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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.5702 0.08450 0.08294 -0.0139 1.0000 0.0125 -9.250 -0.5743 0.07890 0.07736 -0.0182 1.0000 0.0126 -9.000 -0.5907 0.06951 0.06798 -0.0291 1.0000 0.0126 -8.750 -0.6048 0.06232 0.06069 -0.0332 1.0000 0.0126 -8.500 -0.6090 0.05720 0.05546 -0.0346 1.0000 0.0128 -8.250 -0.6105 0.05295 0.05109 -0.0345 1.0000 0.0130 -8.000 -0.6126 0.04914 0.04715 -0.0329 1.0000 0.0134 -7.750 -0.6161 0.04548 0.04334 -0.0300 1.0000 0.0139 -7.500 -0.5839 0.02961 0.02733 -0.0263 1.0000 0.0156 -7.250 -0.5744 0.02461 0.02198 -0.0264 0.9979 0.0156 -7.000 -0.5758 0.01514 0.01189 -0.0262 0.9950 0.0164 -6.750 -0.5494 0.01349 0.01017 -0.0272 0.9934 0.0168 -6.500 -0.5621 0.02247 0.01849 -0.0226 0.9942 0.0148 -6.250 -0.5382 0.01890 0.01447 -0.0222 0.9915 0.0144 -6.000 -0.5076 0.01666 0.01193 -0.0229 0.9890 0.0144 -5.750 -0.4723 0.01516 0.01024 -0.0246 0.9868 0.0145 -5.500 -0.4351 0.01393 0.00886 -0.0266 0.9850 0.0147 -5.250 -0.3994 0.01290 0.00772 -0.0283 0.9828 0.0149 -5.000 -0.3712 0.01207 0.00682 -0.0283 0.9768 0.0150 -4.750 -0.3412 0.01150 0.00618 -0.0287 0.9723 0.0153 -4.500 -0.3132 0.01115 0.00579 -0.0286 0.9674 0.0156 -4.250 -0.2898 0.01030 0.00488 -0.0276 0.9602 0.0159 -4.000 -0.2664 0.00950 0.00400 -0.0265 0.9533 0.0165 -3.750 -0.2421 0.00907 0.00353 -0.0256 0.9450 0.0172 -3.500 -0.2167 0.00876 0.00318 -0.0249 0.9370 0.0179 -3.250 -0.1913 0.00849 0.00287 -0.0242 0.9274 0.0186 -3.000 -0.1656 0.00824 0.00259 -0.0235 0.9154 0.0193 -2.750 -0.1395 0.00803 0.00232 -0.0229 0.9020 0.0202 -2.500 -0.1134 0.00782 0.00205 -0.0224 0.8859 0.0218 -2.250 -0.0875 0.00763 0.00180 -0.0217 0.8661 0.0263 -2.000 -0.0625 0.00729 0.00158 -0.0210 0.8427 0.0741 -1.750 -0.0385 0.00685 0.00139 -0.0203 0.8185 0.1736 -1.500 -0.0156 0.00631 0.00125 -0.0195 0.7917 0.3202 -1.250 0.0080 0.00594 0.00115 -0.0187 0.7633 0.4384 -1.000 0.0308 0.00554 0.00108 -0.0178 0.7351 0.5657 -0.750 0.0522 0.00512 0.00104 -0.0164 0.7070 0.7068 -0.500 0.0728 0.00480 0.00103 -0.0146 0.6760 0.8260 -0.250 0.0976 0.00473 0.00113 -0.0135 0.6388 0.9166 0.000 0.1340 0.00505 0.00131 -0.0150 0.5949 0.9623 0.250 0.1714 0.00538 0.00145 -0.0169 0.5533 0.9751 0.500 0.2066 0.00562 0.00151 -0.0186 0.5153 0.9793 0.750 0.2379 0.00584 0.00156 -0.0194 0.4783 0.9838 1.000 0.2748 0.00607 0.00160 -0.0215 0.4407 0.9855 1.250 0.3110 0.00626 0.00165 -0.0234 0.4113 0.9877 1.500 0.3466 0.00642 0.00170 -0.0252 0.3896 0.9903 1.750 0.3817 0.00658 0.00177 -0.0269 0.3721 0.9934 2.000 0.4188 0.00672 0.00182 -0.0290 0.3565 0.9953 2.250 0.4556 0.00683 0.00186 -0.0311 0.3429 0.9970 2.500 0.4915 0.00694 0.00191 -0.0330 0.3318 0.9988 2.750 0.5252 0.00705 0.00197 -0.0344 0.3216 1.0000 3.000 0.5512 0.00712 