XFOIL Version 6.96 Calculated polar for: NACA M17 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5279 0.08939 0.08716 0.0072 0.7182 0.0067 -8.250 -0.5333 0.08299 0.08072 0.0014 0.7099 0.0072 -8.000 -0.5368 0.07380 0.07147 -0.0067 0.7028 0.0079 -7.750 -0.5230 0.07032 0.06792 -0.0096 0.6935 0.0081 -7.250 -0.5652 0.01902 0.01460 -0.0244 0.6929 0.0146 -7.000 -0.5329 0.02110 0.01688 -0.0248 0.6823 0.0147 -6.750 -0.4630 0.04943 0.04652 -0.0225 0.6624 0.0109 -6.250 -0.4364 0.03003 0.02627 -0.0258 0.6520 0.0147 -6.000 -0.4112 0.02902 0.02513 -0.0258 0.6440 0.0150 -5.750 -0.3855 0.02835 0.02439 -0.0259 0.6371 0.0154 -5.500 -0.3736 0.01805 0.01310 -0.0243 0.6327 0.0187 -5.250 -0.3472 0.01731 0.01217 -0.0241 0.6259 0.0193 -5.000 -0.3198 0.01702 0.01179 -0.0241 0.6191 0.0196 -4.750 -0.2923 0.01676 0.01142 -0.0240 0.6127 0.0198 -4.500 -0.2681 0.01479 0.00914 -0.0237 0.6072 0.0208 -4.250 -0.2407 0.01443 0.00870 -0.0237 0.6008 0.0212 -4.000 -0.2132 0.01403 0.00821 -0.0237 0.5952 0.0216 -3.750 -0.1856 0.01366 0.00776 -0.0237 0.5897 0.0220 -3.500 -0.1579 0.01337 0.00738 -0.0237 0.5839 0.0225 -3.250 -0.1303 0.01290 0.00680 -0.0237 0.5786 0.0230 -3.000 -0.1025 0.01241 0.00621 -0.0236 0.5728 0.0234 -2.500 -0.0469 0.01148 0.00508 -0.0236 0.5627 0.0241 -2.250 -0.0191 0.01105 0.00457 -0.0236 0.5570 0.0243 -2.000 0.0088 0.01066 0.00410 -0.0235 0.5518 0.0245 -1.750 0.0366 0.01028 0.00367 -0.0235 0.5467 0.0246 -1.500 0.0645 0.00996 0.00327 -0.0235 0.5416 0.0248 -1.250 0.0924 0.00971 0.00299 -0.0235 0.5367 0.0252 -1.000 0.1203 0.00945 0.00268 -0.0235 0.5314 0.0254 -0.750 0.1481 0.00920 0.00238 -0.0234 0.5259 0.0255 -0.500 0.1760 0.00899 0.00213 -0.0234 0.5213 0.0257 -0.250 0.2040 0.00881 0.00193 -0.0235 0.5164 0.0260 0.000 0.2320 0.00868 0.00176 -0.0235 0.5111 0.0264 0.250 0.2602 0.00858 0.00164 -0.0236 0.5061 0.0269 0.500 0.2885 0.00851 0.00157 -0.0237 0.5008 0.0273 0.750 0.3167 0.00847 0.00151 -0.0238 0.4959 0.0277 1.000 0.3449 0.00837 0.00140 -0.0239 0.4913 0.0285 1.250 0.3731 0.00829 0.00130 -0.0240 0.4859 0.0296 1.500 0.4014 0.00826 0.00124 -0.0241 0.4807 0.0305 1.750 0.4298 0.00822 0.00121 -0.0242 0.4762 0.0313 2.000 0.4581 0.00821 0.00120 -0.0244 0.4706 0.0321 2.250 0.4864 0.00823 0.00120 -0.0245 0.4644 0.0332 2.500 0.5147 0.00822 0.00121 -0.0247 0.4573 0.0351 2.750 0.5429 0.00826 0.00124 -0.0248 0.4493 0.0381 3.000 0.5709 0.00821 0.00130 -0.0250 0.4399 0.0888 3.250 0.5986 0.00811 0.00140 -0.0251 0.4307 0.1895 3.500 0.6114 0.00634 0.00155 -0.0222 0.4238 0.9491 3.750 0.6483 0.00644 0.00168 -0.0242 0.4173 0.9832 4.000 0.6925 0.00660 0.00182 -0.0280 0.4088 0.9937 4.250 0.7361 0.00672 0.00194 -0.0317 0.4020 0.9972 4.500 0.7787 0.00689 0.00208 -0.0353 0.3915 1.0000 4.750 0.8046 0.00704 0.00218 -0.0350 0.3743 1.0000 5.000 0.8303 0.00723 0.00231 -0.0348 0.3540 1.0000 5.250 0.8557 0.00748 0.00246 -0.0345 0.3293 