XFOIL Version 6.96 Calculated polar for: WORTMANN FX 05-H-126 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4677 0.08212 0.07917 -0.0002 0.5578 0.0087 -8.500 -0.4697 0.07876 0.07584 -0.0023 0.5572 0.0088 -8.250 -0.4816 0.07488 0.07199 -0.0049 0.5567 0.0089 -8.000 -0.4843 0.07023 0.06733 -0.0087 0.5561 0.0090 -7.750 -0.4849 0.06485 0.06191 -0.0125 0.5554 0.0091 -7.250 -0.5535 0.02496 0.02033 -0.0170 0.5553 0.0110 -7.000 -0.5353 0.02213 0.01710 -0.0160 0.5545 0.0112 -6.750 -0.5124 0.02070 0.01544 -0.0155 0.5536 0.0113 -6.500 -0.4923 0.01833 0.01270 -0.0146 0.5528 0.0115 -6.250 -0.4677 0.01732 0.01154 -0.0142 0.5520 0.0117 -6.000 -0.4418 0.01662 0.01073 -0.0139 0.5512 0.0119 -5.750 -0.4155 0.01601 0.01002 -0.0137 0.5504 0.0120 -5.500 -0.3891 0.01541 0.00933 -0.0135 0.5496 0.0122 -5.250 -0.3624 0.01485 0.00867 -0.0133 0.5488 0.0123 -5.000 -0.3355 0.01432 0.00805 -0.0131 0.5480 0.0125 -4.750 -0.3086 0.01379 0.00743 -0.0129 0.5472 0.0127 -4.500 -0.2815 0.01329 0.00684 -0.0127 0.5464 0.0130 -4.250 -0.2543 0.01287 0.00635 -0.0125 0.5456 0.0133 -4.000 -0.2268 0.01251 0.00592 -0.0124 0.5447 0.0137 -3.750 -0.1995 0.01212 0.00547 -0.0122 0.5438 0.0140 -3.500 -0.1721 0.01172 0.00502 -0.0121 0.5433 0.0143 -3.250 -0.1445 0.01139 0.00465 -0.0119 0.5427 0.0146 -3.000 -0.1168 0.01110 0.00433 -0.0118 0.5419 0.0148 -2.750 -0.0890 0.01085 0.00405 -0.0118 0.5412 0.0150 -2.500 -0.0615 0.01054 0.00371 -0.0116 0.5404 0.0152 -2.250 -0.0347 0.01012 0.00326 -0.0114 0.5397 0.0156 -2.000 -0.0071 0.00986 0.00298 -0.0113 0.5389 0.0160 -1.750 0.0208 0.00966 0.00277 -0.0113 0.5382 0.0165 -1.500 0.0488 0.00948 0.00259 -0.0112 0.5374 0.0169 -1.250 0.0769 0.00934 0.00244 -0.0112 0.5367 0.0176 -1.000 0.1051 0.00921 0.00230 -0.0113 0.5359 0.0183 -0.750 0.1334 0.00908 0.00217 -0.0113 0.5352 0.0189 -0.500 0.1617 0.00898 0.00205 -0.0114 0.5344 0.0195 -0.250 0.1901 0.00889 0.00196 -0.0114 0.5336 0.0199 0.000 0.2184 0.00878 0.00183 -0.0115 0.5326 0.0208 0.250 0.2467 0.00870 0.00173 -0.0115 0.5314 0.0222 0.500 0.2751 0.00865 0.00167 -0.0116 0.5299 0.0239 1.000 0.3316 0.00842 0.00161 -0.0118 0.5279 0.0652 1.250 0.3595 0.00826 0.00159 -0.0119 0.5268 0.1102 1.500 0.3859 0.00791 0.00159 -0.0118 0.5256 0.2406 1.750 0.4065 0.00701 0.00158 -0.0107 0.5241 0.5584 2.000 0.4254 0.00636 0.00158 -0.0089 0.5227 0.7594 2.250 0.5179 0.00594 0.00174 -0.0230 0.5214 0.9872 2.500 0.5609 0.00602 0.00179 -0.0263 0.5203 0.9951 2.750 0.5982 0.00604 0.00180 -0.0284 0.5191 0.9979 3.000 0.6367 0.00608 0.00181 -0.0308 0.5178 1.0000 3.250 0.6639 0.00612 0.00184 -0.0307 0.5165 1.0000 3.500 0.6911 0.00618 0.00189 -0.0307 0.5152 1.0000 3.750 0.7185 0.00620 0.00194 -0.0307 0.5138 1.0000 4.000 0.7459 0.00622 0.00198 -0.0307 0.5115 1.0000 4.250 0.7733 0.00625 0.00203 -0.0307 0.5091 1.0000 4.500 0.8008 0.00625 0.00202 -0.0307 0.5045 1.0000 4.750 0.8283 0.00627 0.00205 -0.0307 0.4983 1.0000 5.000 0.8558 0.00631 0.00210 -0.0308 0.4931 1.0000 5.250 0.8833 