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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.6057 0.06921 0.06703 -0.0291 1.0000 0.0096 -9.000 -0.6316 0.05978 0.05746 -0.0341 1.0000 0.0095 -8.750 -0.6482 0.05203 0.04948 -0.0351 1.0000 0.0095 -8.500 -0.6569 0.04597 0.04317 -0.0340 1.0000 0.0098 -8.250 -0.6656 0.04009 0.03696 -0.0312 1.0000 0.0102 -8.000 -0.6778 0.03359 0.02996 -0.0266 1.0000 0.0106 -7.750 -0.6805 0.02912 0.02500 -0.0224 1.0000 0.0109 -7.500 -0.6708 0.02611 0.02157 -0.0199 0.9994 0.0111 -7.250 -0.6463 0.02363 0.01869 -0.0201 0.9971 0.0113 -7.000 -0.6189 0.02183 0.01659 -0.0206 0.9951 0.0115 -6.750 -0.5909 0.02046 0.01494 -0.0210 0.9929 0.0117 -6.500 -0.5643 0.01847 0.01267 -0.0213 0.9902 0.0121 -6.250 -0.5338 0.01728 0.01137 -0.0223 0.9878 0.0125 -6.000 -0.5006 0.01627 0.01025 -0.0237 0.9857 0.0128 -5.750 -0.4694 0.01537 0.00925 -0.0246 0.9822 0.0131 -5.500 -0.4384 0.01457 0.00835 -0.0254 0.9788 0.0134 -5.250 -0.4055 0.01383 0.00753 -0.0266 0.9752 0.0138 -5.000 -0.3759 0.01318 0.00681 -0.0269 0.9679 0.0141 -4.750 -0.3450 0.01258 0.00614 -0.0275 0.9600 0.0145 -4.500 -0.3178 0.01206 0.00555 -0.0273 0.9492 0.0149 -4.250 -0.2919 0.01160 0.00504 -0.0267 0.9375 0.0152 -4.000 -0.2660 0.01120 0.00458 -0.0262 0.9269 0.0155 -3.750 -0.2397 0.01088 0.00421 -0.0258 0.9162 0.0159 -3.500 -0.2141 0.01049 0.00376 -0.0251 0.9032 0.0165 -3.250 -0.1885 0.01013 0.00333 -0.0245 0.8881 0.0172 -3.000 -0.1625 0.00986 0.00299 -0.0239 0.8699 0.0180 -2.750 -0.1366 0.00965 0.00270 -0.0233 0.8486 0.0190 -2.500 -0.1106 0.00950 0.00243 -0.0227 0.8257 0.0205 -2.000 -0.0587 0.00918 0.00202 -0.0216 0.7798 0.0434 -1.750 -0.0332 0.00901 0.00186 -0.0211 0.7550 0.0783 -1.500 -0.0089 0.00863 0.00170 -0.0205 0.7301 0.1649 -1.250 0.0137 0.00803 0.00156 -0.0197 0.7032 0.3261 -1.000 0.0360 0.00757 0.00146 -0.0188 0.6705 0.4639 -0.750 0.0566 0.00714 0.00139 -0.0174 0.6309 0.6082 -0.500 0.0728 0.00658 0.00141 -0.0147 0.5912 0.7976 -0.250 0.1081 0.00663 0.00163 -0.0156 0.5478 0.9221 0.000 0.1438 0.00688 0.00170 -0.0172 0.5104 0.9433 0.250 0.1756 0.00711 0.00173 -0.0181 0.4751 0.9533 0.500 0.2047 0.00731 0.00177 -0.0183 0.4442 0.9629 0.750 0.2384 0.00751 0.00182 -0.0197 0.4191 0.9685 1.000 0.2698 0.00769 0.00188 -0.0204 0.3978 0.9754 1.250 0.3058 0.00788 0.00194 -0.0223 0.3781 0.9798 1.500 0.3378 0.00804 0.00201 -0.0233 0.3631 0.9852 1.750 0.3738 0.00817 0.00206 -0.0251 0.3506 0.9878 2.000 0.4090 0.00830 0.00212 -0.0269 0.3394 0.9912 2.250 0.4470 0.00845 0.00220 -0.0292 0.3277 0.9953 2.750 0.5179 0.00868 0.00235 -0.0328 0.3080 1.0000 3.000 0.5430 0.00880 0.00242 -0.0323 0.3004 1.0000 