0.00202 -0.0341 0.3128 1.0000 3.250 0.5771 0.00721 0.00207 -0.0337 0.3041 1.0000 3.500 0.6028 0.00732 0.00214 -0.0334 0.2952 1.0000 3.750 0.6284 0.00740 0.00222 -0.0329 0.2877 1.0000 4.000 0.6537 0.00753 0.00231 -0.0325 0.2792 1.0000 4.250 0.6792 0.00762 0.00239 -0.0321 0.2713 1.0000 4.500 0.7044 0.00775 0.00250 -0.0316 0.2622 1.0000 4.750 0.7295 0.00789 0.00261 -0.0311 0.2522 1.0000 5.000 0.7546 0.00802 0.00272 -0.0306 0.2425 1.0000 5.250 0.7794 0.00818 0.00285 -0.0301 0.2305 1.0000 5.500 0.8039 0.00837 0.00299 -0.0295 0.2183 1.0000 5.750 0.8283 0.00857 0.00315 -0.0289 0.2070 1.0000 6.000 0.8528 0.00874 0.00331 -0.0283 0.1976 1.0000 6.250 0.8772 0.00893 0.00348 -0.0277 0.1886 1.0000 6.500 0.9012 0.00916 0.00368 -0.0270 0.1776 1.0000 6.750 0.9249 0.00940 0.00389 -0.0263 0.1657 1.0000 7.000 0.9485 0.00966 0.00411 -0.0256 0.1524 1.0000 7.250 0.9717 0.00996 0.00435 -0.0248 0.1354 1.0000 7.500 0.9930 0.01046 0.00471 -0.0238 0.1065 1.0000 7.750 1.0113 0.01129 0.00529 -0.0224 0.0671 1.0000 8.000 1.0308 0.01196 0.00584 -0.0211 0.0444 1.0000 8.250 1.0510 0.01257 0.00636 -0.0199 0.0297 1.0000 8.500 1.0719 0.01308 0.00685 -0.0187 0.0229 1.0000 8.750 1.0923 0.01364 0.00741 -0.0175 0.0184 1.0000 9.000 1.1137 0.01407 0.00788 -0.0165 0.0161 1.0000 9.250 1.1328 0.01474 0.00858 -0.0151 0.0137 1.0000 9.500 1.1542 0.01515 0.00905 -0.0141 0.0126 1.0000 9.750 1.1746 0.01566 0.00959 -0.0130 0.0114 1.0000 10.000 1.1914 0.01654 0.01055 -0.0113 0.0101 1.0000 10.250 1.2122 0.01701 0.01107 -0.0103 0.0097 1.0000 10.500 1.2319 0.01757 0.01170 -0.0092 0.0092 1.0000 10.750 1.2509 0.01819 0.01237 -0.0080 0.0086 1.0000 11.000 1.2690 0.01887 0.01311 -0.0067 0.0082 1.0000 11.250 1.2838 0.01981 0.01413 -0.0050 0.0077 1.0000 11.500 1.2895 0.02140 0.01589 -0.0021 0.0073 1.0000 11.750 1.3051 0.02213 0.01670 -0.0006 0.0072 1.0000 12.000 1.3181 0.02299 0.01764 0.0012 0.0070 1.0000 12.250 1.3265 0.02393 0.01867 0.0037 0.0069 1.0000 12.500 1.3328 0.02500 0.01984 0.0063 0.0067 1.0000 12.750 1.3385 0.02620 0.02114 0.0087 0.0065 1.0000 13.000 1.3428 0.02760 0.02264 0.0108 0.0064 1.0000 13.250 1.3464 0.02916 0.02430 0.0125 0.0062 1.0000 13.500 1.3491 0.03095 0.02619 0.0139 0.0061 1.0000 13.750 1.3518 0.03293 0.02828 0.0147 0.0059 1.0000 14.000 1.3527 0.03529 0.03074 0.0151 0.0058 1.0000 14.250 1.3515 0.03815 0.03371 0.0149 0.0057 1.0000 14.500 1.3481 0.04157 0.03724 0.0140 0.0056 1.0000 14.750 1.3412 0.04580 0.04159 0.0124 0.0055 1.0000 15.000 1.3314 0.05076 0.04669 0.0102 0.0054 1.0000 15.250 1.3184 0.05643 0.05250 0.0075 0.0054 1.0000 15.500 1.3035 0.06247 0.05867 0.0047 0.0053 1.0000 15.750 1.2877 0.06866 0.06499 0.0019 0.0053 1.0000 16.000 1.2704 0.07501 0.07146 -0.0009 0.0053 1.0000 16.250 1.2537 0.08131 0.07787 -0.0036 0.0053 1.0000