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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4323 0.08630 0.08409 -0.0012 1.0000 0.0245 -8.500 -0.4333 0.08211 0.07991 -0.0027 1.0000 0.0249 -8.250 -0.4359 0.07766 0.07547 -0.0046 1.0000 0.0254 -8.000 -0.4460 0.07197 0.06980 -0.0090 1.0000 0.0261 -7.750 -0.4613 0.06592 0.06375 -0.0157 1.0000 0.0262 -7.500 -0.4745 0.05913 0.05683 -0.0214 1.0000 0.0264 -7.250 -0.4769 0.05320 0.05073 -0.0238 1.0000 0.0265 -7.000 -0.4734 0.04824 0.04575 -0.0240 1.0000 0.0267 -6.750 -0.4642 0.04489 0.04240 -0.0239 1.0000 0.0269 -6.500 -0.4537 0.04179 0.03928 -0.0238 1.0000 0.0271 -6.250 -0.4427 0.03860 0.03604 -0.0238 1.0000 0.0275 -6.000 -0.4311 0.03537 0.03275 -0.0236 1.0000 0.0279 -5.750 -0.4195 0.03224 0.02952 -0.0231 1.0000 0.0286 -5.500 -0.4096 0.02826 0.02500 -0.0206 1.0000 0.0309 -5.250 -0.3939 0.02371 0.02033 -0.0212 0.9967 0.0313 -5.000 -0.3666 0.02087 0.01748 -0.0234 0.9917 0.0317 -4.750 -0.3371 0.01847 0.01500 -0.0254 0.9859 0.0323 -4.500 -0.3078 0.01618 0.01258 -0.0268 0.9775 0.0336 -4.250 -0.2776 0.01283 0.00869 -0.0271 0.9684 0.0368 -4.000 -0.2800 0.02618 0.02172 -0.0241 0.9794 0.0372 -3.750 -0.2473 0.02455 0.02003 -0.0258 0.9719 0.0382 -3.500 -0.2122 0.02455 0.01959 -0.0258 0.9609 0.0423 -3.250 -0.1854 0.02092 0.01580 -0.0264 0.9488 0.0434 -3.000 -0.1580 0.01963 0.01450 -0.0266 0.9355 0.0445 -2.750 -0.1316 0.01884 0.01361 -0.0260 0.9210 0.0474 -2.500 -0.1058 0.01761 0.01203 -0.0249 0.9063 0.0512 -2.250 -0.0790 0.01500 0.00909 -0.0233 0.8924 0.0411 -2.000 -0.0528 0.01411 0.00802 -0.0224 0.8780 0.0416 -1.750 -0.0265 0.01321 0.00698 -0.0216 0.8641 0.0417 -1.500 -0.0002 0.01256 0.00621 -0.0208 0.8489 0.0421 -1.250 0.0255 0.01172 0.00527 -0.0200 0.8319 0.0430 -1.000 0.0508 0.01114 0.00469 -0.0193 0.8130 0.0445 -0.750 0.0765 0.01075 0.00425 -0.0186 0.7921 0.0455 -0.500 0.1023 0.01040 0.00383 -0.0178 0.7674 0.0466 -0.250 0.1280 0.01012 0.00345 -0.0171 0.7411 0.0478 0.000 0.1545 0.00998 0.00323 -0.0165 0.7124 0.0495 0.250 0.1796 0.00958 0.00275 -0.0158 0.6836 0.0514 0.500 0.2055 0.00942 0.00250 -0.0152 0.6540 0.0534 0.750 0.2316 0.00936 0.00232 -0.0147 0.6247 0.0558 1.000 0.2582 0.00936 0.00221 -0.0143 0.5958 0.0586 1.250 0.2844 0.00922 0.00199 -0.0138 0.5721 0.0633 1.500 0.3114 0.00921 0.00191 -0.0135 0.5516 0.0682 1.750 0.3384 0.00917 0.00183 -0.0132 0.5333 0.0777 2.000 0.3564 0.00749 0.00175 -0.0120 0.5181 0.6660 2.250 0.3815 0.00686 0.00198 -0.0102 0.5010 0.9648 2.500 0.4413 0.00705 0.00203 -0.0168 0.4753 0.9971 2.750 0.4740 0.00717 0.00207 -0.0179 0.4531 1.0000 3.000 0.4989 0.00732 0.00211 -0.0173 0.4291 1.0000 3.250 0.5239 0.00749 0.00217 -0.0167 0.4004 1.0000 3.500 0.5481 0.00776 0.00224 -0.0160 0.3512 1.0000 3.750 0.5713 0.00822 0.00240 -0.0153 0.2912 1.0000 