XFOIL Version 6.94 Calculated polar for: S3021-095-84 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3601 0.00646 0.00187 -0.0681 0.6803 1.0000 0.500 0.4089 0.00656 0.00181 -0.0666 0.6600 1.0000 1.000 0.4581 0.00670 0.00179 -0.0652 0.6403 1.0000 1.500 0.5077 0.00686 0.00182 -0.0638 0.6204 1.0000 2.000 0.5577 0.00701 0.00190 -0.0625 0.5991 1.0000 2.500 0.6075 0.00720 0.00200 -0.0611 0.5767 1.0000 3.000 0.6574 0.00742 0.00214 -0.0598 0.5529 1.0000 3.500 0.7071 0.00766 0.00232 -0.0585 0.5262 1.0000 4.000 0.7567 0.00793 0.00253 -0.0571 0.4970 1.0000 4.500 0.8058 0.00827 0.00282 -0.0558 0.4635 1.0000 5.000 0.8541 0.00871 0.00315 -0.0543 0.4249 1.0000 5.500 0.9014 0.00928 0.00358 -0.0528 0.3738 1.0000 6.000 0.9466 0.01006 0.00412 -0.0511 0.3125 1.0000 6.500 0.9903 0.01102 0.00479 -0.0492 0.2447 1.0000 7.000 1.0337 0.01203 0.00559 -0.0474 0.1874 1.0000 7.500 1.0727 0.01343 0.00660 -0.0451 0.1150 1.0000 8.000 1.1054 0.01535 0.00806 -0.0419 0.0411 1.0000 8.500 1.1375 0.01725 0.00987 -0.0384 0.0133 1.0000 9.000 1.1728 0.01871 0.01152 -0.0353 0.0116 1.0000 9.500 1.1987 0.02066 0.01367 -0.0310 0.0105 1.0000 10.000 1.2055 0.02316 0.01642 -0.0241 0.0097 1.0000 10.500 1.2158 0.02561 0.01908 -0.0187 0.0095 1.0000 11.000 1.2232 0.02865 0.02237 -0.0142 0.0093 1.0000 11.500 1.2288 0.03236 0.02632 -0.0107 0.0091 1.0000 12.000 1.2334 0.03665 0.03087 -0.0081 0.0089 1.0000 12.500 1.2355 0.04172 0.03623 -0.0061 0.0088 1.0000 13.000 1.2357 0.04734 0.04216 -0.0050 0.0087 1.0000 13.500 1.2298 0.05411 0.04928 -0.0047 0.0087 1.0000 14.000 1.2166 0.06223 0.05777 -0.0058 0.0088 1.0000 14.500 1.1950 0.07220 0.06812 -0.0088 0.0089 1.0000 15.000 1.1681 0.08403 0.08031 -0.0139 0.0091 1.0000 15.500 1.1367 0.09795 0.09458 -0.0211 0.0092 1.0000 16.000 1.1037 0.11379 0.11073 -0.0304 0.0093 1.0000 16.500 1.0661 0.13221 0.12944 -0.0415 0.0095 1.0000 17.000 1.0365 0.15012 0.14757 -0.0521 0.0099 1.0000 17.500 1.0167 0.16760 0.16522 -0.0627 0.0101 1.0000