XFOIL Version 6.96 Calculated polar for: GIII BL387 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5782 0.08560 0.08395 -0.0029 1.0000 0.0161 -8.500 -0.5797 0.08076 0.07913 -0.0074 1.0000 0.0162 -8.250 -0.5839 0.07486 0.07321 -0.0146 1.0000 0.0164 -8.000 -0.5811 0.06970 0.06801 -0.0188 1.0000 0.0166 -7.750 -0.5760 0.06476 0.06299 -0.0220 1.0000 0.0170 -7.500 -0.5688 0.05634 0.05431 -0.0261 1.0000 0.0183 -7.250 -0.5588 0.05146 0.04926 -0.0266 1.0000 0.0184 -7.000 -0.5492 0.04665 0.04426 -0.0264 1.0000 0.0184 -6.750 -0.5502 0.04049 0.03788 -0.0255 1.0000 0.0188 -6.500 -0.5371 0.03855 0.03587 -0.0244 1.0000 0.0190 -6.250 -0.5238 0.03682 0.03407 -0.0229 1.0000 0.0192 -6.000 -0.5098 0.03512 0.03229 -0.0214 0.9997 0.0195 -5.750 -0.4791 0.03266 0.02968 -0.0234 0.9968 0.0202 -5.500 -0.4444 0.02888 0.02543 -0.0240 0.9936 0.0224 -5.000 -0.3983 0.01315 0.00810 -0.0239 0.9843 0.0191 -4.750 -0.3681 0.01262 0.00754 -0.0245 0.9781 0.0195 -4.500 -0.3359 0.01209 0.00697 -0.0254 0.9727 0.0200 -4.250 -0.3067 0.01155 0.00637 -0.0257 0.9639 0.0206 -4.000 -0.2779 0.01097 0.00573 -0.0257 0.9547 0.0213 -3.750 -0.2509 0.01055 0.00524 -0.0253 0.9433 0.0221 -3.500 -0.2256 0.00995 0.00455 -0.0247 0.9311 0.0229 -3.250 -0.2000 0.00955 0.00416 -0.0241 0.9188 0.0239 -3.000 -0.1738 0.00932 0.00389 -0.0236 0.9064 0.0247 -2.750 -0.1478 0.00907 0.00359 -0.0231 0.8934 0.0257 -2.500 -0.1215 0.00884 0.00331 -0.0226 0.8800 0.0266 -2.250 -0.0945 0.00872 0.00315 -0.0222 0.8672 0.0273 -2.000 -0.0695 0.00817 0.00255 -0.0216 0.8544 0.0291 -1.750 -0.0427 0.00804 0.00241 -0.0212 0.8414 0.0306 -1.500 -0.0159 0.00790 0.00222 -0.0208 0.8272 0.0319 -1.250 0.0109 0.00780 0.00206 -0.0204 0.8106 0.0330 -1.000 0.0370 0.00755 0.00173 -0.0199 0.7923 0.0350 -0.750 0.0638 0.00745 0.00159 -0.0196 0.7740 0.0372 -0.500 0.0908 0.00738 0.00147 -0.0193 0.7557 0.0392 -0.250 0.1179 0.00735 0.00137 -0.0190 0.7373 0.0408 0.000 0.1448 0.00723 0.00121 -0.0186 0.7179 0.0460 0.250 0.1719 0.00721 0.00113 -0.0184 0.6959 0.0503 0.500 0.1972 0.00682 0.00103 -0.0179 0.6710 0.1827 0.750 0.2095 0.00496 0.00096 -0.0154 0.6422 0.7869 1.000 0.2323 0.00492 0.00101 -0.0140 0.6019 0.8541 1.250 0.2562 0.00499 0.00106 -0.0129 0.5655 0.8946 1.500 0.2810 0.00509 0.00112 -0.0120 0.5351 0.9238 1.750 0.3077 0.00521 0.00119 -0.0114 0.5094 0.9508 2.000 0.3378 0.00537 0.00126 -0.0118 0.4859 0.9686 2.250 0.3729 0.00553 0.00135 -0.0132 0.4638 0.9828 2.500 0.4127 0.00572 0.00142 -0.0158 0.4385 0.9884 2.750 0.4472 0.00588 0.00148 -0.0174 0.4102 0.9919 3.000 0.4810 0.00614 0.00155 -0.0188 0.3641 0.9950 3.250 0.5150 0.00655 0.00168 -0.0204 0.2991 0.9974 3.500 0.5489 0.00692 0.00183 -0.0220 0.2483 0.9998 3.750 0.5733 0.00726 0.00197 -0.0215 0.2090 1.0000 4.000 0.5966 0.00755 0.00213 -0.0208 0.1778 1.0000 4.250 0.6200 0.00785 0.00229 -0.0200 0.1500 1.0000 4.500 0.6436 0.00814 0.00247 -0.0192 0.1269 1.0000 4.750 0.6673 0.00843 0.00266 -0.0185 0.1076 1.0000 5.000 0.6914 0.00870 0.00286 -0.0178 0.0934 1.0000 5.250 0.7154 0.00898 0.00306 -0.0171 0.0822 1.0000 5.500 0.7400 0.00920 0.00326 -0.0164 0.0750 1.0000 5.750 0.7646 0.00946 0.00350 -0.0158 0.0678 1.0000 6.000 0.7893 0.00974 0.00373 -0.0153 0.0614 1.0000 6.250 0.8143 0.01000 0.00399 -0.0148 0.0566 1.0000 6.500 0.8393 0.01029 0.00424 -0.0143 0.0522 1.0000 6.750 0.8641 0.01061 0.00456 -0.0138 0.0481 1.0000 7.000 0.8897 0.01085 0.00481 -0.0134 0.0455 1.0000 7.250 0.9146 0.01119 0.00513 -0.0130 0.0425 1.0000 7.500 0.9392 0.01158 0.00554 -0.0125 0.0401 1.0000 7.750 0.9648 0.01183 0.00581 -0.0122 0.0385 1.0000 8.000 0.9900 0.01213 0.00612 -0.0119 0.0367 1.0000 8.250 1.0142 0.01256 0.00655 -0.0114 0.0345 1.0000 8.500 1.0385 0.01301 0.00704 -0.0109 0.0330 1.0000 8.750 1.0636 0.01330 0.00737 -0.0106 0.0319 1.0000 9.000 1.0885 0.01364 0.00773 -0.0102 0.0305 1.0000 9.250 1.1126 0.01407 0.00816 -0.0098 0.0289 1.0000 9.500 1.1351 0.01470 0.00883 -0.0092 0.0273 1.0000 9.750 1.1600 0.01501 0.00918 -0.0088 0.0263 1.0000 10.000 1.1842 0.01539 0.00961 -0.0085 0.0252 1.0000 10.250 1.2078 0.01584 0.01008 -0.0080 0.0240 1.0000 10.500 1.2275 0.01677 0.01105 -0.0071 0.0225 1.0000 10.750 1.2514 0.01714 0.01147 -0.0067 0.0219 1.0000 11.000 1.2743 0.01760 0.01200 -0.0062 0.0211 1.0000 11.250 1.2969 0.01808 0.01252 -0.0056 0.0203 1.0000 11.500 1.3188 0.01862 0.01308 -0.0051 0.0195 1.0000 11.750 1.3362 0.01963 0.01414 -0.0040 0.0185 1.0000 12.000 1.3556 0.02038 0.01499 -0.0031 0.0181 1.0000 12.250 1.3758 0.02099 0.01568 -0.0023 0.0176 1.0000 12.500 1.3949 0.02168 0.01645 -0.0014 0.0172 1.0000 12.750 1.4131 0.02241 0.01724 -0.0005 0.0167 1.0000 13.000 1.4304 0.02317 0.01807 0.0005 0.0163 1.0000 13.250 1.4463 0.02399 0.01895 0.0017 0.0158 1.0000 13.500 1.4572 0.02504 0.02007 0.0034 0.0154 1.0000 13.750 1.4578 0.02672 0.02186 0.0061 0.0149 1.0000 14.000 1.4639 0.02807 0.02332 0.0079 0.0147 1.0000 14.250 1.4725 0.02928 0.02464 0.0093 0.0145 1.0000 14.500 1.4792 0.03073 0.02621 0.0104 0.0143 1.0000 14.750 1.4841 0.03246 0.02804 0.0114 0.0141 1.0000 15.000 1.4877 0.03444 0.03014 0.0119 0.0139 1.0000 15.250 1.4896 0.03673 0.03256 0.0122 0.0137 1.0000 15.500 1.4900 0.03937 0.03532 0.0120 0.0135 1.0000 15.750 1.4884 0.04241 0.03847 0.0114 0.0133 1.0000 16.000 1.4853 0.04589 0.04207 0.0103 0.0132 1.0000 16.250 1.4794 0.04993 0.04624 0.0087 0.0130 1.0000 16.500 1.4710 0.05461 0.05104 0.0065 0.0129 1.0000 16.750 1.4593 0.05997 0.05654 0.0038 0.0128 1.0000 17.000 1.4439 0.06610 0.06280 0.0006 0.0128 1.0000 17.250 1.4246 0.07295 0.06979 -0.0030 0.0127 1.0000 17.500 1.4007 0.08076 0.07775 -0.0071 0.0127 1.0000 17.750 1.3738 0.08936 0.08649 -0.0116 0.0127 1.0000 18.000 1.3447 0.09867 0.09595 -0.0165 0.0127 1.0000 18.250 1.3127 0.10870 0.10613 -0.0217 0.0128 1.0000 18.500 1.2795 0.11929 0.11687 -0.0273 0.0129 1.0000 18.750 1.2462 0.13019 0.12792 -0.0332 0.0129 1.0000 19.000 1.2114 0.14188 0.13974 -0.0397 0.0130 1.0000 19.250 1.1710 0.15558 0.15359 -0.0476 0.0131 1.0000