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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5448 0.09381 0.09025 -0.0139 1.0000 0.0215 -9.500 -0.5450 0.08987 0.08634 -0.0153 1.0000 0.0210 -9.250 -0.5477 0.08499 0.08149 -0.0181 1.0000 0.0206 -9.000 -0.5532 0.07923 0.07577 -0.0224 1.0000 0.0202 -8.750 -0.5646 0.07224 0.06879 -0.0291 1.0000 0.0198 -8.500 -0.5771 0.06613 0.06260 -0.0321 1.0000 0.0193 -8.250 -0.5867 0.06011 0.05644 -0.0335 1.0000 0.0189 -8.000 -0.5946 0.05431 0.05042 -0.0334 1.0000 0.0185 -7.750 -0.6001 0.04891 0.04474 -0.0320 1.0000 0.0182 -7.500 -0.6026 0.04410 0.03962 -0.0296 1.0000 0.0180 -7.250 -0.6016 0.03990 0.03506 -0.0268 1.0000 0.0179 -7.000 -0.5967 0.03639 0.03119 -0.0240 1.0000 0.0180 -6.750 -0.5867 0.03407 0.02861 -0.0216 1.0000 0.0186 -6.500 -0.5755 0.03175 0.02598 -0.0192 1.0000 0.0193 -6.250 -0.5632 0.02930 0.02317 -0.0167 1.0000 0.0197 -6.000 -0.5491 0.02694 0.02045 -0.0144 1.0000 0.0197 -5.750 -0.5328 0.02493 0.01809 -0.0124 1.0000 0.0198 -5.500 -0.5147 0.02322 0.01606 -0.0105 1.0000 0.0200 -5.250 -0.4927 0.02171 0.01428 -0.0095 0.9994 0.0203 -5.000 -0.4586 0.02022 0.01253 -0.0108 0.9961 0.0207 -4.750 -0.4244 0.01899 0.01110 -0.0121 0.9927 0.0212 -4.500 -0.3902 0.01808 0.01005 -0.0135 0.9887 0.0219 -4.250 -0.3565 0.01686 0.00878 -0.0150 0.9855 0.0233 -4.000 -0.3230 0.01603 0.00791 -0.0163 0.9800 0.0242 -3.750 -0.2829 0.01521 0.00706 -0.0189 0.9746 0.0251 -3.500 -0.2445 0.01450 0.00627 -0.0211 0.9652 0.0263 -3.250 -0.2093 0.01391 0.00561 -0.0225 0.9552 0.0280 -3.000 -0.1745 0.01343 0.00505 -0.0238 0.9477 0.0301 -2.750 -0.1463 0.01296 0.00458 -0.0238 0.9373 0.0354 -2.500 -0.1172 0.01249 0.00418 -0.0240 0.9270 0.0555 -2.250 -0.0896 0.01181 0.00382 -0.0240 0.9159 0.1313 -2.000 -0.0658 0.01079 0.00353 -0.0236 0.9031 0.3123 -1.750 -0.0472 0.00965 0.00336 -0.0219 0.8882 0.5481 -1.500 -0.0275 0.00878 0.00336 -0.0193 0.8728 0.7615 -1.250 0.0331 0.00877 0.00365 -0.0246 0.8597 0.9194 -1.000 0.0772 0.00889 0.00362 -0.0272 0.8391 0.9519 -0.750 0.1117 0.00892 0.00347 -0.0282 0.8137 0.9638 -0.500 0.1464 0.00898 0.00333 -0.0293 0.7842 0.9737 -0.250 0.1834 0.00905 0.00319 -0.0310 0.7512 0.9816 0.000 0.2204 0.00917 0.00307 -0.0328 0.7124 0.9893 0.250 0.2576 0.00932 0.00295 -0.0347 0.6653 0.9962 0.500 0.2904 0.00950 0.00285 -0.0358 0.6162 1.0000 0.750 0.3147 0.00968 0.00278 -0.0351 0.5745 1.0000 1.000 0.3389 0.00988 0.00275 -0.0345 0.5367 1.0000 1.250 0.3630 0.01008 0.00275 -0.0338 0.5021 1.0000 1.500 0.3872 0.01029 0.00278 -0.0332 0.4713 1.0000 1.750 0.4114 0.01049 0.00282 -0.0326 0.4459 1.0000 2.000 0.4357 0.01068 0.00289 -0.0320 0.4240 1.0000 2.500 0.4841 0.01109 0.00308 -0.0307 0.3890 1.0000 2.750 0.5084 0.01129 0.00321 -0.0301 0.3753 1.0000 3.000 0.5328 0.01147 0.00335 -0.0295 0.3630 1.0000 3.250 0.5571 0.01167 0.00350 -0.0289 0.3515 1.0000 3.500 0.5813 0.01187 0.00366 -0.0282 0.3406 1.0000 3.750 0.6053 0.01210 0.00385 -0.0276 0.3306 1.0000 