XFOIL Version 6.96 Calculated polar for: BELL/WORTMANN FX 69-H-098 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4343 0.08176 0.07965 -0.0201 1.0000 0.0228 -9.250 -0.5655 0.07666 0.07449 -0.0274 1.0000 0.0212 -9.000 -0.5813 0.06909 0.06686 -0.0339 1.0000 0.0213 -8.750 -0.5886 0.06533 0.06305 -0.0343 1.0000 0.0214 -8.500 -0.5897 0.06206 0.05971 -0.0346 1.0000 0.0217 -8.250 -0.5889 0.05893 0.05652 -0.0346 1.0000 0.0220 -8.000 -0.5864 0.05600 0.05352 -0.0340 1.0000 0.0224 -7.750 -0.5845 0.05302 0.05045 -0.0329 1.0000 0.0229 -7.500 -0.5833 0.05003 0.04734 -0.0310 1.0000 0.0235 -7.250 -0.5820 0.04694 0.04410 -0.0287 1.0000 0.0244 -7.000 -0.5745 0.04465 0.04142 -0.0252 1.0000 0.0271 -6.750 -0.5706 0.04283 0.03930 -0.0217 1.0000 0.0274 -6.500 -0.5836 0.03555 0.03168 -0.0179 1.0000 0.0285 -6.250 -0.5710 0.03396 0.03013 -0.0162 1.0000 0.0293 -6.000 -0.5587 0.03256 0.02866 -0.0142 1.0000 0.0302 -5.750 -0.5405 0.03080 0.02674 -0.0131 0.9993 0.0318 -5.500 -0.5009 0.03172 0.02727 -0.0143 0.9967 0.0359 -5.250 -0.4767 0.02291 0.01770 -0.0139 0.9944 0.0269 -5.000 -0.4476 0.01728 0.01131 -0.0134 0.9919 0.0216 -4.750 -0.4093 0.01583 0.00975 -0.0157 0.9882 0.0223 -4.500 -0.3682 0.01455 0.00836 -0.0184 0.9852 0.0226 -4.250 -0.3285 0.01341 0.00714 -0.0208 0.9826 0.0228 -4.000 -0.2954 0.01259 0.00627 -0.0218 0.9776 0.0234 -3.750 -0.2593 0.01188 0.00554 -0.0235 0.9745 0.0242 -3.500 -0.2226 0.01127 0.00488 -0.0254 0.9719 0.0253 -3.250 -0.1899 0.01078 0.00435 -0.0263 0.9668 0.0264 -3.000 -0.1589 0.01032 0.00386 -0.0268 0.9603 0.0281 -2.750 -0.1281 0.00983 0.00335 -0.0273 0.9544 0.0319 -2.500 -0.1012 0.00948 0.00298 -0.0267 0.9449 0.0382 -2.250 -0.0778 0.00865 0.00260 -0.0258 0.9344 0.1430 -2.000 -0.0570 0.00764 0.00233 -0.0246 0.9229 0.3495 -1.750 -0.0361 0.00691 0.00215 -0.0232 0.9099 0.5068 -1.500 -0.0178 0.00617 0.00203 -0.0210 0.8941 0.6755 -1.250 0.0011 0.00562 0.00198 -0.0184 0.8764 0.8191 -1.000 0.0374 0.00556 0.00212 -0.0192 0.8580 0.9218 -0.750 0.0750 0.00578 0.00224 -0.0205 0.8338 0.9583 -0.500 0.1263 0.00612 0.00240 -0.0249 0.8039 0.9769 -0.250 0.1652 0.00631 0.00239 -0.0271 0.7713 0.9850 0.000 0.2040 0.00645 0.00233 -0.0294 0.7372 0.9895 0.250 0.2408 0.00661 0.00230 -0.0313 0.6991 0.9945 0.500 0.2800 0.00677 0.00223 -0.0338 0.6499 0.9977 0.750 0.3142 0.00698 0.00218 -0.0353 0.5995 1.0000 1.000 0.3398 0.00716 0.00214 -0.0350 0.5562 1.0000 1.250 0.3653 0.00736 0.00213 -0.0347 0.5150 1.0000 1.500 0.3908 0.00755 0.00214 -0.0344 0.4761 1.0000 1.750 0.4164 0.00774 0.00216 -0.0341 0.4436 1.0000 2.000 0.4419 0.00791 0.00220 -0.0337 0.4188 1.0000 2.250 0.4674 0.00807 0.00226 -0.0334 0.3992 1.0000 2.500 0.4927 0.00823 0.00232 -0.0330 0.3830 1.0000 2.750 0.5178 0.00838 0.00241 -0.0325 0.3687 1.0000 3.000 0.5430 0.00852 0.00250 -0.0320 0.3562 1.0000 3.250 0.5681 0.00866 0.00260 -0.0315 0.3454 1.0000 3.500 0.5930 0.00883 0.00272 -0.0310 0.3354 