XFOIL Version 6.96 Calculated polar for: BELL/WORTMANN FX 69-H-083 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5140 0.09148 0.08947 -0.0018 1.0000 0.0043 -8.250 -0.5126 0.08689 0.08491 -0.0051 1.0000 0.0043 -8.000 -0.5119 0.08211 0.08016 -0.0095 1.0000 0.0043 -7.750 -0.5067 0.07651 0.07454 -0.0164 0.9577 0.0043 -7.500 -0.5017 0.07115 0.06911 -0.0212 0.9386 0.0043 -7.250 -0.4948 0.06585 0.06372 -0.0252 0.9251 0.0043 -6.750 -0.4734 0.05501 0.05259 -0.0313 0.9047 0.0045 -6.500 -0.4596 0.04958 0.04697 -0.0332 0.8964 0.0047 -6.250 -0.4436 0.04439 0.04154 -0.0342 0.8886 0.0052 -6.000 -0.4267 0.03850 0.03534 -0.0345 0.8813 0.0056 -5.750 -0.4103 0.03224 0.02865 -0.0338 0.8742 0.0057 -5.500 -0.3950 0.02420 0.01990 -0.0319 0.8673 0.0056 -5.250 -0.3764 0.01834 0.01317 -0.0299 0.8608 0.0060 -5.000 -0.3520 0.01620 0.01059 -0.0290 0.8543 0.0064 -4.750 -0.3276 0.01448 0.00855 -0.0284 0.8476 0.0071 -4.500 -0.3011 0.01400 0.00798 -0.0282 0.8407 0.0077 -4.250 -0.2744 0.01365 0.00754 -0.0280 0.8333 0.0088 -4.000 -0.2475 0.01325 0.00703 -0.0279 0.8254 0.0104 -3.500 -0.1947 0.01181 0.00525 -0.0271 0.8101 0.0124 -3.250 -0.1691 0.01101 0.00435 -0.0267 0.8022 0.0145 -3.000 -0.1421 0.01075 0.00403 -0.0266 0.7924 0.0166 -2.750 -0.1152 0.01037 0.00356 -0.0263 0.7824 0.0179 -2.500 -0.0884 0.01003 0.00311 -0.0261 0.7726 0.0187 -2.250 -0.0612 0.00980 0.00276 -0.0259 0.7616 0.0198 -2.000 -0.0341 0.00955 0.00241 -0.0258 0.7487 0.0203 -1.750 -0.0067 0.00934 0.00209 -0.0257 0.7359 0.0206 -1.500 0.0208 0.00911 0.00175 -0.0255 0.7243 0.0238 -1.250 0.0484 0.00893 0.00155 -0.0255 0.7137 0.0350 -1.000 0.0756 0.00869 0.00141 -0.0255 0.7033 0.0794 -0.500 0.1274 0.00766 0.00121 -0.0254 0.6815 0.3643 -0.250 0.1473 0.00649 0.00111 -0.0243 0.6691 0.6969 0.000 0.1707 0.00598 0.00129 -0.0223 0.6550 0.9479 0.250 0.2224 0.00618 0.00138 -0.0273 0.6342 0.9870 0.500 0.2772 0.00635 0.00137 -0.0334 0.6082 0.9978 0.750 0.3106 0.00644 0.00134 -0.0348 0.5892 1.0000 1.000 0.3372 0.00651 0.00132 -0.0347 0.5735 1.0000 1.250 0.3637 0.00659 0.00132 -0.0345 0.5581 1.0000 1.500 0.3902 0.00667 0.00133 -0.0344 0.5442 1.0000 1.750 0.4166 0.00676 0.00135 -0.0342 0.5291 1.0000 2.000 0.4428 0.00686 0.00139 -0.0340 0.5128 1.0000 2.250 0.4689 0.00698 0.00145 -0.0339 0.4938 1.0000 2.500 0.4948 0.00714 0.00151 -0.0336 0.4716 1.0000 2.750 0.5206 0.00730 