XFOIL Version 6.96 Calculated polar for: EPPLER 332 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4085 0.09058 0.08729 -0.0158 1.0000 0.0213 -8.500 -0.4088 0.08673 0.08349 -0.0179 1.0000 0.0216 -8.250 -0.4111 0.08274 0.07955 -0.0208 1.0000 0.0216 -8.000 -0.4176 0.07859 0.07544 -0.0236 1.0000 0.0217 -7.750 -0.4255 0.07508 0.07194 -0.0244 1.0000 0.0218 -7.500 -0.4317 0.07162 0.06848 -0.0244 1.0000 0.0220 -7.250 -0.4335 0.06821 0.06504 -0.0244 1.0000 0.0221 -7.000 -0.4203 0.06361 0.06032 -0.0277 0.9299 0.0224 -6.750 -0.3963 0.05860 0.05501 -0.0324 0.8663 0.0228 -6.250 -0.3833 0.04700 0.04249 -0.0298 0.7996 0.0151 -6.000 -0.3716 0.04541 0.04076 -0.0286 0.7722 0.0140 -5.750 -0.3625 0.03903 0.03376 -0.0250 0.7549 0.0111 -5.500 -0.3500 0.03670 0.03116 -0.0233 0.7352 0.0109 -5.250 -0.3354 0.03427 0.02843 -0.0214 0.7175 0.0107 -5.000 -0.3194 0.03162 0.02541 -0.0194 0.7014 0.0104 -4.750 -0.3015 0.02920 0.02261 -0.0175 0.6863 0.0102 -4.500 -0.2821 0.02670 0.01969 -0.0156 0.6722 0.0099 -4.250 -0.2607 0.02424 0.01677 -0.0137 0.6588 0.0097 -4.000 -0.2372 0.02223 0.01433 -0.0123 0.6452 0.0096 -3.750 -0.2119 0.02043 0.01212 -0.0112 0.6325 0.0096 -3.500 -0.1858 0.01906 0.01044 -0.0104 0.6200 0.0097 -3.250 -0.1595 0.01781 0.00892 -0.0095 0.6079 0.0103 -3.000 -0.1341 0.01695 0.00786 -0.0088 0.5963 0.0106 -2.750 -0.1091 0.01621 0.00697 -0.0079 0.5847 0.0110 -2.500 -0.0851 0.01561 0.00632 -0.0071 0.5737 0.0123 -2.250 -0.0603 0.01526 0.00585 -0.0064 0.5635 0.0146 -2.000 -0.0365 0.01480 0.00534 -0.0055 0.5534 0.0169 -1.750 -0.0122 0.01439 0.00482 -0.0046 0.5435 0.0195 -1.500 0.0118 0.01403 0.00437 -0.0036 0.5346 0.0259 -1.250 0.0349 0.01356 0.00398 -0.0026 0.5255 0.0515 -1.000 0.0549 0.01285 0.00373 -0.0013 0.5176 0.1742 -0.750 0.0860 0.01141 0.00481 0.0000 0.5087 0.9061 -0.250 0.2210 0.01278 0.00563 -0.0139 0.4873 0.9603 0.250 0.2945 0.01279 0.00535 -0.0177 0.4709 0.9678 0.500 0.3231 0.01281 0.00523 -0.0180 0.4635 0.9706 0.750 0.3495 0.01285 0.00517 -0.0178 0.4571 0.9735 1.000 0.3783 0.01286 0.00509 -0.0181 0.4499 0.9755 1.250 0.4090 0.01287 0.00500 -0.0189 0.4436 0.9770 1.500 0.4391 0.01287 0.00494 -0.0195 0.4366 0.9788 1.750 0.4679 0.01292 0.00489 -0.0199 0.4309 0.9806 2.000 0.4963 0.01295 0.00489 -0.0201 0.4243 0.9826 2.250 0.5234 0.01301 0.00490 -0.0202 0.4185 0.9844 2.500 0.5502 0.01309 0.00493 -0.0201 0.4131 0.9862 2.750 0.5800 0.01312 0.00494 -0.0208 0.4067 0.9874 3.000 0.6089 0.01319 0.00495 -0.0212 0.4016 0.9887 3.250 0.6380 0.01324 0.00501 -0.0217 0.3957 0.9902 3.500 0.6660 0.01332 0.00509 -0.0219 0.3900 0.9916 3.750 0.6933 0.01343 0.00516 -0.0221 0.3851 0.9929 4.000 0.7213 0.01352 0.00528 -0.0223 0.3792 0.9944 