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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4068 0.08830 0.08619 -0.0158 1.0000 0.0138 -8.500 -0.4094 0.08383 0.08176 -0.0189 1.0000 0.0142 -8.250 -0.4126 0.07982 0.07778 -0.0218 1.0000 0.0140 -8.000 -0.4227 0.07538 0.07335 -0.0249 1.0000 0.0142 -7.750 -0.4327 0.07202 0.06999 -0.0248 1.0000 0.0142 -7.500 -0.4385 0.06758 0.06547 -0.0256 1.0000 0.0145 -7.250 -0.4385 0.06405 0.06188 -0.0251 1.0000 0.0146 -7.000 -0.4322 0.05988 0.05759 -0.0253 0.9925 0.0148 -6.750 -0.3919 0.05350 0.05088 -0.0328 0.9152 0.0149 -6.500 -0.3904 0.04821 0.04521 -0.0322 0.8475 0.0152 -6.250 -0.3834 0.04597 0.04272 -0.0304 0.8070 0.0155 -6.000 -0.3732 0.04396 0.04051 -0.0289 0.7773 0.0158 -5.750 -0.3610 0.04174 0.03807 -0.0273 0.7530 0.0162 -5.500 -0.3474 0.03944 0.03555 -0.0257 0.7322 0.0167 -5.250 -0.3322 0.03702 0.03288 -0.0239 0.7132 0.0175 -5.000 -0.3095 0.03494 0.03034 -0.0212 0.6968 0.0196 -4.750 -0.2921 0.03333 0.02833 -0.0190 0.6809 0.0198 -4.500 -0.2825 0.02866 0.02347 -0.0172 0.6674 0.0207 -4.250 -0.2631 0.02716 0.02184 -0.0162 0.6527 0.0215 -4.000 -0.2421 0.02576 0.02023 -0.0150 0.6389 0.0226 -3.750 -0.2155 0.02590 0.01998 -0.0132 0.6254 0.0260 -3.500 -0.1988 0.02220 0.01595 -0.0115 0.6139 0.0276 -3.250 -0.1754 0.02086 0.01452 -0.0107 0.6013 0.0291 -3.000 -0.1447 0.01622 0.00913 -0.0080 0.5919 0.0139 -2.750 -0.1165 0.01452 0.00703 -0.0069 0.5810 0.0113 -2.500 -0.0902 0.01365 0.00605 -0.0062 0.5698 0.0110 -2.250 -0.0654 0.01282 0.00512 -0.0054 0.5591 0.0110 -2.000 -0.0411 0.01225 0.00446 -0.0044 0.5491 0.0111 -1.750 -0.0185 0.01153 0.00368 -0.0032 0.5391 0.0118 -1.500 0.0062 0.01120 0.00329 -0.0024 0.5299 0.0131 -1.000 0.0546 0.01043 0.00256 -0.0005 0.5121 0.0513 -0.750 0.0657 0.00898 0.00233 0.0022 0.5050 0.4086 -0.500 0.0635 0.00763 0.00274 0.0094 0.4984 0.8951 -0.250 0.1099 0.00872 0.00373 0.0076 0.4892 0.9380 0.000 0.1797 0.00937 0.00418 -0.0004 0.4784 0.9492 0.250 0.2545 0.00998 0.00463 -0.0096 0.4674 0.9624 0.500 0.3165 0.01014 0.00462 -0.0165 0.4584 0.9690 0.750 0.3449 0.01020 0.00461 -0.0166 0.4510 0.9731 1.000 0.3742 0.01022 0.00453 -0.0171 0.4446 0.9755 1.250 0.4084 0.01014 0.00441 -0.0185 0.4374 0.9768 1.500 0.4405 0.01014 0.00432 -0.0196 0.4309 0.9784 1.750 0.4718 0.01011 0.00426 -0.0204 0.4245 0.9801 2.000 0.5012 0.01013 0.00422 -0.0209 0.4184 0.9821 2.250 0.5288 0.01017 0.00422 -0.0210 0.4127 0.9841 2.500 0.5548 0.01023 0.00426 -0.0208 0.4069 0.9862 2.750 0.5864 0.01023 0.00419 -0.0218 0.4012 0.9872 3.000 0.6178 0.01018 0.00415 -0.0227 0.3955 0.9883 3.250 0.6484 0.01019 0.00412 -0.0235 0.3900 0.9896 3.500 0.6773 0.01025 0.00415 -0.0239 0.3847 0.9909 3.750 0.7066 0.01025 0.00417 -0.0244 0.3791 0.9923 4.000 0.7348 0.01032 0.00420 -0.0247 0.3739 0.9936 4.250 0.7622 0.01039 0.00428 -0.0248 0.3687 0.9948 4.500 0.7922 0.01040 0.00432 -0.0255 0.3631 0.9958 4.750 0.8213 0.01048 0.00435 -0.0260 0.3578 0.9968 5.000 0.8498 0.01051 0.00443 -0.0264 0.3524 0.9976 5.250 0.8788 0.01055 0.00449 -0.0269 0.3467 0.9987 5.500 0.9078 0.01067 0.00458 -0.0274 0.3411 0.9997 5.750 0.9339 0.01071 0.00469 -0.0273 0.3354 1.0000 6.000 0.9571 0.01084 0.00483 -0.0266 0.3299 1.0000 6.250 0.9805 0.01097 0.00499 -0.0259 0.3243 1.0000 6.500 1.0039 0.01107 0.00513 -0.0252 0.3183 1.0000 6.750 1.0265 0.01124 0.00531 -0.0245 0.3124 1.0000 7.000 1.0499 0.01133 0.00547 -0.0238 0.3059 1.0000 7.500 1.0950 0.01163 0.00583 -0.0222 0.2922 1.0000 7.750 1.1166 0.01184 0.00605 -0.0213 0.2851 1.0000 8.000 1.1391 0.01196 0.00624 -0.0205 0.2766 1.0000 8.250 1.1603 0.01218 0.00648 -0.0195 0.2690 1.0000 8.500 1.1817 0.01236 0.00671 -0.0185 0.2601 1.0000 8.750 1.2025 0.01258 0.00698 -0.0175 0.2500 1.0000 9.000 1.2223 0.01286 0.00727 -0.0163 0.2401 1.0000 9.250 1.2411 0.01317 0.00759 -0.0150 0.2283 1.0000 9.750 1.2757 0.01394 0.00835 -0.0119 0.2014 1.0000 10.000 1.2909 0.01440 0.00882 -0.0100 0.1860 1.0000 10.250 1.3043 0.01493 0.00932 -0.0078 0.1705 1.0000 10.500 1.3156 0.01551 0.00987 -0.0053 0.1557 1.0000 10.750 1.3243 0.01614 0.01047 -0.0024 0.1413 1.0000 11.000 1.3301 0.01679 0.01109 0.0010 0.1278 1.0000 11.250 1.3326 0.01746 0.01173 0.0049 0.1153 1.0000 11.500 1.3326 0.01810 0.01236 0.0093 0.1054 1.0000 11.750 1.3303 0.01879 0.01304 0.0140 0.0963 1.0000 12.000 1.3242 0.01951 0.01376 0.0192 0.0884 1.0000 12.250 1.3238 0.02032 0.01460 0.0230 0.0813 1.0000 12.500 1.3226 0.02147 0.01575 0.0261 0.0736 1.0000 12.750 1.3223 0.02285 0.01716 0.0284 0.0672 1.0000 13.000 1.3225 0.02447 0.01883 0.0300 0.0611 1.0000 13.250 1.3192 0.02665 0.02103 0.0311 0.0556 1.0000 13.500 1.3196 0.02879 0.02325 0.0316 0.0510 1.0000 13.750 1.3155 0.03152 0.02603 0.0317 0.0470 1.0000 14.000 1.3115 0.03443 0.02902 0.0316 0.0431 1.0000 14.250 1.3071 0.03749 0.03215 0.0313 0.0399 1.0000 14.500 1.2961 0.04137 0.03608 0.0307 0.0370 1.0000 14.750 1.2899 0.04478 0.03960 0.0301 0.0345 1.0000 15.000 1.2820 0.04846 0.04334 0.0293 0.0319 1.0000 15.250 1.2708 0.05258 0.04753 0.0284 0.0305 1.0000 15.500 1.2548 0.05737 0.05238 0.0272 0.0283 1.0000 15.750 1.2493 0.06103 0.05618 0.0262 0.0270 1.0000 16.000 1.2406 0.06523 0.06046 0.0249 0.0254 1.0000 16.250 1.2299 0.06979 0.06507 0.0234 0.0238 1.0000 16.500 1.2151 0.07505 0.07040 0.0216 0.0228 1.0000 16.750 1.2067 0.07955 0.07499 0.0200 0.0213 1.0000 17.000 1.1988 0.08403 0.07957 0.0183 0.0205 1.0000 17.250 1.1933 0.08822 0.08385 0.0167 0.0195 1.0000 17.500 1.1837 0.09317 0.08886 0.0147 0.0185 1.0000 17.750 1.1722 0.09846 0.09423 0.0126 0.0179 1.0000