XFOIL Version 6.96 Calculated polar for: EH 2.5/10 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 -0.4934 0.10221 0.10005 0.0022 1.0000 0.0183 -9.500 -0.4933 0.09780 0.09567 -0.0003 1.0000 0.0192 -7.500 -0.5437 0.05549 0.05319 -0.0211 1.0000 0.0215 -7.250 -0.5355 0.05335 0.05101 -0.0205 1.0000 0.0221 -7.000 -0.5247 0.05127 0.04888 -0.0200 1.0000 0.0228 -6.750 -0.5129 0.04887 0.04641 -0.0195 1.0000 0.0239 -6.500 -0.5003 0.04543 0.04281 -0.0189 1.0000 0.0265 -6.250 -0.4804 0.04241 0.03938 -0.0172 1.0000 0.0286 -5.750 -0.4506 0.02345 0.01884 -0.0174 0.9230 0.0210 -5.500 -0.4309 0.02028 0.01510 -0.0159 0.8741 0.0212 -5.250 -0.4105 0.01844 0.01283 -0.0141 0.8374 0.0212 -5.000 -0.3888 0.01656 0.01058 -0.0127 0.8070 0.0214 -4.750 -0.3657 0.01506 0.00877 -0.0115 0.7804 0.0218 -4.500 -0.3417 0.01402 0.00752 -0.0106 0.7567 0.0224 -4.250 -0.3173 0.01327 0.00660 -0.0097 0.7355 0.0230 -4.000 -0.2922 0.01279 0.00601 -0.0091 0.7161 0.0242 -3.750 -0.2671 0.01233 0.00543 -0.0084 0.6984 0.0255 -3.500 -0.2423 0.01182 0.00477 -0.0076 0.6825 0.0266 -3.250 -0.2171 0.01141 0.00424 -0.0068 0.6675 0.0279 -3.000 -0.1922 0.01099 0.00370 -0.0061 0.6531 0.0294 -2.750 -0.1673 0.01055 0.00320 -0.0054 0.6395 0.0336 -2.500 -0.1416 0.01025 0.00285 -0.0048 0.6264 0.0429 -2.250 -0.1162 0.00994 0.00262 -0.0042 0.6139 0.0725 -2.000 -0.0899 0.00979 0.00246 -0.0039 0.6018 0.0917 -1.750 -0.0638 0.00961 0.00231 -0.0035 0.5905 0.1143 -1.500 -0.0380 0.00942 0.00217 -0.0031 0.5796 0.1494 -1.250 -0.0140 0.00896 0.00203 -0.0025 0.5691 0.2469 -1.000 -0.0083 0.00704 0.00183 0.0014 0.5608 0.7296 -0.750 0.0120 0.00680 0.00194 0.0037 0.5515 0.8467 -0.500 0.0375 0.00681 0.00197 0.0047 0.5414 0.8866 -0.250 0.0640 0.00688 0.00200 0.0055 0.5319 0.9122 0.000 0.0934 0.00700 0.00206 0.0056 0.5227 0.9314 0.250 0.1243 0.00711 0.00210 0.0053 0.5131 0.9441 0.500 0.1572 0.00726 0.00217 0.0046 0.5039 0.9558 0.750 0.2010 0.00749 0.00230 0.0015 0.4941 0.9639 1.000 0.2441 0.00767 0.00239 -0.0015 0.4842 0.9702 1.250 0.2954 0.00786 0.00250 -0.0063 0.4739 0.9752 1.500 0.3324 0.00800 0.00256 -0.0082 0.4652 0.9809 1.750 0.3666 0.00803 0.00254 -0.0097 0.4562 0.9833 2.000 0.4023 0.00808 0.00253 -0.0115 0.4476 0.9852 2.250 0.4368 0.00814 0.00253 -0.0130 0.4394 0.9876 2.500 0.4706 0.00818 0.00255 -0.0144 0.4310 0.9903 2.750 0.5033 0.00827 0.00258 -0.0156 0.4231 0.9932 3.000 0.5384 0.00829 0.00259 -0.0173 0.4143 0.9954 3.250 0.5737 0.00835 0.00262 -0.0191 0.4063 0.9978 3.500 0.6085 0.00840 0.00265 -0.0208 0.3980 1.0000 3.750 0.6315 0.00845 0.00270 -0.0199 0.3906 1.0000 4.000 0.6543 0.00853 0.00276 -0.0191 0.3835 1.0000 4.250 0.6773 0.00860 0.00285 -0.0183 0.3766 1.0000 