XFOIL Version 6.96 Calculated polar for: GIII BL332 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.6197 0.10076 0.09909 0.0045 1.0000 0.0082 -10.000 -0.6215 0.09578 0.09411 0.0018 1.0000 0.0083 -9.000 -0.8292 0.02035 0.01623 -0.0238 1.0000 0.0101 -8.750 -0.8100 0.01885 0.01452 -0.0227 1.0000 0.0103 -8.500 -0.7895 0.01779 0.01331 -0.0217 1.0000 0.0104 -8.250 -0.7687 0.01687 0.01226 -0.0207 1.0000 0.0105 -8.000 -0.7469 0.01604 0.01132 -0.0198 0.9997 0.0106 -7.750 -0.7174 0.01520 0.01036 -0.0205 0.9968 0.0108 -7.500 -0.6872 0.01444 0.00948 -0.0214 0.9939 0.0109 -7.250 -0.6579 0.01373 0.00868 -0.0220 0.9895 0.0111 -7.000 -0.6274 0.01306 0.00792 -0.0228 0.9857 0.0113 -6.750 -0.5981 0.01249 0.00726 -0.0233 0.9803 0.0115 -6.500 -0.5674 0.01199 0.00669 -0.0241 0.9751 0.0118 -6.250 -0.5384 0.01150 0.00613 -0.0245 0.9668 0.0121 -6.000 -0.5098 0.01101 0.00557 -0.0248 0.9575 0.0124 -5.750 -0.4825 0.01060 0.00508 -0.0247 0.9462 0.0126 -5.250 -0.4308 0.00984 0.00419 -0.0238 0.9221 0.0134 -5.000 -0.4047 0.00960 0.00391 -0.0234 0.9103 0.0139 -4.750 -0.3785 0.00940 0.00368 -0.0231 0.8984 0.0145 -4.500 -0.3522 0.00921 0.00343 -0.0227 0.8864 0.0152 -4.000 -0.2992 0.00885 0.00295 -0.0220 0.8629 0.0165 -3.750 -0.2725 0.00864 0.00273 -0.0218 0.8529 0.0177 -3.500 -0.2455 0.00853 0.00259 -0.0216 0.8433 0.0187 -3.250 -0.2182 0.00841 0.00245 -0.0214 0.8332 0.0198 -3.000 -0.1910 0.00829 0.00229 -0.0212 0.8239 0.0208 -2.750 -0.1637 0.00820 0.00216 -0.0211 0.8136 0.0213 -2.500 -0.1370 0.00800 0.00193 -0.0208 0.8006 0.0231 -2.250 -0.1099 0.00792 0.00182 -0.0206 0.7863 0.0244 -2.000 -0.0827 0.00785 0.00171 -0.0204 0.7724 0.0258 -1.750 -0.0554 0.00777 0.00160 -0.0203 0.7604 0.0270 -1.500 -0.0280 0.00771 0.00150 -0.0202 0.7489 0.0277 -1.250 -0.0008 0.00760 0.00134 -0.0200 0.7367 0.0291 -1.000 0.0264 0.00751 0.00120 -0.0198 0.7217 0.0308 -0.750 0.0536 0.00746 0.00112 -0.0196 0.7042 0.0327 -0.500 0.0809 0.00743 0.00104 -0.0194 0.6878 0.0347 -0.250 0.1083 0.00741 0.00098 -0.0193 0.6720 0.0368 0.000 0.1356 0.00738 0.00093 -0.0192 0.6546 0.0449 0.250 0.1615 0.00712 0.00088 -0.0189 0.6337 0.1446 0.500 0.1768 0.00539 0.00076 -0.0173 0.6073 0.6908 0.750 0.2018 0.00537 0.00079 -0.0166 0.5716 0.7485 1.000 0.2276 0.00543 0.00083 -0.0161 0.5394 0.7814 1.250 0.2532 0.00551 0.00088 -0.0156 0.5052 0.8090 1.500 0.2779 0.00565 0.00096 -0.0149 0.4626 0.8414 1.750 0.3035 0.00584 0.00103 -0.0145 0.4176 0.8595 2.000 0.3295 0.00597 0.00110 -0.0141 0.3853 0.8781 2.250 0.3546 0.00610 0.00120 -0.0134 0.3534 0.9043 2.500 0.3804 0.00634 0.00130 -0.0130 0.3121 0.9188 2.750 0.4065 0.00657 0.00142 -0.0127 0.2761 0.9319 3.000 0.4333 0.00684 0.00156 -0.0126 0.2359 0.9444 3.250 0.4609 0.00719 0.00172 -0.0127 0.1894 0.9559 3.500 0.4901 0.00749 0.00188 -0.0132 0.1553 0.9658 3.750 0.5202 0.00778 0.00205 -0.0138 0.1276 0.9748 4.000 0.5519 0.00810 0.00224 -0.0149 0.0992 0.9815 4.250 0.5832 0.00837 0.00242 -0.0158 0.0810 0.9873 4.500 