4.250 0.7488 0.01363 0.00538 -0.0225 0.3740 0.9955 4.500 0.7765 0.01374 0.00552 -0.0227 0.3687 0.9965 4.750 0.8049 0.01384 0.00566 -0.0231 0.3630 0.9978 5.000 0.8328 0.01397 0.00578 -0.0234 0.3577 0.9991 5.250 0.8599 0.01411 0.00599 -0.0235 0.3521 1.0000 5.500 0.8827 0.01426 0.00619 -0.0228 0.3464 1.0000 5.750 0.9052 0.01445 0.00637 -0.0219 0.3415 1.0000 6.000 0.9279 0.01460 0.00662 -0.0212 0.3355 1.0000 6.250 0.9500 0.01479 0.00685 -0.0203 0.3298 1.0000 6.500 0.9720 0.01498 0.00710 -0.0194 0.3238 1.0000 6.750 0.9937 0.01517 0.00736 -0.0184 0.3173 1.0000 7.000 1.0148 0.01540 0.00764 -0.0174 0.3114 1.0000 7.250 1.0360 0.01560 0.00794 -0.0164 0.3043 1.0000 7.500 1.0563 0.01585 0.00822 -0.0152 0.2978 1.0000 7.750 1.0768 0.01608 0.00856 -0.0141 0.2902 1.0000 8.000 1.0962 0.01635 0.00889 -0.0128 0.2829 1.0000 8.250 1.1155 0.01661 0.00925 -0.0115 0.2744 1.0000 8.500 1.1339 0.01690 0.00961 -0.0100 0.2657 1.0000 8.750 1.1512 0.01723 0.00998 -0.0084 0.2569 1.0000 9.000 1.1685 0.01755 0.01042 -0.0068 0.2468 1.0000 9.250 1.1844 0.01791 0.01085 -0.0050 0.2365 1.0000 9.500 1.1988 0.01833 0.01131 -0.0029 0.2255 1.0000 9.750 1.2116 0.01879 0.01181 -0.0007 0.2144 1.0000 10.000 1.2226 0.01930 0.01235 0.0018 0.2023 1.0000 10.250 1.2322 0.01985 0.01294 0.0046 0.1899 1.0000 10.500 1.2396 0.02046 0.01359 0.0076 0.1773 1.0000 10.750 1.2453 0.02111 0.01428 0.0108 0.1656 1.0000 11.000 1.2489 0.02185 0.01503 0.0142 0.1541 1.0000 11.250 1.2498 0.02266 0.01586 0.0179 0.1431 1.0000 11.500 1.2460 0.02356 0.01676 0.0222 0.1335 1.0000 11.750 1.2431 0.02469 0.01790 0.0256 0.1240 1.0000 12.000 1.2424 0.02599 0.01925 0.0281 0.1147 1.0000 12.250 1.2405 0.02765 0.02095 0.0300 0.1063 1.0000 12.500 1.2365 0.02975 0.02308 0.0312 0.0984 1.0000 12.750 1.2350 0.03193 0.02533 0.0319 0.0912 1.0000 13.000 1.2308 0.03456 0.02804 0.0322 0.0851 1.0000 13.250 1.2270 0.03734 0.03090 0.0321 0.0791 1.0000 13.500 1.2209 0.04049 0.03411 0.0318 0.0739 1.0000 13.750 1.2157 0.04367 0.03738 0.0314 0.0688 1.0000 14.000 1.2068 0.04735 0.04110 0.0307 0.0650 1.0000 14.250 1.2016 0.05069 0.04454 0.0300 0.0608 1.0000 14.500 1.1931 0.05448 0.04841 0.0291 0.0571 1.0000 15.000 1.1763 0.06231 0.05642 0.0270 0.0508 1.0000 15.250 1.1686 0.06637 0.06055 0.0257 0.0479 1.0000 15.500 1.1580 0.07095 0.06518 0.0241 0.0453 1.0000 15.750 1.1518 0.07504 0.06937 0.0227 0.0423 1.0000 16.000 1.1452 0.07929 0.07371 0.0212 0.0400 1.0000 16.250 1.1361 0.08397 0.07846 0.0193 0.0377 1.0000 16.500 1.1257 0.08897 0.08351 0.0173 0.0359 1.0000 16.750 1.1214 0.09314 0.08782 0.0157 0.0337 1.0000 17.000 1.1147 0.09773 0.09251 0.0138 0.0318 1.0000 17.250 1.1069 0.10260 0.09744 0.0117 0.0302 1.0000