XFOIL Version 6.94 Calculated polar for: S4158 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4225 0.00807 0.00398 -0.0866 0.7769 0.9977 0.500 0.4789 0.00799 0.00378 -0.0868 0.7705 1.0000 1.000 0.5297 0.00792 0.00366 -0.0858 0.7617 1.0000 1.500 0.5811 0.00783 0.00348 -0.0847 0.7542 1.0000 2.000 0.6331 0.00772 0.00334 -0.0839 0.7438 1.0000 2.500 0.6854 0.00757 0.00318 -0.0829 0.7309 1.0000 3.000 0.7378 0.00739 0.00297 -0.0820 0.7141 1.0000 3.500 0.7903 0.00731 0.00289 -0.0812 0.6952 1.0000 4.000 0.8422 0.00735 0.00291 -0.0803 0.6707 1.0000 4.500 0.8929 0.00752 0.00301 -0.0792 0.6395 1.0000 5.000 0.9412 0.00790 0.00325 -0.0778 0.5974 1.0000 5.500 0.9852 0.00855 0.00368 -0.0758 0.5349 1.0000 6.000 1.0250 0.00944 0.00429 -0.0732 0.4672 1.0000 6.500 1.0613 0.01045 0.00503 -0.0701 0.4012 1.0000 7.000 1.0925 0.01163 0.00593 -0.0664 0.3322 1.0000 7.500 1.1160 0.01305 0.00699 -0.0615 0.2560 1.0000 8.000 1.1312 0.01453 0.00819 -0.0553 0.1995 1.0000 8.500 1.1511 0.01613 0.00956 -0.0505 0.1475 1.0000 9.000 1.1701 0.01802 0.01118 -0.0460 0.0960 1.0000 9.500 1.1887 0.02010 0.01308 -0.0417 0.0644 1.0000 10.000 1.2099 0.02212 0.01509 -0.0380 0.0496 1.0000 10.500 1.2339 0.02402 0.01708 -0.0349 0.0412 1.0000 11.000 1.2540 0.02627 0.01948 -0.0315 0.0352 1.0000 11.500 1.2694 0.02896 0.02224 -0.0281 0.0295 1.0000 12.000 1.2873 0.03158 0.02504 -0.0252 0.0258 1.0000 12.500 1.3029 0.03448 0.02808 -0.0225 0.0225 1.0000 13.000 1.3016 0.03908 0.03287 -0.0190 0.0199 1.0000 13.500 1.3174 0.04236 0.03636 -0.0172 0.0179 1.0000 14.000 1.3285 0.04626 0.04042 -0.0157 0.0162 1.0000 14.500 1.3235 0.05219 0.04654 -0.0140 0.0146 1.0000 15.000 1.3219 0.05819 0.05283 -0.0130 0.0139 1.0000 15.500 1.3246 0.06401 0.05893 -0.0131 0.0130 1.0000 16.000 1.3213 0.07097 0.06620 -0.0139 0.0122 1.0000 16.500 1.3162 0.07862 0.07408 -0.0158 0.0115 1.0000 17.000 1.3076 0.08720 0.08287 -0.0187 0.0109 1.0000 17.500 1.2919 0.09741 0.09334 -0.0226 0.0105 1.0000 18.000 1.2650 0.11017 0.10642 -0.0281 0.0101 1.0000 18.500 1.2325 0.12498 0.12159 -0.0356 0.0100 1.0000 19.000 1.2026 0.14038 0.13732 -0.0445 0.0100 1.0000 19.500 1.1713 0.15726 0.15450 -0.0548 0.0100 1.0000 20.000 1.1405 0.17569 0.17321 -0.0664 0.0101 1.0000 21.500 0.7853 0.24825 0.24640 -0.1016 0.0176 1.0000 22.000 0.7934 0.25630 0.25447 -0.1051 0.0159 1.0000 22.500 0.8036 0.26314 0.26134 -0.1080 0.0150 1.0000 23.000 0.8141 0.27225 0.27048 -0.1104 0.0142 1.0000 23.500 0.8197 0.28167 0.27992 -0.1144 0.0141 1.0000 24.000 0.8218 0.29245 0.29070 -0.1197 0.0125 1.0000 24.500 0.8294 0.30097 0.29924 -0.1232 0.0111 1.0000 25.000 0.8382 0.30818 0.30648 -0.1261 0.0102 1.0000 26.000 0.8527 0.32728 0.32562 -0.1324 0.0097 1.0000 26.500 0.8562 0.33818 0.33652 -0.1370 0.0092 1.0000 27.000 0.8626 0.34789 0.34626 -0.1405 0.0082 1.0000 27.500 0.8687 0.35639 0.35480 -0.1437 0.0072 1.0000 28.000 0.8749 0.36475 0.36318 -0.1470 0.0069 1.0000 28.500 0.8828 0.37372 0.37218 -0.1492 0.0066 1.0000 29.000 0.8863 0.38419 0.38266 -0.1532 0.0065 1.0000 29.500 0.8904 0.39605 0.39453 -0.1571 0.0057 1.0000 30.000 0.8953 0.40570 0.40420 -0.1603 0.0050 1.0000 30.500 0.8997 0.41504 0.41357 -0.1635 0.0047 1.0000 31.000 0.9039 0.42409 0.42265 -0.1667 0.0045 1.0000 31.500 0.9075 0.43236 0.43096 -0.1696 0.0043 1.0000 33.000 0.9177 0.46500 0.46365 -0.1793 0.0037 1.0000 33.500 0.9205 0.47499 0.47366 -0.1823 0.0030 1.0000 34.000 0.9227 0.48439 0.48309 -0.1854 0.0029 1.0000