.2801 0.02191 0.01324 -0.0952 0.7390 0.0417 -7.000 -0.2582 0.02121 0.01256 -0.0945 0.7347 0.0437 -6.750 -0.2369 0.02057 0.01186 -0.0935 0.7309 0.0467 -6.500 -0.2193 0.01980 0.01111 -0.0921 0.7276 0.0504 -6.250 -0.2017 0.01923 0.01049 -0.0905 0.7248 0.0565 -6.000 -0.1887 0.01863 0.01002 -0.0882 0.7213 0.0683 -5.750 -0.1766 0.01795 0.00953 -0.0858 0.7179 0.0946 -5.500 -0.1619 0.01743 0.00914 -0.0839 0.7147 0.1272 -5.250 -0.1457 0.01697 0.00882 -0.0822 0.7117 0.1619 -5.000 -0.1306 0.01647 0.00852 -0.0803 0.7091 0.2100 -4.750 -0.1205 0.01585 0.00829 -0.0777 0.7066 0.2873 -4.500 -0.1181 0.01502 0.00812 -0.0738 0.7037 0.4100 -4.250 -0.1139 0.01429 0.00826 -0.0694 0.7010 0.5733 -4.000 -0.0900 0.01487 0.00926 -0.0672 0.6985 0.6859 -3.750 -0.0667 0.01539 0.00970 -0.0657 0.6962 0.7227 -3.500 -0.0436 0.01591 0.01010 -0.0642 0.6941 0.7468 -3.250 -0.0167 0.01656 0.01063 -0.0632 0.6923 0.7634 -3.000 0.0144 0.01733 0.01130 -0.0627 0.6905 0.7751 -2.750 0.0367 0.01786 0.01183 -0.0611 0.6879 0.7870 -2.500 0.0565 0.01828 0.01219 -0.0593 0.6852 0.8001 -2.250 0.0898 0.01898 0.01286 -0.0591 0.6831 0.8062 -2.000 0.1101 0.01930 0.01312 -0.0575 0.6810 0.8179 -1.750 0.1495 0.01998 0.01373 -0.0585 0.6792 0.8240 -1.500 0.1745 0.02035 0.01404 -0.0575 0.6775 0.8358 -1.250 0.2264 0.02102 0.01461 -0.0609 0.6760 0.8427 -1.000 0.2524 0.02124 0.01476 -0.0604 0.6744 0.8527 -0.750 0.2970 0.02159 0.01505 -0.0634 0.6724 0.8569 -0.500 0.2983 0.02177 0.01528 -0.0588 0.6700 0.8680 -0.250 0.3388 0.02201 0.01550 -0.0614 0.6679 0.8709 0.000 0.3751 0.02219 0.01566 -0.0634 0.6658 0.8748 0.250 0.3717 0.02226 0.01573 -0.0579 0.6635 0.8843 0.500 0.4149 0.02232 0.01574 -0.0612 0.6616 0.8865 0.750 0.4548 0.02241 0.01579 -0.0640 0.6600 0.8893 1.000 0.4817 0.02248 0.01582 -0.0642 0.6584 0.8937 1.250 0.4843 0.02257 0.01587 -0.0597 0.6568 0.9005 1.500 0.5096 0.02297 0.01637 -0.0602 0.6538 0.9034 1.750 0.5249 0.02338 0.01684 -0.0587 0.6507 0.9076 2.000 0.5016 0.02362 0.01714 -0.0496 0.6474 0.9159 2.250 0.5383 0.02373 0.01724 -0.0518 0.6453 0.9175 2.500 0.5754 0.02376 0.01725 -0.0541 0.6436 0.9192 2.750 0.6088 0.02377 0.01723 -0.0556 0.6418 0.9214 3.000 0.6365 0.02382 0.01725 -0.0559 0.6402 0.9241 3.250 0.5746 0.02516 0.01881 -0.0410 0.6330 0.9336 3.500 0.5939 0.02550 0.01919 -0.0403 0.6297 0.9366 3.750 0.6198 0.02544 0.01912 -0.0403 0.6275 0.9390 4.000 0.6481 0.02526 0.01891 -0.0405 0.6258 0.9415 4.250 0.6657 0.02506 0.01870 -0.0387 0.6242 0.9450 4.500 0.6065 0.02763 0.02148 -0.0266 0.6129 0.9541 4.750 0.6432 0.02728 0.02113 -0.0282 0.6110 0.9557 5.000 0.6825 0.02686 0.02070 -0.0301 0.6096 0.9568 5.250 0.7312 0.02629 0.02012 -0.0336 0.6085 0.9570 5.500 0.7733 0.02587 0.01969 -0.0360 0.6071 0.9579 5.750 0.7224 