0.6149 0.00861 0.00261 -0.0169 0.0691 0.9920 4.750 0.6465 0.00885 0.00280 -0.0179 0.0602 0.9956 5.000 0.6784 0.00910 0.00299 -0.0190 0.0517 0.9987 5.250 0.7064 0.00930 0.00318 -0.0192 0.0474 1.0000 5.500 0.7304 0.00954 0.00339 -0.0185 0.0418 1.0000 5.750 0.7548 0.00975 0.00360 -0.0179 0.0384 1.0000 6.000 0.7791 0.01001 0.00383 -0.0173 0.0340 1.0000 6.250 0.8038 0.01026 0.00408 -0.0168 0.0308 1.0000 6.500 0.8286 0.01051 0.00433 -0.0163 0.0283 1.0000 6.750 0.8532 0.01081 0.00461 -0.0158 0.0256 1.0000 7.000 0.8782 0.01108 0.00490 -0.0154 0.0241 1.0000 7.250 0.9032 0.01136 0.00520 -0.0150 0.0227 1.0000 7.500 0.9280 0.01167 0.00551 -0.0146 0.0213 1.0000 7.750 0.9525 0.01203 0.00587 -0.0141 0.0197 1.0000 8.000 0.9771 0.01238 0.00625 -0.0137 0.0187 1.0000 8.250 1.0020 0.01270 0.00662 -0.0133 0.0180 1.0000 8.500 1.0266 0.01305 0.00700 -0.0129 0.0173 1.0000 8.750 1.0509 0.01343 0.00740 -0.0125 0.0166 1.0000 9.000 1.0750 0.01383 0.00783 -0.0121 0.0159 1.0000 9.250 1.0985 0.01432 0.00835 -0.0116 0.0149 1.0000 9.500 1.1218 0.01482 0.00890 -0.0111 0.0144 1.0000 9.750 1.1456 0.01524 0.00937 -0.0106 0.0141 1.0000 10.000 1.1691 0.01568 0.00986 -0.0102 0.0137 1.0000 10.250 1.1924 0.01612 0.01036 -0.0097 0.0132 1.0000 10.500 1.2154 0.01659 0.01087 -0.0092 0.0127 1.0000 10.750 1.2380 0.01710 0.01142 -0.0087 0.0122 1.0000 11.000 1.2599 0.01766 0.01203 -0.0081 0.0118 1.0000 11.250 1.2808 0.01833 0.01275 -0.0074 0.0113 1.0000 11.500 1.3007 0.01907 0.01356 -0.0066 0.0109 1.0000 11.750 1.3222 0.01959 0.01418 -0.0059 0.0107 1.0000 12.000 1.3429 0.02017 0.01482 -0.0052 0.0103 1.0000 12.250 1.3629 0.02079 0.01552 -0.0045 0.0100 1.0000 12.500 1.3821 0.02146 0.01626 -0.0036 0.0097 1.0000 12.750 1.4006 0.02215 0.01701 -0.0027 0.0093 1.0000 13.000 1.4182 0.02288 0.01781 -0.0017 0.0090 1.0000 13.250 1.4344 0.02369 0.01868 -0.0006 0.0087 1.0000 13.500 1.4474 0.02463 0.01971 0.0009 0.0084 1.0000 13.750 1.4565 0.02574 0.02092 0.0029 0.0081 1.0000 14.000 1.4672 0.02670 0.02198 0.0045 0.0080 1.0000 14.250 1.4765 0.02778 0.02316 0.0061 0.0078 1.0000 14.500 1.4847 0.02899 0.02447 0.0076 0.0076 1.0000 14.750 1.4919 0.03035 0.02593 0.0088 0.0074 1.0000 15.000 1.4982 0.03185 0.02754 0.0099 0.0072 1.0000 15.250 1.5031 0.03358 0.02937 0.0108 0.0070 1.0000 15.500 1.5069 0.03551 0.03140 0.0114 0.0068 1.0000 15.750 1.5090 0.03775 0.03374 0.0117 0.0066 1.0000 16.000 1.5087 0.04039 0.03648 0.0116 0.0065 1.0000 16.250 1.5063 0.04348 0.03970 0.0111 0.0063 1.0000 16.500 1.5005 0.04716 0.04350 0.0101 0.0062 1.0000 16.750 1.4913 0.05159 0.04807 0.0085 0.0061 1.0000 17.000 1.4779 0.05694 0.05357 0.0060 0.0060 1.0000 17.250 1.4597 0.06346 0.06025 0.0026 0.0060 1.0000 17.500 1.4364 0.07115 0.06811 -0.0016 0.0060 1.0000 17.750 1.4071 0.08028 0.07742 -0.0067 0.0060 1.0000 18.000 1.3689 0.09140 0.08873 -0.0127 0.0061 1.0000 18.250 1.3175 0.10549 0.10303 -0.0202 0.0063 1.0000 18.500 1.2476 0.12375 0.12152 -0.0298 0.0066 1.0000