4.000 0.6297 0.01229 0.00405 -0.0269 0.3213 1.0000 4.250 0.6538 0.01252 0.00426 -0.0263 0.3125 1.0000 4.500 0.6778 0.01275 0.00450 -0.0256 0.3033 1.0000 4.750 0.7020 0.01297 0.00473 -0.0249 0.2944 1.0000 5.000 0.7257 0.01324 0.00498 -0.0242 0.2868 1.0000 5.250 0.7500 0.01346 0.00526 -0.0235 0.2784 1.0000 5.500 0.7737 0.01373 0.00554 -0.0228 0.2706 1.0000 5.750 0.7976 0.01398 0.00586 -0.0221 0.2624 1.0000 6.000 0.8212 0.01426 0.00617 -0.0214 0.2554 1.0000 6.250 0.8447 0.01453 0.00648 -0.0206 0.2456 1.0000 6.500 0.8681 0.01479 0.00678 -0.0199 0.2343 1.0000 6.750 0.8912 0.01507 0.00711 -0.0191 0.2223 1.0000 7.000 0.9140 0.01538 0.00743 -0.0183 0.2090 1.0000 7.250 0.9365 0.01571 0.00778 -0.0175 0.1938 1.0000 7.500 0.9590 0.01608 0.00817 -0.0167 0.1804 1.0000 7.750 0.9813 0.01647 0.00862 -0.0158 0.1659 1.0000 8.000 1.0029 0.01693 0.00907 -0.0149 0.1469 1.0000 8.250 1.0233 0.01754 0.00961 -0.0140 0.1187 1.0000 8.500 1.0399 0.01858 0.01041 -0.0126 0.0790 1.0000 8.750 1.0557 0.01973 0.01143 -0.0111 0.0547 1.0000 9.000 1.0726 0.02072 0.01243 -0.0096 0.0414 1.0000 9.250 1.0894 0.02169 0.01345 -0.0082 0.0338 1.0000 9.500 1.1050 0.02273 0.01453 -0.0066 0.0283 1.0000 9.750 1.1208 0.02368 0.01560 -0.0051 0.0247 1.0000 10.000 1.1351 0.02472 0.01676 -0.0034 0.0221 1.0000 10.250 1.1443 0.02612 0.01826 -0.0012 0.0201 1.0000 10.500 1.1549 0.02732 0.01961 0.0009 0.0188 1.0000 10.750 1.1644 0.02851 0.02098 0.0030 0.0174 1.0000 11.000 1.1707 0.02972 0.02230 0.0055 0.0162 1.0000 11.250 1.1743 0.03111 0.02379 0.0080 0.0153 1.0000 11.500 1.1725 0.03300 0.02577 0.0106 0.0145 1.0000 11.750 1.1722 0.03496 0.02787 0.0126 0.0140 1.0000 12.000 1.1728 0.03703 0.03010 0.0141 0.0136 1.0000 12.250 1.1722 0.03941 0.03265 0.0150 0.0132 1.0000 12.500 1.1706 0.04211 0.03550 0.0155 0.0128 1.0000 12.750 1.1681 0.04514 0.03868 0.0155 0.0125 1.0000 13.000 1.1650 0.04847 0.04217 0.0150 0.0122 1.0000 13.250 1.1610 0.05212 0.04596 0.0140 0.0120 1.0000 13.500 1.1563 0.05607 0.05006 0.0127 0.0117 1.0000 13.750 1.1509 0.06027 0.05440 0.0111 0.0115 1.0000 14.000 1.1447 0.06470 0.05897 0.0093 0.0114 1.0000 14.250 1.1377 0.06935 0.06377 0.0073 0.0112 1.0000 14.500 1.1299 0.07416 0.06871 0.0052 0.0110 1.0000 14.750 1.1216 0.07913 0.07379 0.0030 0.0109 1.0000 15.000 1.1128 0.08422 0.07899 0.0007 0.0108 1.0000 15.250 1.1033 0.08951 0.08440 -0.0016 0.0106 1.0000 15.500 1.0932 0.09500 0.08999 -0.0041 0.0105 1.0000 15.750 1.0824 0.10072 0.09581 -0.0067 0.0104 1.0000 16.000 1.0711 0.10697 0.10222 -0.0099 0.0103 1.0000 16.250 1.0595 0.11342 0.10883 -0.0132 0.0102 1.0000 16.500 1.0471 0.12020 0.11576 -0.0167 0.0102 1.0000 16.750 1.0340 0.12739 0.12310 -0.0206 0.0102 1.0000 17.000 1.0203 0.13501 0.13086 -0.0248 0.0101 1.0000 17.250 1.0058 0.14308 0.13906 -0.0293 0.0102 1.0000 17.500 0.9902 0.15180 0.14791 -0.0341 0.0102 1.0000 17.750 0.9733 0.16135 0.15755 -0.0395 0.0103 1.0000 18.000 0.9544 0.17218 0.16848 -0.0455 0.0104 1.0000