4.500 0.7000 0.00870 0.00294 -0.0174 0.3693 1.0000 4.750 0.7228 0.00879 0.00305 -0.0165 0.3620 1.0000 5.000 0.7454 0.00892 0.00316 -0.0156 0.3546 1.0000 5.250 0.7684 0.00904 0.00332 -0.0147 0.3478 1.0000 5.500 0.7910 0.00919 0.00346 -0.0138 0.3406 1.0000 5.750 0.8141 0.00931 0.00362 -0.0130 0.3328 1.0000 6.000 0.8366 0.00950 0.00380 -0.0121 0.3253 1.0000 6.250 0.8600 0.00963 0.00400 -0.0113 0.3179 1.0000 6.500 0.8828 0.00982 0.00419 -0.0104 0.3085 1.0000 6.750 0.9058 0.00999 0.00435 -0.0096 0.2940 1.0000 7.000 0.9288 0.01019 0.00455 -0.0088 0.2796 1.0000 7.250 0.9517 0.01041 0.00477 -0.0081 0.2646 1.0000 7.500 0.9745 0.01068 0.00504 -0.0073 0.2490 1.0000 7.750 0.9965 0.01102 0.00533 -0.0064 0.2290 1.0000 8.000 1.0178 0.01147 0.00569 -0.0055 0.2025 1.0000 8.250 1.0369 0.01215 0.00619 -0.0044 0.1640 1.0000 8.500 1.0484 0.01360 0.00718 -0.0025 0.0922 1.0000 8.750 1.0540 0.01560 0.00874 0.0002 0.0255 1.0000 9.000 1.0697 0.01659 0.00976 0.0019 0.0180 1.0000 9.250 1.0848 0.01758 0.01083 0.0035 0.0146 1.0000 9.500 1.0982 0.01867 0.01205 0.0054 0.0128 1.0000 9.750 1.1123 0.01961 0.01309 0.0070 0.0118 1.0000 10.000 1.1248 0.02060 0.01415 0.0088 0.0107 1.0000 10.250 1.1303 0.02197 0.01562 0.0112 0.0099 1.0000 10.500 1.1251 0.02367 0.01744 0.0150 0.0092 1.0000 10.750 1.1254 0.02495 0.01882 0.0178 0.0091 1.0000 11.000 1.1256 0.02656 0.02055 0.0197 0.0088 1.0000 11.250 1.1261 0.02853 0.02263 0.0206 0.0087 1.0000 11.500 1.1254 0.03093 0.02514 0.0210 0.0085 1.0000 11.750 1.1260 0.03341 0.02772 0.0210 0.0082 1.0000 12.000 1.1263 0.03604 0.03045 0.0209 0.0081 1.0000 12.250 1.1266 0.03877 0.03326 0.0206 0.0077 1.0000 12.500 1.1260 0.04160 0.03618 0.0203 0.0076 1.0000 12.750 1.1253 0.04450 0.03917 0.0199 0.0073 1.0000 13.000 1.1246 0.04734 0.04211 0.0198 0.0074 1.0000 13.250 1.1238 0.05028 0.04513 0.0194 0.0072 1.0000 13.500 1.1230 0.05324 0.04817 0.0190 0.0071 1.0000 13.750 1.1212 0.05634 0.05135 0.0185 0.0069 1.0000 14.000 1.1198 0.05942 0.05452 0.0181 0.0069 1.0000 14.250 1.1181 0.06259 0.05779 0.0176 0.0068 1.0000 14.500 1.1158 0.06595 0.06126 0.0171 0.0068 1.0000 14.750 1.1131 0.06950 0.06492 0.0164 0.0067 1.0000 15.000 1.1058 0.07363 0.06918 0.0160 0.0065 1.0000 15.250 1.1014 0.07777 0.07346 0.0145 0.0065 1.0000 15.500 1.0925 0.08269 0.07853 0.0130 0.0065 1.0000 15.750 1.0884 0.08713 0.08310 0.0106 0.0066 1.0000 16.000 1.0767 0.09288 0.08901 0.0083 0.0065 1.0000 16.250 1.0701 0.09809 0.09436 0.0054 0.0066 1.0000 16.500 1.0574 0.10463 0.10110 0.0020 0.0068 1.0000 16.750 1.0443 0.11146 0.10810 -0.0017 0.0069 1.0000 17.000 1.0069 0.12412 0.12113 -0.0085 0.0074 1.0000 17.250 0.9847 0.13389 0.13106 -0.0141 0.0076 1.0000