0.02862 0.02264 -0.0261 0.5945 0.9678 6.000 0.7783 0.02777 0.02179 -0.0305 0.5936 0.9671 6.250 0.8350 0.02684 0.02087 -0.0350 0.5925 0.9665 6.500 0.8892 0.02602 0.02005 -0.0392 0.5911 0.9661 6.750 0.8490 0.02833 0.02254 -0.0307 0.5793 0.9756 7.000 0.9086 0.02707 0.02129 -0.0352 0.5781 0.9747 7.250 0.9665 0.02579 0.02002 -0.0396 0.5763 0.9740 7.500 1.0265 0.02451 0.01872 -0.0444 0.5743 0.9732 7.750 1.0248 0.02557 0.01997 -0.0412 0.5648 0.9796 8.000 1.0803 0.02426 0.01867 -0.0453 0.5611 0.9794 8.250 1.1430 0.02286 0.01722 -0.0506 0.5579 0.9781 8.500 1.1434 0.02343 0.01799 -0.0471 0.5488 0.9847 8.750 1.1937 0.02229 0.01685 -0.0506 0.5436 0.9851 9.000 1.2180 0.02215 0.01684 -0.0506 0.5355 0.9891 9.250 1.2537 0.02144 0.01618 -0.0520 0.5281 0.9920 9.500 1.2730 0.02135 0.01622 -0.0513 0.5187 0.9984 9.750 1.2694 0.02085 0.01574 -0.0457 0.5119 1.0000 10.000 1.2300 0.02093 0.01584 -0.0346 0.5061 1.0000 10.250 1.2350 0.02087 0.01583 -0.0314 0.4962 1.0000 10.500 1.2273 0.02165 0.01670 -0.0273 0.4840 1.0000 10.750 1.2285 0.02232 0.01743 -0.0245 0.4700 1.0000 11.000 1.2331 0.02300 0.01811 -0.0222 0.4534 1.0000 11.250 1.2416 0.02358 0.01864 -0.0204 0.4337 1.0000 11.500 1.2434 0.02471 0.01969 -0.0182 0.4104 1.0000 11.750 1.2458 0.02589 0.02070 -0.0160 0.3852 1.0000 12.000 1.2420 0.02759 0.02225 -0.0135 0.3599 1.0000 12.250 1.2354 0.02963 0.02416 -0.0111 0.3356 1.0000 12.500 1.2275 0.03186 0.02626 -0.0088 0.3127 1.0000 12.750 1.2195 0.03425 0.02854 -0.0068 0.2906 1.0000 13.000 1.2116 0.03676 0.03094 -0.0050 0.2692 1.0000 13.250 1.2039 0.03937 0.03343 -0.0034 0.2495 1.0000 13.500 1.1979 0.04198 0.03595 -0.0021 0.2302 1.0000 13.750 1.1932 0.04458 0.03848 -0.0009 0.2122 1.0000 14.000 1.1890 0.04723 0.04105 0.0000 0.1955 1.0000 14.250 1.1861 0.04984 0.04359 0.0008 0.1802 1.0000 14.500 1.1839 0.05245 0.04615 0.0015 0.1662 1.0000 14.750 1.1826 0.05506 0.04870 0.0020 0.1534 1.0000 15.000 1.1816 0.05769 0.05127 0.0025 0.1419 1.0000 15.250 1.1799 0.06043 0.05393 0.0028 0.1313 1.0000 15.500 1.1816 0.06296 0.05649 0.0030 0.1209 1.0000 15.750 1.1828 0.06555 0.05908 0.0031 0.1120 1.0000 16.000 1.1823 0.06832 0.06176 0.0032 0.1042 1.0000 16.250 1.1854 0.07087 0.06441 0.0030 0.0968 1.0000 16.500 1.1864 0.07356 0.06707 0.0030 0.0905 1.0000 16.750 1.1887 0.07628 0.06985 0.0027 0.0843 1.0000 17.000 1.1903 0.07899 0.07254 0.0025 0.0792 1.0000 17.250 1.1928 0.08177 0.07541 0.0021 0.0740 1.0000 17.500 1.1936 0.08460 0.07819 0.0018 0.0695 1.0000 17.750 1.1959 0.08749 0.08122 0.0012 0.0650 1.0000 18.000 1.1958 0.09059 0.08427 0.0006 0.0610 1.0000 18.250 1.1979 0.09354 0.08735 0.0000 0.0571 1.0000 18.500 1.1972 0.09690 0.09075 -0.0009 0.0534 1.0000 18.750 1.1982 0.09991 0.09380 -0.0015 0.0498 1.0000