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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5188 0.09150 0.09009 -0.0008 1.0000 0.0067 -8.250 -0.5168 0.08681 0.08543 -0.0043 1.0000 0.0067 -8.000 -0.5293 0.07873 0.07738 -0.0121 1.0000 0.0069 -7.750 -0.5209 0.07384 0.07247 -0.0177 0.9847 0.0071 -7.500 -0.5112 0.07008 0.06865 -0.0210 0.9581 0.0073 -7.250 -0.5037 0.06652 0.06499 -0.0230 0.9423 0.0076 -7.000 -0.4932 0.06260 0.06097 -0.0254 0.9306 0.0080 -6.750 -0.4803 0.05824 0.05650 -0.0278 0.9207 0.0086 -6.500 -0.4639 0.05339 0.05150 -0.0299 0.9123 0.0097 -4.750 -0.3397 0.01645 0.01194 -0.0266 0.8608 0.0081 -4.500 -0.3143 0.01461 0.00980 -0.0259 0.8530 0.0088 -4.250 -0.2881 0.01361 0.00859 -0.0254 0.8454 0.0098 -4.000 -0.2609 0.01297 0.00782 -0.0251 0.8371 0.0104 -3.750 -0.2339 0.01238 0.00705 -0.0248 0.8298 0.0108 -3.500 -0.2095 0.01043 0.00492 -0.0241 0.8224 0.0125 -3.250 -0.1821 0.01020 0.00465 -0.0241 0.8147 0.0140 -3.000 -0.1552 0.00971 0.00408 -0.0238 0.8058 0.0153 -2.750 -0.1281 0.00928 0.00357 -0.0236 0.7964 0.0161 -2.500 -0.1007 0.00896 0.00317 -0.0234 0.7879 0.0168 -2.250 -0.0744 0.00830 0.00238 -0.0231 0.7797 0.0189 -2.000 -0.0469 0.00795 0.00196 -0.0230 0.7717 0.0210 -1.500 0.0088 0.00758 0.00146 -0.0229 0.7539 0.0246 -1.250 0.0366 0.00739 0.00125 -0.0229 0.7444 0.0359 -1.000 0.0630 0.00687 0.00110 -0.0228 0.7346 0.1605 -0.750 0.0885 0.00621 0.00100 -0.0228 0.7238 0.3545 -0.500 0.1103 0.00512 0.00090 -0.0221 0.7126 0.6756 -0.250 0.1278 0.00442 0.00094 -0.0195 0.7001 0.9113 0.000 0.1548 0.00447 0.00101 -0.0188 0.6873 0.9643 0.250 0.1937 0.00461 0.00107 -0.0210 0.6727 0.9843 0.500 0.2429 0.00478 0.00112 -0.0258 0.6526 0.9920 0.750 0.2983 0.00495 0.00117 -0.0320 0.6305 0.9994 1.000 0.3286 0.00501 0.00115 -0.0327 0.6149 1.0000 1.250 0.3561 0.00506 0.00114 -0.0328 0.6006 1.0000 1.500 0.3835 0.00512 0.00113 -0.0328 0.5861 1.0000 2.000 0.4376 0.00527 0.00115 -0.0328 0.5556 1.0000 2.250 0.4643 0.00535 0.00118 -0.0327 0.5387 1.0000 2.500 0.4910 0.00545 0.00123 -0.0326 0.5209 1.0000 2.750 0.5175 0.00556 0.00127 -0.0325 0.5025 1.0000 3.000 0.5438 0.00571 0.00134 -0.0323 0.4765 1.0000 3.250 0.5699 0.00589 0.00142 -0.0322 0.4493 1.0000 3.500 0.5959 0.00605 0.00153 -0.0320 0.4286 1.0000 3.750 0.6217 0.00622 0.00163 -0.0318 0.4073 1.0000 4.000 0.6474 0.00641 0.00176 -0.0315 0.3850 1.0000 4.250 0.6721 0.00678 0.00193 -0.0312 0.3390 1.0000 4.500 0.6958 0.00731 0.00217 -0.0308 0.2711 1.0000 4.750 0.7176 0.00817 0.00258 -0.0303 0.1703 1.0000 5.000 0.7411 0.00865 0.00291 -0.0298 0.1372 1.0000 5.250 0.7643 0.00918 0.00323 -0.0293 0.0900 1.0000 5.500 0.7876 0.00968 0.00359 -0.0287 0.0569 1.0000 5.750 0.8089 0.01052 0.00420 -0.0278 0.0136 1.0000 6.000 0.8319 0.01112 0.00490 -0.0270 0.0099 1.0000 6.250 0.8559 0.01153 0.00536 -0.0265 0.0092 1.0000 6.500 0.8797 0.01199 0.00588 -0.0259 0.0084 1.0000 6.750 0.9030 0.01254 0.00650 -0.0253 0.0076 1.0000 7.000 0.9256 0.01320 0.00723 -0.0245 0.0070 1.0000 7.250 0.9466 0.01408 0.00819 -0.0236 0.0064 1.0000 7.500 0.9614 0.01584 0.01013 -0.0218 0.0059 1.0000 7.750 0.9796 0.01717 0.01157 -0.0205 0.0057 1.0000 8.000 1.0012 0.01796 0.01243 -0.0198 0.0056 1.0000 8.250 1.0221 0.01889 0.01346 -0.0189 0.0054 1.0000 8.500 1.0424 0.01994 0.01461 -0.0180 0.0052 1.0000 8.750 1.0621 0.02111 0.01589 -0.0170 0.0050 1.0000 9.000 1.0812 0.02241 0.01733 -0.0159 0.0047 1.0000 9.250 1.0990 0.02390 0.01897 -0.0148 0.0044 1.0000 9.500 1.1149 0.02578 0.02105 -0.0134 0.0042 1.0000 9.750 1.1233 0.02962 0.02529 -0.0110 0.0043 1.0000 10.750 1.1094 0.04574 0.04258 0.0004 0.0063 1.0000 11.000 1.0966 0.04881 0.04581 0.0028 0.0062 1.0000 11.250 1.0818 0.05234 0.04951 0.0042 0.0062 1.0000 11.500 1.0659 0.05633 0.05368 0.0046 0.0061 1.0000 11.750 1.0491 0.06086 0.05836 0.0039 0.0061 1.0000 12.000 1.0325 0.06587 0.06352 0.0022 0.0061 1.0000 12.250 1.0153 0.07156 0.06936 -0.0006 0.0061 1.0000 12.500 0.9987 0.07782 0.07577 -0.0043 0.0061 1.0000 12.750 0.9809 0.08510 0.08319 -0.0090 0.0062 1.0000 13.000 0.9612 0.09376 0.09198 -0.0149 0.0063 1.0000 13.250 0.9369 0.10503 0.10340 -0.0224 0.0064 1.0000