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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5584 0.08955 0.08790 0.0065 1.0000 0.0172 -8.250 -0.5569 0.08543 0.08380 0.0033 1.0000 0.0174 -8.000 -0.5579 0.08058 0.07898 -0.0021 1.0000 0.0177 -7.750 -0.5544 0.07494 0.07330 -0.0086 1.0000 0.0183 -7.500 -0.5509 0.06474 0.06289 -0.0185 1.0000 0.0191 -7.250 -0.5409 0.05989 0.05793 -0.0204 1.0000 0.0191 -7.000 -0.5295 0.05525 0.05316 -0.0216 1.0000 0.0191 -6.750 -0.5232 0.05022 0.04803 -0.0225 1.0000 0.0194 -6.500 -0.5074 0.04781 0.04555 -0.0226 1.0000 0.0195 -6.250 -0.4904 0.04554 0.04322 -0.0227 1.0000 0.0197 -6.000 -0.4727 0.04340 0.04102 -0.0225 1.0000 0.0200 -5.750 -0.4549 0.04124 0.03879 -0.0222 1.0000 0.0204 -4.750 -0.3492 0.02485 0.02131 -0.0252 0.9665 0.0211 -4.500 -0.3309 0.01373 0.00890 -0.0228 0.9481 0.0231 -4.250 -0.3038 0.01364 0.00879 -0.0225 0.9306 0.0235 -4.000 -0.2778 0.01358 0.00869 -0.0220 0.9135 0.0240 -3.750 -0.2520 0.01304 0.00803 -0.0214 0.8981 0.0247 -3.500 -0.2263 0.01207 0.00687 -0.0206 0.8842 0.0259 -3.250 -0.2006 0.01121 0.00582 -0.0200 0.8710 0.0269 -3.000 -0.1743 0.01084 0.00540 -0.0195 0.8580 0.0275 -2.750 -0.1473 0.01062 0.00515 -0.0192 0.8455 0.0282 -2.500 -0.1203 0.01032 0.00480 -0.0188 0.8337 0.0290 -2.250 -0.0934 0.00998 0.00439 -0.0184 0.8209 0.0299 -2.000 -0.0664 0.00980 0.00412 -0.0180 0.8054 0.0307 -1.750 -0.0407 0.00917 0.00342 -0.0174 0.7887 0.0316 -1.500 -0.0141 0.00890 0.00312 -0.0170 0.7693 0.0324 -1.250 0.0126 0.00876 0.00291 -0.0166 0.7448 0.0333 -1.000 0.0393 0.00864 0.00271 -0.0161 0.7149 0.0344 -0.750 0.0658 0.00858 0.00251 -0.0157 0.6784 0.0354 -0.500 0.0926 0.00853 0.00234 -0.0153 0.6461 0.0361 -0.250 0.1186 0.00824 0.00195 -0.0148 0.6176 0.0374 0.000 0.1455 0.00820 0.00183 -0.0145 0.5899 0.0387 0.250 0.1727 0.00820 0.00175 -0.0143 0.5640 0.0403 0.500 0.1999 0.00822 0.00169 -0.0140 0.5403 0.0418 0.750 0.2271 0.00812 0.00152 -0.0138 0.5216 0.0437 1.000 0.2546 0.00809 0.00145 -0.0136 0.5056 0.0461 1.250 0.2822 0.00809 0.00142 -0.0134 0.4906 0.0487 1.500 0.3097 0.00806 0.00135 -0.0132 0.4753 0.0525 2.000 0.3649 0.00806 0.00129 -0.0129 0.4434 0.0641 2.250 0.3923 0.00803 0.00130 -0.0127 0.4253 0.0964 2.500 0.4040 0.00598 0.00136 -0.0100 0.4090 0.8623 2.750 0.4279 0.00591 0.00147 -0.0085 0.3839 0.9538 3.000 0.4667 0.00627 0.00158 -0.0109 0.3200 0.9847 3.250 0.5084 0.00672 0.00175 -0.0141 0.2611 0.9950 3.500 0.5488 0.00707 0.00189 -0.0170 0.2221 0.9997 3.750 0.5744 0.00730 0.00202 -0.0166 0.2004 1.0000 4.000 0.5991 0.00752 0.00214 -0.0160 0.1817 1.0000 4.250 0.6237 0.00775 0.00228 -0.0153 0.1621 1.0000 4.500 0.6483 0.00801 0.00242 -0.0147 0.1434 1.0000 4.750 0.6731 0.00826 0.00258 -0.0141 0.1273 1.0000 5.000 0.6979 0.00852 0.00276 -0.0135 0.1137 1.0000 5.250 0.7230 0.00876 0.00294 -0.0129 0.1037 1.0000 5.500 0.7483 0.00898 0.00313 -0.0124 