0.00160 -0.0334 0.4505 1.0000 3.000 0.5462 0.00749 0.00170 -0.0331 0.4275 1.0000 3.250 0.5718 0.00767 0.00184 -0.0329 0.4062 1.0000 3.500 0.5974 0.00785 0.00197 -0.0326 0.3885 1.0000 3.750 0.6229 0.00803 0.00211 -0.0323 0.3714 1.0000 4.000 0.6482 0.00824 0.00227 -0.0320 0.3521 1.0000 4.250 0.6730 0.00854 0.00247 -0.0317 0.3224 1.0000 4.500 0.6976 0.00888 0.00272 -0.0313 0.2876 1.0000 4.750 0.7211 0.00937 0.00302 -0.0309 0.2395 1.0000 5.000 0.7411 0.01042 0.00357 -0.0301 0.1425 1.0000 5.250 0.7635 0.01108 0.00399 -0.0296 0.0883 1.0000 5.500 0.7875 0.01148 0.00436 -0.0291 0.0699 1.0000 5.750 0.8093 0.01223 0.00488 -0.0285 0.0263 1.0000 6.000 0.8321 0.01286 0.00548 -0.0278 0.0114 1.0000 6.250 0.8560 0.01330 0.00599 -0.0273 0.0090 1.0000 6.500 0.8792 0.01386 0.00662 -0.0267 0.0074 1.0000 6.750 0.9002 0.01478 0.00771 -0.0257 0.0062 1.0000 7.000 0.9225 0.01543 0.00844 -0.0250 0.0059 1.0000 7.250 0.9439 0.01620 0.00931 -0.0242 0.0055 1.0000 7.500 0.9656 0.01688 0.01008 -0.0235 0.0049 1.0000 7.750 0.9873 0.01754 0.01080 -0.0228 0.0043 1.0000 8.000 1.0074 0.01838 0.01177 -0.0219 0.0040 1.0000 8.250 1.0265 0.01933 0.01280 -0.0210 0.0037 1.0000 8.500 1.0435 0.02054 0.01413 -0.0197 0.0034 1.0000 8.750 1.0538 0.02280 0.01658 -0.0176 0.0031 1.0000 9.000 1.0704 0.02418 0.01812 -0.0163 0.0030 1.0000 9.250 1.0863 0.02565 0.01977 -0.0149 0.0029 1.0000 9.500 1.1006 0.02740 0.02172 -0.0134 0.0028 1.0000 9.750 1.1128 0.02942 0.02398 -0.0117 0.0028 1.0000 10.000 1.1222 0.03172 0.02654 -0.0098 0.0027 1.0000 10.250 1.1274 0.03423 0.02933 -0.0076 0.0027 1.0000 10.500 1.1269 0.03686 0.03223 -0.0049 0.0026 1.0000 10.750 1.1225 0.03976 0.03540 -0.0024 0.0026 1.0000 11.000 1.1150 0.04297 0.03888 -0.0004 0.0026 1.0000 11.250 1.1047 0.04657 0.04272 0.0010 0.0026 1.0000 11.500 1.0924 0.05058 0.04698 0.0016 0.0026 1.0000 11.750 1.0782 0.05512 0.05174 0.0014 0.0026 1.0000 12.000 1.0625 0.06024 0.05706 0.0001 0.0026 1.0000 12.250 1.0459 0.06598 0.06299 -0.0022 0.0027 1.0000 12.500 1.0286 0.07239 0.06958 -0.0055 0.0027 1.0000 12.750 1.0110 0.07949 0.07684 -0.0096 0.0027 1.0000 13.000 0.9926 0.08745 0.08495 -0.0145 0.0027 1.0000 13.250 0.9742 0.09626 0.09389 -0.0201 0.0027 1.0000 13.500 0.9554 0.10603 0.10377 -0.0261 0.0028 1.0000 13.750 0.9348 0.11750 0.11533 -0.0325 0.0028 1.0000 14.000 0.9107 0.13128 0.12917 -0.0387 0.0029 1.0000