0.00636 0.00215 -0.0308 0.4887 1.0000 5.500 0.9108 0.00641 0.00222 -0.0309 0.4817 1.0000 5.750 0.9383 0.00650 0.00229 -0.0310 0.4724 1.0000 6.000 0.9657 0.00662 0.00239 -0.0312 0.4580 1.0000 6.250 0.9924 0.00711 0.00267 -0.0316 0.4109 1.0000 6.500 1.0187 0.00768 0.00310 -0.0320 0.3777 1.0000 6.750 1.0451 0.00810 0.00345 -0.0323 0.3569 1.0000 7.000 1.0707 0.00870 0.00392 -0.0326 0.3254 1.0000 7.250 1.0940 0.00979 0.00474 -0.0332 0.2679 1.0000 7.500 1.1151 0.01110 0.00574 -0.0337 0.2078 1.0000 7.750 1.1345 0.01237 0.00676 -0.0340 0.1615 1.0000 8.000 1.1547 0.01332 0.00759 -0.0341 0.1347 1.0000 8.250 1.1700 0.01474 0.00882 -0.0341 0.0968 1.0000 8.500 1.1863 0.01612 0.01013 -0.0346 0.0789 1.0000 8.750 1.2026 0.01770 0.01171 -0.0358 0.0713 1.0000 9.000 1.2162 0.01908 0.01311 -0.0360 0.0662 1.0000 9.250 1.2200 0.02055 0.01459 -0.0344 0.0623 1.0000 9.500 1.2240 0.02207 0.01610 -0.0330 0.0570 1.0000 9.750 1.2337 0.02331 0.01737 -0.0322 0.0540 1.0000 10.000 1.2429 0.02462 0.01870 -0.0314 0.0510 1.0000 10.250 1.2500 0.02612 0.02018 -0.0305 0.0460 1.0000 10.500 1.2606 0.02738 0.02147 -0.0299 0.0440 1.0000 10.750 1.2680 0.02887 0.02294 -0.0292 0.0391 1.0000 11.000 1.2759 0.03035 0.02443 -0.0285 0.0356 1.0000 11.250 1.2808 0.03207 0.02610 -0.0277 0.0290 1.0000 11.500 1.2863 0.03376 0.02779 -0.0270 0.0240 1.0000 11.750 1.2896 0.03562 0.02961 -0.0262 0.0170 1.0000 12.000 1.2920 0.03766 0.03163 -0.0255 0.0112 1.0000 12.250 1.2978 0.03946 0.03343 -0.0249 0.0086 1.0000 12.500 1.3058 0.04111 0.03512 -0.0245 0.0076 1.0000 12.750 1.3141 0.04277 0.03681 -0.0241 0.0069 1.0000 13.000 1.3228 0.04440 0.03848 -0.0237 0.0064 1.0000 13.250 1.3306 0.04614 0.04027 -0.0234 0.0061 1.0000 13.500 1.3370 0.04804 0.04222 -0.0231 0.0056 1.0000 13.750 1.3447 0.04983 0.04405 -0.0228 0.0052 1.0000 14.000 1.3531 0.05158 0.04585 -0.0226 0.0050 1.0000 14.250 1.3601 0.05351 0.04783 -0.0224 0.0049 1.0000 14.500 1.3676 0.05536 0.04974 -0.0222 0.0047 1.0000 14.750 1.3739 0.05740 0.05183 -0.0220 0.0045 1.0000 15.000 1.3804 0.05944 0.05393 -0.0219 0.0044 1.0000 15.250 1.3863 0.06156 0.05610 -0.0219 0.0043 1.0000 15.500 1.3909 0.06384 0.05844 -0.0218 0.0041 1.0000 15.750 1.3948 0.06624 0.06091 -0.0218 0.0039 1.0000 16.000 1.3975 0.06880 0.06353 -0.0219 0.0038 1.0000 16.250 1.3988 0.07161 0.06641 -0.0220 0.0037 1.0000 16.500 1.3996 0.07446 0.06934 -0.0222 0.0036 1.0000 16.750 1.4023 0.07717 0.07211 -0.0224 0.0035 1.0000 17.000 1.4056 0.07980 0.07481 -0.0227 0.0035 1.0000 17.250 1.4063 0.08283 0.07792 -0.0231 0.0034 1.0000 17.500 1.4073 0.08583 0.08100 -0.0235 0.0034 1.0000 17.750 1.4086 0.08882 0.08407 -0.0241 0.0033 1.0000 18.000 1.4079 0.09214 0.08748 -0.0247 0.0032 1.0000 18.250 1.4058 0.09572 0.09114 -0.0254 0.0032 1.0000 18.500 1.4045 0.09922 0.09473 -0.0262 0.0032 1.0000 18.750 1.4029 0.10276 0.09834 -0.0271 0.0031 1.0000 19.000 1.3977 0.10693 0.10262 -0.0282 0.0031 1.0000 19.250 1.3953 0.11071 0.10648 -0.0293 0.0030 1.0000