0.0957 1.0000 5.750 0.7736 0.00925 0.00334 -0.0119 0.0874 1.0000 6.000 0.7993 0.00947 0.00354 -0.0115 0.0815 1.0000 6.250 0.8248 0.00974 0.00378 -0.0111 0.0755 1.0000 6.500 0.8507 0.00997 0.00399 -0.0107 0.0709 1.0000 6.750 0.8761 0.01028 0.00426 -0.0103 0.0653 1.0000 7.000 0.9021 0.01051 0.00449 -0.0100 0.0617 1.0000 7.250 0.9272 0.01088 0.00482 -0.0096 0.0566 1.0000 7.500 0.9533 0.01110 0.00506 -0.0093 0.0542 1.0000 7.750 0.9788 0.01142 0.00535 -0.0090 0.0508 1.0000 8.000 1.0040 0.01177 0.00571 -0.0086 0.0476 1.0000 8.250 1.0297 0.01205 0.00600 -0.0083 0.0454 1.0000 8.500 1.0547 0.01244 0.00637 -0.0080 0.0429 1.0000 8.750 1.0794 0.01286 0.00681 -0.0076 0.0408 1.0000 9.000 1.1048 0.01317 0.00715 -0.0073 0.0394 1.0000 9.250 1.1297 0.01353 0.00753 -0.0069 0.0378 1.0000 9.500 1.1535 0.01405 0.00804 -0.0065 0.0359 1.0000 9.750 1.1775 0.01451 0.00854 -0.0060 0.0347 1.0000 10.000 1.2021 0.01488 0.00896 -0.0057 0.0337 1.0000 10.250 1.2263 0.01529 0.00941 -0.0053 0.0327 1.0000 10.500 1.2499 0.01577 0.00990 -0.0048 0.0317 1.0000 10.750 1.2719 0.01643 0.01059 -0.0042 0.0305 1.0000 11.000 1.2931 0.01716 0.01138 -0.0035 0.0296 1.0000 11.250 1.3165 0.01760 0.01188 -0.0031 0.0291 1.0000 11.500 1.3393 0.01808 0.01242 -0.0026 0.0284 1.0000 11.750 1.3615 0.01861 0.01299 -0.0020 0.0277 1.0000 12.000 1.3829 0.01919 0.01361 -0.0014 0.0270 1.0000 12.250 1.4031 0.01988 0.01434 -0.0007 0.0264 1.0000 12.500 1.4199 0.02088 0.01540 0.0003 0.0257 1.0000 12.750 1.4348 0.02199 0.01660 0.0015 0.0251 1.0000 13.000 1.4542 0.02262 0.01731 0.0023 0.0248 1.0000 13.250 1.4725 0.02329 0.01806 0.0032 0.0244 1.0000 13.500 1.4893 0.02404 0.01888 0.0042 0.0239 1.0000 13.750 1.5033 0.02487 0.01978 0.0055 0.0235 1.0000 14.000 1.5146 0.02579 0.02078 0.0071 0.0231 1.0000 14.250 1.5244 0.02684 0.02190 0.0085 0.0228 1.0000 14.500 1.5325 0.02808 0.02321 0.0098 0.0225 1.0000 14.750 1.5384 0.02960 0.02481 0.0109 0.0221 1.0000 15.000 1.5403 0.03160 0.02690 0.0117 0.0218 1.0000 15.250 1.5356 0.03448 0.02988 0.0121 0.0214 1.0000 15.500 1.5305 0.03765 0.03319 0.0120 0.0211 1.0000 15.750 1.5356 0.03993 0.03558 0.0115 0.0210 1.0000 16.000 1.5372 0.04273 0.03849 0.0107 0.0208 1.0000 16.250 1.5364 0.04601 0.04190 0.0095 0.0207 1.0000 16.500 1.5330 0.04976 0.04577 0.0079 0.0205 1.0000 16.750 1.5269 0.05401 0.05015 0.0060 0.0203 1.0000 17.000 1.5180 0.05876 0.05503 0.0038 0.0202 1.0000 17.250 1.5065 0.06393 0.06033 0.0014 0.0200 1.0000 17.500 1.4920 0.06963 0.06616 -0.0014 0.0199 1.0000 17.750 1.4749 0.07583 0.07248 -0.0044 0.0198 1.0000 18.000 1.4561 0.08254 0.07932 -0.0077 0.0198 1.0000 18.250 1.4356 0.08973 0.08663 -0.0114 0.0197 1.0000 18.500 1.4138 0.09740 0.09443 -0.0153 0.0196 1.0000 18.750 1.3909 0.10542 0.10257 -0.0195 0.0195 1.0000 19.000 1.3674 0.11370 0.11098 -0.0239 0.0195 1.0000 19.250 1.3446 0.12205 0.11944 -0.0284 0.0194 1.0000