1.0000 5.500 0.8796 0.00806 0.00277 -0.0342 0.2719 1.0000 5.750 0.9020 0.00893 0.00326 -0.0339 0.1972 1.0000 6.000 0.9248 0.00958 0.00368 -0.0334 0.1516 1.0000 6.250 0.9439 0.01087 0.00447 -0.0327 0.0561 1.0000 6.500 0.9658 0.01155 0.00499 -0.0320 0.0237 1.0000 6.750 0.9893 0.01192 0.00533 -0.0315 0.0165 1.0000 7.000 1.0128 0.01229 0.00570 -0.0309 0.0128 1.0000 7.250 1.0366 0.01259 0.00603 -0.0304 0.0117 1.0000 7.500 1.0602 0.01293 0.00639 -0.0299 0.0106 1.0000 7.750 1.0832 0.01333 0.00680 -0.0294 0.0094 1.0000 8.000 1.1056 0.01379 0.00731 -0.0287 0.0084 1.0000 8.250 1.1287 0.01416 0.00770 -0.0282 0.0078 1.0000 8.500 1.1515 0.01456 0.00813 -0.0276 0.0072 1.0000 8.750 1.1739 0.01501 0.00861 -0.0271 0.0067 1.0000 9.000 1.1955 0.01553 0.00915 -0.0265 0.0062 1.0000 9.250 1.2157 0.01621 0.00989 -0.0257 0.0057 1.0000 9.500 1.2370 0.01674 0.01048 -0.0250 0.0055 1.0000 9.750 1.2575 0.01732 0.01112 -0.0243 0.0053 1.0000 10.000 1.2773 0.01794 0.01180 -0.0236 0.0050 1.0000 10.250 1.2967 0.01857 0.01248 -0.0228 0.0048 1.0000 10.500 1.3154 0.01921 0.01316 -0.0220 0.0045 1.0000 10.750 1.3331 0.01990 0.01388 -0.0210 0.0043 1.0000 11.000 1.3483 0.02074 0.01479 -0.0199 0.0041 1.0000 11.250 1.3570 0.02191 0.01605 -0.0179 0.0039 1.0000 11.500 1.3633 0.02305 0.01728 -0.0158 0.0038 1.0000 11.750 1.3716 0.02432 0.01863 -0.0146 0.0037 1.0000 12.000 1.3798 0.02579 0.02019 -0.0137 0.0036 1.0000 12.250 1.3875 0.02744 0.02193 -0.0131 0.0035 1.0000 12.500 1.3943 0.02928 0.02387 -0.0127 0.0035 1.0000 12.750 1.4003 0.03127 0.02595 -0.0124 0.0034 1.0000 13.000 1.4052 0.03343 0.02821 -0.0122 0.0033 1.0000 13.250 1.4092 0.03572 0.03059 -0.0120 0.0032 1.0000 13.500 1.4124 0.03814 0.03310 -0.0119 0.0032 1.0000 13.750 1.4148 0.04065 0.03573 -0.0119 0.0031 1.0000 14.000 1.4160 0.04334 0.03851 -0.0119 0.0030 1.0000 14.250 1.4165 0.04612 0.04139 -0.0120 0.0030 1.0000 14.500 1.4160 0.04905 0.04440 -0.0122 0.0029 1.0000 14.750 1.4145 0.05214 0.04759 -0.0124 0.0029 1.0000 15.000 1.4125 0.05531 0.05086 -0.0128 0.0028 1.0000 15.250 1.4096 0.05868 0.05432 -0.0132 0.0028 1.0000 15.500 1.4065 0.06224 0.05798 -0.0139 0.0028 1.0000 15.750 1.4030 0.06593 0.06177 -0.0147 0.0027 1.0000 16.000 1.3984 0.06986 0.06579 -0.0156 0.0027 1.0000 16.250 1.3930 0.07401 0.07004 -0.0167 0.0027 1.0000 16.500 1.3868 0.07836 0.07450 -0.0179 0.0026 1.0000 16.750 1.3790 0.08301 0.07926 -0.0193 0.0026 1.0000 17.000 1.3703 0.08795 0.08430 -0.0208 0.0026 1.0000 17.250 1.3607 0.09311 0.08958 -0.0226 0.0025 1.0000 17.500 1.3497 0.09858 0.09516 -0.0245 0.0025 1.0000 17.750 1.3378 0.10433 0.10102 -0.0266 0.0025 1.0000 18.000 1.3253 0.11032 0.10714 -0.0290 0.0025 1.0000 18.250 1.3118 0.11660 0.11354 -0.0315 0.0024 1.0000 18.500 1.2975 0.12320 0.12026 -0.0344 0.0024 1.0000 18.750 1.2827 0.13008 0.12726 -0.0375 0.0024 1.0000 19.000 1.2680 0.13717 0.13449 -0.0410 0.0024 1.0000