1.0000 3.750 0.6179 0.00898 0.00284 -0.0305 0.3252 1.0000 4.000 0.6428 0.00912 0.00297 -0.0300 0.3154 1.0000 4.250 0.6674 0.00930 0.00312 -0.0294 0.3062 1.0000 4.500 0.6922 0.00946 0.00327 -0.0288 0.2971 1.0000 4.750 0.7169 0.00963 0.00344 -0.0282 0.2884 1.0000 5.000 0.7411 0.00984 0.00362 -0.0276 0.2792 1.0000 5.250 0.7659 0.00998 0.00378 -0.0270 0.2698 1.0000 5.500 0.7902 0.01018 0.00398 -0.0264 0.2602 1.0000 5.750 0.8142 0.01039 0.00416 -0.0257 0.2494 1.0000 6.000 0.8385 0.01056 0.00432 -0.0251 0.2377 1.0000 6.250 0.8627 0.01075 0.00451 -0.0244 0.2258 1.0000 6.500 0.8867 0.01097 0.00474 -0.0238 0.2161 1.0000 6.750 0.9103 0.01122 0.00498 -0.0230 0.2060 1.0000 7.000 0.9339 0.01147 0.00523 -0.0223 0.1948 1.0000 7.250 0.9575 0.01173 0.00548 -0.0216 0.1823 1.0000 7.500 0.9806 0.01202 0.00577 -0.0209 0.1683 1.0000 7.750 1.0033 0.01237 0.00609 -0.0201 0.1502 1.0000 8.000 1.0243 0.01291 0.00648 -0.0191 0.1175 1.0000 8.250 1.0398 0.01405 0.00728 -0.0174 0.0664 1.0000 8.500 1.0564 0.01508 0.00816 -0.0157 0.0407 1.0000 8.750 1.0747 0.01590 0.00897 -0.0142 0.0303 1.0000 9.000 1.0919 0.01683 0.00992 -0.0126 0.0245 1.0000 9.250 1.1117 0.01745 0.01062 -0.0114 0.0216 1.0000 9.500 1.1252 0.01869 0.01193 -0.0093 0.0187 1.0000 9.750 1.1438 0.01938 0.01273 -0.0079 0.0176 1.0000 10.000 1.1607 0.02020 0.01364 -0.0064 0.0163 1.0000 10.250 1.1761 0.02112 0.01464 -0.0047 0.0153 1.0000 10.500 1.1856 0.02247 0.01607 -0.0024 0.0143 1.0000 10.750 1.1919 0.02400 0.01773 0.0004 0.0137 1.0000 11.000 1.2059 0.02485 0.01868 0.0021 0.0131 1.0000 11.250 1.2152 0.02585 0.01979 0.0045 0.0125 1.0000 11.500 1.2211 0.02703 0.02106 0.0072 0.0121 1.0000 11.750 1.2261 0.02835 0.02247 0.0096 0.0117 1.0000 12.000 1.2302 0.02983 0.02407 0.0117 0.0113 1.0000 12.250 1.2328 0.03154 0.02587 0.0136 0.0111 1.0000 12.500 1.2333 0.03359 0.02802 0.0152 0.0108 1.0000 12.750 1.2306 0.03614 0.03068 0.0164 0.0106 1.0000 13.000 1.2249 0.03926 0.03392 0.0174 0.0104 1.0000 13.250 1.2165 0.04295 0.03777 0.0181 0.0102 1.0000 13.500 1.2136 0.04618 0.04115 0.0180 0.0101 1.0000 13.750 1.2119 0.04941 0.04454 0.0173 0.0100 1.0000 14.000 1.2084 0.05308 0.04837 0.0163 0.0099 1.0000 14.250 1.2030 0.05713 0.05258 0.0149 0.0098 1.0000 14.500 1.1962 0.06157 0.05718 0.0132 0.0098 1.0000 14.750 1.1876 0.06639 0.06216 0.0111 0.0097 1.0000 15.000 1.1773 0.07158 0.06751 0.0088 0.0097 1.0000 15.250 1.1658 0.07715 0.07324 0.0061 0.0096 1.0000 15.500 1.1527 0.08310 0.07934 0.0032 0.0096 1.0000 15.750 1.1387 0.08942 0.08581 0.0000 0.0096 1.0000 16.000 1.1236 0.09612 0.09266 -0.0035 0.0096 1.0000 16.250 1.1077 0.10315 0.09984 -0.0072 0.0096 1.0000 16.500 1.0909 0.11062 0.10745 -0.0112 0.0097 1.0000 16.750 1.0735 0.11844 0.11540 -0.0155 0.0097 1.0000 17.000 1.0551 0.12673 0.12383 -0.0200 0.0098 1.0000 17.250 1.0362 0.13553 0.13276 -0.0250 0.0099 1.0000 17.500 1.0157 0.14509 0.14244 -0.0304 0.0099 1.0000