XFOIL Version 6.96 Calculated polar for: EPPLER 327 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.4455 0.08783 0.08565 -0.0251 1.0000 0.0150 -9.500 -0.4480 0.08373 0.08158 -0.0274 1.0000 0.0154 -9.250 -0.4597 0.07774 0.07561 -0.0324 1.0000 0.0158 -9.000 -0.4762 0.07260 0.07044 -0.0349 1.0000 0.0155 -8.750 -0.4935 0.06874 0.06654 -0.0347 1.0000 0.0157 -8.500 -0.5118 0.06564 0.06339 -0.0323 1.0000 0.0155 -8.250 -0.5265 0.06285 0.06055 -0.0290 1.0000 0.0156 -8.000 -0.5356 0.05988 0.05750 -0.0262 1.0000 0.0161 -7.750 -0.5428 0.05671 0.05423 -0.0230 1.0000 0.0166 -7.500 -0.5615 0.05092 0.04789 -0.0160 1.0000 0.0178 -7.250 -0.5501 0.04627 0.04322 -0.0173 0.9924 0.0183 -7.000 -0.5266 0.04358 0.04045 -0.0191 0.9710 0.0186 -6.750 -0.4874 0.04021 0.03689 -0.0241 0.9328 0.0195 -6.500 -0.4613 0.03460 0.03037 -0.0243 0.8807 0.0224 -6.250 -0.4435 0.03292 0.02856 -0.0236 0.8328 0.0230 -6.000 -0.4279 0.03178 0.02723 -0.0220 0.7986 0.0237 -5.750 -0.4120 0.03023 0.02539 -0.0198 0.7720 0.0253 -4.750 -0.3291 0.01779 0.01084 -0.0104 0.6978 0.0146 -4.500 -0.3019 0.01664 0.00956 -0.0100 0.6810 0.0139 -4.250 -0.2752 0.01542 0.00820 -0.0095 0.6656 0.0134 -4.000 -0.2498 0.01450 0.00713 -0.0088 0.6506 0.0132 -3.750 -0.2262 0.01375 0.00626 -0.0077 0.6364 0.0133 -3.500 -0.2035 0.01319 0.00561 -0.0066 0.6229 0.0133 -3.250 -0.1811 0.01270 0.00504 -0.0054 0.6101 0.0136 -3.000 -0.1583 0.01231 0.00456 -0.0043 0.5976 0.0140 -2.750 -0.1368 0.01182 0.00402 -0.0029 0.5859 0.0156 -2.500 -0.1132 0.01157 0.00368 -0.0020 0.5745 0.0178 -2.250 -0.0912 0.01114 0.00327 -0.0007 0.5634 0.0299 -2.000 -0.0727 0.01047 0.00299 0.0010 0.5536 0.1240 -1.750 -0.0688 0.00894 0.00259 0.0049 0.5453 0.4363 -1.500 -0.0731 0.00764 0.00272 0.0118 0.5375 0.7970 -1.250 -0.0509 0.00809 0.00314 0.0139 0.5281 0.8409 -1.000 -0.0268 0.00864 0.00368 0.0158 0.5185 0.8640 -0.750 -0.0008 0.00897 0.00393 0.0169 0.5100 0.8735 -0.500 0.0236 0.00927 0.00414 0.0181 0.5013 0.8840 -0.250 0.0534 0.00979 0.00462 0.0189 0.4927 0.8925 0.000 0.0779 0.01004 0.00478 0.0200 0.4845 0.9010 0.250 0.1139 0.01044 0.00512 0.0192 0.4766 0.9056 0.500 0.1419 0.01050 0.00510 0.0192 0.4690 0.9080 0.750 0.1663 0.01048 0.00500 0.0198 0.4620 0.9103 1.000 0.1882 0.01040 0.00487 0.0208 0.4552 0.9131 1.250 0.2098 0.01037 0.00473 0.0218 0.4492 0.9156 1.500 0.2374 0.01031 0.00466 0.0218 0.4426 0.9166 1.750 0.2647 0.01034 0.00461 0.0219 0.4363 0.9178 2.000 0.2920 0.01035 0.00459 0.0219 0.4303 0.9190 2.250 0.3187 0.01035 0.00456 0.0220 0.4243 0.9201 2.500 0.3446 0.01042 0.00455 0.0222 0.4185 0.9216 2.750 0.3710 0.01040 0.00454 0.0224 0.4131 0.9232 3.000 0.3965 0.01041 0.00451 0.0227 0.4077 0.9247 3.250 0.4213 0.01047 0.00450 0.0231 0.4024 0.9263 3.500 0.4466 0.01044 0.00450 0.0234 0.3972 0.9282 3.750 0.4712 0.01046 0.00450 0.0238 0.3922 0.9300 4.000 0.4969 0.01054 0.00451 0.0240 0.3871 