XFOIL Version 6.96 Calculated polar for: GOE 332 (PFALZ 61) 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.1353 0.09560 0.09303 -0.0805 0.8068 0.0144 -10.000 -0.1293 0.09252 0.08992 -0.0820 0.7965 0.0148 -9.750 -0.1397 0.08537 0.08273 -0.0856 0.7884 0.0162 -9.500 -0.1304 0.08314 0.08047 -0.0869 0.7795 0.0163 -9.250 -0.1203 0.08109 0.07838 -0.0882 0.7710 0.0164 -9.000 -0.1104 0.07891 0.07618 -0.0895 0.7620 0.0166 -8.750 -0.1014 0.07652 0.07376 -0.0910 0.7535 0.0168 -8.500 -0.0935 0.07383 0.07104 -0.0928 0.7444 0.0170 -8.250 -0.0864 0.07096 0.06815 -0.0949 0.7363 0.0172 -8.000 -0.0803 0.06777 0.06493 -0.0979 0.7273 0.0175 -7.750 -0.0698 0.06348 0.06061 -0.1034 0.7192 0.0180 -7.500 -0.0667 0.04887 0.04586 -0.1229 0.7116 0.0195 -7.250 -0.0762 0.01865 0.01414 -0.1450 0.7075 0.0217 -7.000 -0.0525 0.01687 0.01205 -0.1453 0.6993 0.0220 -6.750 -0.0276 0.01571 0.01064 -0.1453 0.6913 0.0222 -6.500 -0.0015 0.01482 0.00955 -0.1453 0.6837 0.0224 -6.000 0.0516 0.01356 0.00795 -0.1452 0.6690 0.0228 -5.750 0.0787 0.01318 0.00745 -0.1452 0.6619 0.0229 -5.500 0.1062 0.01286 0.00703 -0.1452 0.6556 0.0231 -5.250 0.1329 0.01208 0.00609 -0.1452 0.6493 0.0234 -4.750 0.1877 0.01129 0.00513 -0.1452 0.6376 0.0239 -4.500 0.2154 0.01103 0.00481 -0.1452 0.6318 0.0241 -4.250 0.2429 0.01081 0.00452 -0.1451 0.6262 0.0243 -4.000 0.2710 0.01057 0.00424 -0.1452 0.6213 0.0245 -3.750 0.2990 0.01036 0.00399 -0.1452 0.6158 0.0248 -3.250 0.3547 0.00999 0.00351 -0.1451 0.6040 0.0253 -3.000 0.3825 0.00983 0.00329 -0.1451 0.5973 0.0256 -2.750 0.4103 0.00968 0.00310 -0.1451 0.5918 0.0259 -2.500 0.4385 0.00953 0.00291 -0.1451 0.5873 0.0262 -2.250 0.4666 0.00940 0.00275 -0.1452 0.5824 0.0265 -2.000 0.4944 0.00930 0.00261 -0.1451 0.5775 0.0268 -1.750 0.5228 0.00920 0.00250 -0.1452 0.5732 0.0272 -1.500 0.5510 0.00914 0.00242 -0.1453 0.5685 0.0275 -1.250 0.5789 0.00900 0.00224 -0.1453 0.5634 0.0282 -1.000 0.6069 0.00891 0.00214 -0.1453 0.5586 0.0288 -0.750 0.6351 0.00884 0.00207 -0.1453 0.5534 0.0294 -0.500 0.6631 0.00881 0.00202 -0.1454 0.5482 0.0301 -0.250 0.6908 0.00879 0.00198 -0.1453 0.5431 0.0308 0.000 0.7190 0.00876 0.00195 -0.1454 0.5374 0.0315 0.250 0.7466 0.00877 0.00192 -0.1453 0.5306 0.0323 0.500 0.7744 0.00876 0.00191 -0.1453 0.5247 0.0333 0.750 0.8022 0.00876 0.00190 -0.1453 0.5181 0.0357 1.000 0.8296 0.00879 0.00192 -0.1453 0.5115 0.0389 1.250 0.8573 0.00878 0.00193 -0.1453 0.5040 0.0494 1.500 0.8843 0.00875 0.00201 -0.1452 0.4955 0.1033 1.750 0.9116 0.00880 0.00207 -0.1452 0.4865 0.1213 2.000 0.9385 0.00888 0.00214 -0.1450 0.4781 0.1329 2.250 0.9654 0.00894 0.00222 -0.1449 0.4691 0.1467 2.500 0.9919 0.00904 0.00231 -0.1447 0.4580 0.1638 2.750 1.0178 0.00908 0.00244 -0.1445 0.4441 0.2350 3.000 1.0390 0.00806 0.00282 -0.1438 0.4295 0.8683 3.250 1.0624 0.00810 0.00292 -0.1428 0.4157 1.0000 3.500 1.0880 0.00831 0.00306 -0.1424 0.4031 1.0000 3.750 1.1138 0.00849 0.00318 -0.1421 0.3925 1.0000 4.000 1.1393 0.00870 0.00333 -0.1417 0.3826 1.0000 4.250 1.1646 