4.000 0.5949 0.00865 0.00260 -0.0146 0.2490 1.0000 4.250 0.6188 0.00903 0.00282 -0.0139 0.2188 1.0000 4.500 0.6433 0.00934 0.00302 -0.0133 0.1953 1.0000 4.750 0.6677 0.00969 0.00324 -0.0127 0.1728 1.0000 5.000 0.6925 0.01000 0.00345 -0.0121 0.1523 1.0000 5.250 0.7173 0.01034 0.00370 -0.0116 0.1347 1.0000 5.500 0.7421 0.01068 0.00397 -0.0111 0.1210 1.0000 5.750 0.7671 0.01103 0.00426 -0.0106 0.1100 1.0000 6.000 0.7917 0.01145 0.00460 -0.0101 0.1003 1.0000 6.250 0.8171 0.01173 0.00489 -0.0097 0.0935 1.0000 6.500 0.8418 0.01215 0.00526 -0.0092 0.0865 1.0000 6.750 0.8671 0.01247 0.00558 -0.0088 0.0808 1.0000 7.000 0.8915 0.01294 0.00603 -0.0083 0.0752 1.0000 7.250 0.9168 0.01326 0.00636 -0.0079 0.0708 1.0000 7.500 0.9403 0.01386 0.00691 -0.0073 0.0657 1.0000 7.750 0.9658 0.01415 0.00727 -0.0070 0.0624 1.0000 8.000 0.9902 0.01460 0.00770 -0.0065 0.0590 1.0000 8.250 1.0130 0.01527 0.00838 -0.0059 0.0558 1.0000 8.500 1.0377 0.01565 0.00882 -0.0055 0.0534 1.0000 8.750 1.0618 0.01611 0.00928 -0.0050 0.0509 1.0000 9.000 1.0826 0.01701 0.01018 -0.0042 0.0483 1.0000 9.250 1.1067 0.01745 0.01070 -0.0038 0.0468 1.0000 9.500 1.1300 0.01798 0.01128 -0.0032 0.0452 1.0000 9.750 1.1528 0.01855 0.01188 -0.0027 0.0436 1.0000 10.000 1.1732 0.01941 0.01275 -0.0019 0.0421 1.0000 10.250 1.1933 0.02033 0.01374 -0.0011 0.0408 1.0000 10.500 1.2154 0.02092 0.01443 -0.0005 0.0396 1.0000 10.750 1.2364 0.02162 0.01520 0.0002 0.0385 1.0000 11.000 1.2568 0.02235 0.01599 0.0009 0.0375 1.0000 11.250 1.2761 0.02317 0.01684 0.0017 0.0366 1.0000 11.500 1.2918 0.02447 0.01817 0.0029 0.0356 1.0000 11.750 1.3074 0.02578 0.01959 0.0040 0.0349 1.0000 12.000 1.3251 0.02661 0.02056 0.0049 0.0342 1.0000 12.250 1.3413 0.02755 0.02162 0.0060 0.0334 1.0000 12.500 1.3560 0.02858 0.02275 0.0071 0.0327 1.0000 12.750 1.3678 0.02966 0.02392 0.0086 0.0321 1.0000 13.000 1.3779 0.03080 0.02514 0.0101 0.0316 1.0000 13.250 1.3862 0.03210 0.02651 0.0115 0.0311 1.0000 13.500 1.3925 0.03369 0.02816 0.0128 0.0306 1.0000 13.750 1.3945 0.03596 0.03053 0.0141 0.0301 1.0000 14.000 1.3936 0.03854 0.03328 0.0152 0.0297 1.0000 14.250 1.3959 0.04061 0.03552 0.0155 0.0294 1.0000 14.500 1.3964 0.04304 0.03812 0.0155 0.0291 1.0000 14.750 1.3950 0.04587 0.04112 0.0152 0.0288 1.0000 15.000 1.3919 0.04911 0.04452 0.0144 0.0284 1.0000 15.250 1.3867 0.05278 0.04835 0.0132 0.0282 1.0000 15.500 1.3799 0.05688 0.05261 0.0115 0.0279 1.0000 15.750 1.3703 0.06155 0.05744 0.0093 0.0277 1.0000 16.000 1.3583 0.06677 0.06282 0.0066 0.0275 1.0000 16.250 1.3434 0.07260 0.06881 0.0035 0.0274 1.0000 16.500 1.3256 0.07912 0.07550 -0.0002 0.0272 1.0000 16.750 1.3036 0.08665 0.08321 -0.0046 0.0272 1.0000 17.000 1.2756 0.09580 0.09255 -0.0101 0.0272 1.0000 17.250 1.2349 0.10813 0.10511 -0.0177 0.0273 1.0000