0.9312 4.250 0.5240 0.01052 0.00454 0.0240 0.3821 0.9322 4.500 0.5506 0.01057 0.00458 0.0241 0.3770 0.9333 4.750 0.5766 0.01070 0.00465 0.0242 0.3719 0.9346 5.000 0.6033 0.01071 0.00472 0.0243 0.3672 0.9360 5.250 0.6294 0.01077 0.00479 0.0244 0.3619 0.9377 5.500 0.6546 0.01091 0.00489 0.0247 0.3569 0.9395 5.750 0.6805 0.01093 0.00497 0.0249 0.3520 0.9412 6.000 0.7057 0.01098 0.00504 0.0251 0.3467 0.9430 6.250 0.7299 0.01113 0.00515 0.0255 0.3415 0.9448 6.500 0.7563 0.01114 0.00524 0.0255 0.3362 0.9462 6.750 0.7825 0.01122 0.00535 0.0256 0.3306 0.9477 7.000 0.8081 0.01138 0.00550 0.0258 0.3252 0.9493 7.250 0.8343 0.01144 0.00564 0.0258 0.3193 0.9512 7.500 0.8588 0.01157 0.00577 0.0262 0.3132 0.9536 7.750 0.8834 0.01168 0.00594 0.0265 0.3074 0.9560 8.000 0.9069 0.01177 0.00606 0.0271 0.3007 0.9586 8.250 0.9319 0.01192 0.00624 0.0272 0.2941 0.9607 8.500 0.9589 0.01205 0.00643 0.0270 0.2867 0.9625 8.750 0.9849 0.01224 0.00665 0.0269 0.2791 0.9648 9.000 1.0108 0.01241 0.00687 0.0269 0.2709 0.9673 9.250 1.0350 0.01260 0.00711 0.0271 0.2626 0.9705 9.500 1.0594 0.01286 0.00737 0.0272 0.2532 0.9734 9.750 1.0887 0.01312 0.00769 0.0263 0.2425 0.9752 10.000 1.1173 0.01345 0.00805 0.0254 0.2306 0.9774 10.250 1.1447 0.01384 0.00845 0.0247 0.2178 0.9801 10.500 1.1692 0.01429 0.00890 0.0245 0.2029 0.9838 10.750 1.1973 0.01489 0.00947 0.0232 0.1856 0.9857 11.000 1.2244 0.01560 0.01014 0.0220 0.1681 0.9878 11.250 1.2501 0.01635 0.01086 0.0211 0.1502 0.9908 11.500 1.2732 0.01722 0.01169 0.0204 0.1334 0.9950 11.750 1.2954 0.01822 0.01266 0.0195 0.1174 0.9999 12.000 1.2716 0.01840 0.01286 0.0282 0.1147 1.0000 12.250 1.2735 0.01927 0.01372 0.0312 0.1050 1.0000 12.500 1.2770 0.02031 0.01476 0.0336 0.0958 1.0000 12.750 1.2788 0.02159 0.01604 0.0356 0.0874 1.0000 13.000 1.2774 0.02325 0.01770 0.0374 0.0799 1.0000 13.250 1.2792 0.02491 0.01941 0.0385 0.0733 1.0000 13.500 1.2775 0.02704 0.02157 0.0393 0.0673 1.0000 13.750 1.2756 0.02940 0.02397 0.0398 0.0620 1.0000 14.000 1.2718 0.03208 0.02672 0.0399 0.0573 1.0000 14.250 1.2685 0.03487 0.02956 0.0398 0.0532 1.0000 14.500 1.2581 0.03848 0.03321 0.0395 0.0495 1.0000 14.750 1.2559 0.04133 0.03615 0.0391 0.0464 1.0000 15.000 1.2466 0.04501 0.03989 0.0385 0.0436 1.0000 15.250 1.2335 0.04921 0.04414 0.0376 0.0412 1.0000 15.500 1.2297 0.05242 0.04745 0.0369 0.0387 1.0000 15.750 1.2189 0.05656 0.05166 0.0358 0.0368 1.0000 16.000 1.2064 0.06108 0.05624 0.0345 0.0350 1.0000 16.250 1.1962 0.06544 0.06068 0.0331 0.0334 1.0000 16.500 1.1910 0.06926 0.06460 0.0318 0.0316 1.0000 16.750 1.1823 0.07363 0.06902 0.0302 0.0300 1.0000 17.000 1.1704 0.07855 0.07399 0.0284 0.0287 1.0000 17.250 1.1602 0.08331 0.07883 0.0265 0.0274 1.0000 17.500 1.1564 0.08726 0.08287 0.0249 0.0262 1.0000 17.750 1.1512 0.09150 0.08719 0.0231 0.0247 1.0000 18.000 1.1414 0.09649 0.09220 0.0209 0.0231 1.0000