0.00890 0.00348 -0.1414 0.3724 1.0000 4.500 1.1896 0.00912 0.00364 -0.1409 0.3611 1.0000 4.750 1.2142 0.00937 0.00382 -0.1404 0.3501 1.0000 5.000 1.2389 0.00959 0.00400 -0.1400 0.3404 1.0000 5.250 1.2639 0.00980 0.00418 -0.1396 0.3330 1.0000 5.500 1.2883 0.01003 0.00437 -0.1391 0.3248 1.0000 5.750 1.3129 0.01024 0.00455 -0.1386 0.3182 1.0000 6.000 1.3370 0.01047 0.00476 -0.1380 0.3103 1.0000 6.250 1.3607 0.01071 0.00498 -0.1374 0.3033 1.0000 6.500 1.3843 0.01095 0.00519 -0.1368 0.2953 1.0000 6.750 1.4069 0.01123 0.00545 -0.1360 0.2862 1.0000 7.000 1.4282 0.01158 0.00573 -0.1349 0.2744 1.0000 7.250 1.4489 0.01193 0.00603 -0.1338 0.2615 1.0000 7.500 1.4691 0.01228 0.00633 -0.1326 0.2491 1.0000 7.750 1.4844 0.01279 0.00674 -0.1305 0.2307 1.0000 8.000 1.4987 0.01334 0.00719 -0.1282 0.2103 1.0000 8.250 1.5100 0.01406 0.00778 -0.1255 0.1876 1.0000 8.500 1.5215 0.01478 0.00839 -0.1228 0.1677 1.0000 8.750 1.5341 0.01545 0.00900 -0.1205 0.1529 1.0000 9.000 1.5467 0.01615 0.00963 -0.1182 0.1391 1.0000 9.250 1.5537 0.01714 0.01049 -0.1151 0.1174 1.0000 9.500 1.5531 0.01860 0.01177 -0.1111 0.0870 1.0000 9.750 1.5642 0.01946 0.01261 -0.1089 0.0787 1.0000 10.000 1.5745 0.02041 0.01355 -0.1067 0.0716 1.0000 10.250 1.5858 0.02133 0.01447 -0.1048 0.0638 1.0000 10.500 1.5776 0.02362 0.01657 -0.1008 0.0328 1.0000 10.750 1.5818 0.02520 0.01814 -0.0985 0.0237 1.0000 11.000 1.5902 0.02654 0.01950 -0.0968 0.0200 1.0000 11.250 1.5987 0.02793 0.02092 -0.0952 0.0176 1.0000 11.500 1.6082 0.02927 0.02230 -0.0938 0.0161 1.0000 11.750 1.6163 0.03076 0.02383 -0.0924 0.0149 1.0000 12.000 1.6242 0.03230 0.02541 -0.0911 0.0139 1.0000 12.250 1.6326 0.03383 0.02700 -0.0899 0.0133 1.0000 12.500 1.6398 0.03550 0.02872 -0.0887 0.0127 1.0000 12.750 1.6458 0.03731 0.03058 -0.0875 0.0121 1.0000 13.000 1.6509 0.03925 0.03258 -0.0864 0.0115 1.0000 13.250 1.6552 0.04132 0.03470 -0.0853 0.0111 1.0000 13.500 1.6608 0.04329 0.03674 -0.0844 0.0108 1.0000 13.750 1.6655 0.04539 0.03890 -0.0835 0.0104 1.0000 14.000 1.6692 0.04763 0.04121 -0.0826 0.0101 1.0000 14.250 1.6721 0.05002 0.04366 -0.0818 0.0097 1.0000 14.500 1.6741 0.05255 0.04626 -0.0811 0.0094 1.0000 14.750 1.6748 0.05526 0.04903 -0.0805 0.0090 1.0000 15.000 1.6743 0.05813 0.05197 -0.0798 0.0088 1.0000 15.250 1.6739 0.06107 0.05498 -0.0793 0.0085 1.0000 15.500 1.6745 0.06392 0.05791 -0.0789 0.0084 1.0000 15.750 1.6738 0.06697 0.06105 -0.0785 0.0082 1.0000 16.000 1.6726 0.07011 0.06426 -0.0783 0.0081 1.0000 16.250 1.6710 0.07333 0.06756 -0.0780 0.0079 1.0000 16.500 1.6686 0.07669 0.07101 -0.0779 0.0077 1.0000 16.750 1.6652 0.08025 0.07465 -0.0779 0.0076 1.0000 17.000 1.6614 0.08391 0.07839 -0.0780 0.0074 1.0000 17.250 1.6567 0.08770 0.08226 -0.0782 0.0073 1.0000 17.500 1.6517 0.09156 0.08620 -0.0784 0.0071 1.0000 17.750 1.6461 0.09557 0.09029 -0.0788 0.0070 1.0000 18.000 1.6395 0.09977 0.09459 -0.0793 0.0068 1.0000 18.250 1.6319 0.10418 0.09908 -0.0800 0.0067 1.0000 18.500 1.6231 0.10877 0.10375 -0.0808 0.0065 1.0000