XFOIL Version 6.96 Calculated polar for: GIII BL430 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5679 0.09014 0.08776 0.0055 1.0000 0.0142 -8.500 -0.5692 0.08528 0.08292 0.0019 1.0000 0.0142 -8.250 -0.5750 0.07914 0.07680 -0.0048 1.0000 0.0141 -8.000 -0.5754 0.07293 0.07054 -0.0110 1.0000 0.0141 -7.750 -0.5716 0.06739 0.06492 -0.0152 1.0000 0.0141 -7.500 -0.5645 0.06246 0.05990 -0.0181 1.0000 0.0142 -7.250 -0.5532 0.05862 0.05597 -0.0198 1.0000 0.0143 -7.000 -0.5402 0.05499 0.05224 -0.0211 1.0000 0.0146 -6.750 -0.5267 0.05104 0.04815 -0.0220 1.0000 0.0149 -6.500 -0.5134 0.04649 0.04342 -0.0226 1.0000 0.0151 -6.000 -0.4938 0.02990 0.02574 -0.0213 0.9942 0.0165 -5.750 -0.4643 0.02851 0.02423 -0.0225 0.9829 0.0168 -5.250 -0.4118 0.01898 0.01367 -0.0230 0.9544 0.0198 -5.000 -0.3810 0.01887 0.01353 -0.0238 0.9397 0.0201 -4.750 -0.3528 0.01842 0.01300 -0.0239 0.9230 0.0205 -4.500 -0.3269 0.01728 0.01166 -0.0234 0.9061 0.0213 -4.250 -0.3029 0.01440 0.00824 -0.0223 0.8909 0.0233 -4.000 -0.2768 0.01418 0.00799 -0.0218 0.8764 0.0237 -3.750 -0.2505 0.01396 0.00771 -0.0214 0.8633 0.0242 -3.500 -0.2242 0.01349 0.00714 -0.0209 0.8506 0.0248 -3.250 -0.1979 0.01290 0.00644 -0.0204 0.8385 0.0257 -3.000 -0.1716 0.01233 0.00572 -0.0199 0.8265 0.0267 -2.750 -0.1455 0.01180 0.00508 -0.0193 0.8140 0.0274 -2.500 -0.1190 0.01145 0.00470 -0.0189 0.8004 0.0280 -2.250 -0.0924 0.01118 0.00440 -0.0185 0.7861 0.0286 -2.000 -0.0658 0.01090 0.00407 -0.0180 0.7713 0.0293 -1.750 -0.0391 0.01065 0.00376 -0.0176 0.7562 0.0303 -1.500 -0.0126 0.01042 0.00344 -0.0172 0.7364 0.0313 -1.250 0.0135 0.01019 0.00310 -0.0166 0.7101 0.0320 -1.000 0.0393 0.01000 0.00281 -0.0160 0.6775 0.0328 -0.750 0.0654 0.00993 0.00262 -0.0155 0.6419 0.0337 -0.500 0.0916 0.00990 0.00244 -0.0151 0.6056 0.0347 -0.250 0.1180 0.00988 0.00230 -0.0147 0.5748 0.0362 0.000 0.1449 0.00984 0.00217 -0.0143 0.5522 0.0374 0.250 0.1719 0.00974 0.00203 -0.0141 0.5355 0.0389 0.500 0.1991 0.00969 0.00195 -0.0138 0.5202 0.0405 0.750 0.2263 0.00967 0.00188 -0.0136 0.5034 0.0425 1.000 0.2535 0.00966 0.00181 -0.0133 0.4839 0.0450 1.250 0.2807 0.00967 0.00178 -0.0131 0.4653 0.0480 1.500 0.3080 0.00970 0.00175 -0.0129 0.4472 0.0510 1.750 0.3353 0.00970 0.00172 -0.0127 0.4297 0.0558 2.000 0.3625 0.00975 0.00172 -0.0125 0.4100 0.0626 2.250 0.3896 0.00979 0.00174 -0.0123 0.3819 0.0799 2.500 0.4031 0.00795 0.00179 -0.0101 0.3456 0.7921 2.750 0.4232 0.00798 0.00195 -0.0081 0.2979 0.8942 3.000 0.4568 0.00827 0.00214 -0.0091 0.2534 0.9600 3.250 0.4962 0.00860 0.00231 -0.0117 0.2205 0.9849 3.500 0.5363 0.00887 0.00245 -0.0144 0.1986 0.9969 3.750 0.5664 0.00911 0.00260 -0.0150 0.1794 1.0000 4.000 0.5910 0.00935 0.00275 -0.0144 0.1624 1.0000 4.250 0.6157 0.00962 0.00291 -0.0138 0.1449 1.0000 4.500 0.6403 0.00989 0.00309 -0.0132 0.1289 1.0000 4.750 0.6653 0.01016 0.00328 -0.0126 0.1162 1.0000 5.000 0.6904 0.01042 0.00348 -0.0121 0.1062 1.0000 5.250 0.7156 0.01069 0.00370 -0.0116 0.0974 1.0000 5.500 0.7410 0.01096 0.00393 -0.0112 0.0902 1.0000 5.750 0.7664 0.01122 0.00417 -0.0107 0.0842 1.0000 6.000 0.7918 0.01151 0.00442 -0.0103 0.0781 1.0000 6.250 0.8172 0.01180 0.00469 -0.0099 0.0731 1.0000 6.500 0.8427 0.01209 0.00497 -0.0096 0.0685 1.0000 6.750 0.8680 0.01241 0.00527 -0.0092 0.0641 1.0000 7.000 0.8934 0.01271 0.00558 -0.0088 0.0602 1.0000 7.250 0.9185 0.01307 0.00591 -0.0084 0.0562 1.0000 7.500 0.9438 0.01339 0.00625 -0.0080 0.0534 1.0000 7.750 0.9688 0.01374 0.00661 -0.0077 0.0502 1.0000 8.000 0.9934 0.01416 0.00701 -0.0073 0.0472 1.0000 8.250 1.0184 0.01450 0.00739 -0.0069 0.0450 1.0000 8.500 1.0430 0.01490 0.00780 -0.0065 0.0428 1.0000 8.750 1.0671 0.01537 0.00827 -0.0061 0.0407 1.0000 9.000 1.0914 0.01579 0.00874 -0.0056 0.0392 1.0000 9.250 1.1155 0.01622 0.00922 -0.0052 0.0376 1.0000 9.500 1.1392 0.01669 0.00971 -0.0048 0.0360 1.0000 9.750 1.1622 0.01724 0.01028 -0.0043 0.0345 1.0000 10.000 1.1852 0.01778 0.01087 -0.0038 0.0335 1.0000 10.250 1.2081 0.01830 0.01146 -0.0032 0.0326 1.0000 10.500 1.2306 0.01885 0.01207 -0.0027 0.0316 1.0000 10.750 1.2525 0.01944 0.01270 -0.0021 0.0307 1.0000 11.000 1.2737 0.02009 0.01340 -0.0015 0.0298 1.0000 11.250 1.2934 0.02088 0.01423 -0.0007 0.0290 1.0000 11.500 1.3134 0.02160 0.01503 0.0000 0.0284 1.0000 11.750 1.3334 0.02227 0.01579 0.0008 0.0277 1.0000 12.000 1.3527 0.02299 0.01660 0.0016 0.0270 1.0000 12.250 1.3710 0.02376 0.01745 0.0024 0.0264 1.0000 12.500 1.3881 0.02459 0.01836 0.0034 0.0259 1.0000 12.750 1.4038 0.02549 0.01933 0.0044 0.0254 1.0000 13.000 1.4167 0.02649 0.02040 0.0057 0.0249 1.0000 13.250 1.4256 0.02766 0.02165 0.0074 0.0245 1.0000 13.500 1.4311 0.02912 0.02319 0.0091 0.0241 1.0000 13.750 1.4395 0.03044 0.02463 0.0102 0.0238 1.0000 14.000 1.4467 0.03195 0.02627 0.0111 0.0236 1.0000 14.250 1.4527 0.03367 0.02812 0.0118 0.0232 1.0000 14.500 1.4578 0.03560 0.03018 0.0121 0.0229 1.0000 14.750 1.4614 0.03782 0.03252 0.0121 0.0226 1.0000 15.000 1.4635 0.04035 0.03518 0.0117 0.0223 1.0000 15.250 1.4637 0.04327 0.03822 0.0110 0.0220 1.0000 15.500 1.4621 0.04659 0.04167 0.0098 0.0218 1.0000 15.750 1.4588 0.05032 0.04554 0.0083 0.0216 1.0000 16.000 1.4532 0.05451 0.04986 0.0064 0.0214 1.0000 16.250 1.4453 0.05915 0.05463 0.0041 0.0213 1.0000 16.500 1.4347 0.06427 0.05988 0.0017 0.0211 1.0000 16.750 1.4215 0.06987 0.06561 -0.0011 0.0210 1.0000 17.000 1.4054 0.07598 0.07184 -0.0041 0.0209 1.0000 17.250 1.3876 0.08262 0.07862 -0.0075 0.0208 1.0000 17.500 1.3680 0.08975 0.08588 -0.0112 0.0207 1.0000 17.750 1.3474 0.09734 0.09360 -0.0152 0.0206 1.0000 18.000 1.3260 0.10525 0.10164 -0.0194 0.0206 1.0000 18.250 1.3042 0.11340 0.10991 -0.0237 0.0205 1.0000 18.500 1.2831 0.12155 0.11817 -0.0281 0.0204 1.0000 18.750 1.2622 0.12977 0.12649 -0.0326 0.0202 1.0000 19.000 1.2428 0.13784 0.13466 -0.0371 0.0201 1.0000