3.250 0.5683 0.00890 0.00250 -0.0318 0.2923 1.0000 3.500 0.5933 0.00903 0.00261 -0.0313 0.2843 1.0000 3.750 0.6183 0.00915 0.00271 -0.0308 0.2762 1.0000 4.000 0.6433 0.00928 0.00283 -0.0303 0.2693 1.0000 4.250 0.6681 0.00942 0.00295 -0.0297 0.2616 1.0000 4.500 0.6929 0.00957 0.00310 -0.0292 0.2539 1.0000 4.750 0.7176 0.00973 0.00325 -0.0286 0.2456 1.0000 5.000 0.7422 0.00988 0.00340 -0.0280 0.2389 1.0000 5.250 0.7666 0.01007 0.00357 -0.0274 0.2301 1.0000 5.500 0.7908 0.01026 0.00376 -0.0267 0.2187 1.0000 5.750 0.8150 0.01047 0.00396 -0.0261 0.2093 1.0000 6.000 0.8387 0.01072 0.00416 -0.0254 0.1956 1.0000 6.250 0.8623 0.01099 0.00439 -0.0247 0.1826 1.0000 6.500 0.8858 0.01126 0.00465 -0.0240 0.1721 1.0000 6.750 0.9094 0.01152 0.00490 -0.0233 0.1611 1.0000 7.000 0.9327 0.01180 0.00518 -0.0225 0.1487 1.0000 7.250 0.9553 0.01217 0.00549 -0.0217 0.1313 1.0000 7.500 0.9757 0.01279 0.00594 -0.0206 0.0970 1.0000 7.750 0.9942 0.01361 0.00656 -0.0193 0.0636 1.0000 8.000 1.0140 0.01427 0.00714 -0.0181 0.0461 1.0000 8.250 1.0344 0.01485 0.00768 -0.0170 0.0343 1.0000 8.500 1.0549 0.01541 0.00822 -0.0159 0.0269 1.0000 8.750 1.0758 0.01592 0.00877 -0.0148 0.0227 1.0000 9.000 1.0963 0.01647 0.00936 -0.0137 0.0191 1.0000 9.250 1.1169 0.01700 0.00993 -0.0127 0.0166 1.0000 9.500 1.1363 0.01766 0.01062 -0.0115 0.0142 1.0000 9.750 1.1566 0.01820 0.01124 -0.0105 0.0128 1.0000 10.000 1.1758 0.01884 0.01194 -0.0093 0.0114 1.0000 10.250 1.1933 0.01963 0.01280 -0.0079 0.0103 1.0000 10.500 1.2117 0.02030 0.01357 -0.0067 0.0096 1.0000 10.750 1.2291 0.02102 0.01438 -0.0054 0.0089 1.0000 11.000 1.2457 0.02178 0.01520 -0.0040 0.0083 1.0000 11.250 1.2601 0.02268 0.01617 -0.0024 0.0077 1.0000 11.500 1.2723 0.02369 0.01728 -0.0005 0.0073 1.0000 11.750 1.2845 0.02459 0.01829 0.0013 0.0070 1.0000 12.000 1.2928 0.02558 0.01938 0.0038 0.0067 1.0000 12.250 1.2995 0.02669 0.02062 0.0062 0.0065 1.0000 12.500 1.3051 0.02794 0.02198 0.0084 0.0063 1.0000 12.750 1.3096 0.02937 0.02353 0.0104 0.0061 1.0000 13.000 1.3128 0.03101 0.02528 0.0120 0.0059 1.0000 13.250 1.3146 0.03293 0.02732 0.0133 0.0057 1.0000 13.500 1.3144 0.03524 0.02975 0.0141 0.0056 1.0000 13.750 1.3123 0.03802 0.03267 0.0142 0.0055 1.0000 14.000 1.3077 0.04142 0.03621 0.0137 0.0054 1.0000 14.250 1.3005 0.04555 0.04048 0.0123 0.0053 1.0000 14.500 1.2908 0.05044 0.04552 0.0101 0.0052 1.0000 14.750 1.2791 0.05595 0.05119 0.0074 0.0052 1.0000 15.000 1.2651 0.06197 0.05735 0.0045 0.0051 1.0000 15.250 1.2503 0.06814 0.06367 0.0015 0.0051 1.0000 15.500 1.2339 0.07450 0.07015 -0.0014 0.0051 1.0000 15.750 1.2177 0.08079 0.07656 -0.0041 0.0051 1.0000