XFOIL Version 6.96 Calculated polar for: WB-135/35 13.5% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.4269 0.10537 0.10174 -0.0473 1.0000 0.0137 -12.500 -0.4932 0.08622 0.08249 -0.0568 1.0000 0.0129 -12.250 -0.5427 0.07329 0.06939 -0.0646 1.0000 0.0122 -12.000 -0.5615 0.06700 0.06302 -0.0684 1.0000 0.0124 -11.750 -0.5887 0.05971 0.05557 -0.0728 1.0000 0.0120 -11.500 -0.6076 0.05432 0.05007 -0.0760 1.0000 0.0120 -11.250 -0.6244 0.04983 0.04549 -0.0784 1.0000 0.0120 -11.000 -0.6490 0.04542 0.04095 -0.0799 1.0000 0.0118 -10.750 -0.6636 0.04251 0.03793 -0.0812 0.9969 0.0119 -10.500 -0.6529 0.03877 0.03390 -0.0856 0.9852 0.0121 -10.250 -0.6364 0.03589 0.03076 -0.0885 0.9754 0.0125 -10.000 -0.6196 0.03332 0.02793 -0.0901 0.9658 0.0128 -9.750 -0.5994 0.03107 0.02540 -0.0915 0.9574 0.0132 -9.500 -0.5748 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1.0000 5.500 0.9486 0.01456 0.00659 -0.0742 0.3473 1.0000 5.750 0.9679 0.01492 0.00694 -0.0727 0.3386 1.0000 6.000 0.9874 0.01527 0.00729 -0.0713 0.3307 1.0000 6.250 1.0046 0.01570 0.00766 -0.0695 0.3196 1.0000 6.500 1.0217 0.01609 0.00802 -0.0676 0.3068 1.0000 6.750 1.0394 0.01645 0.00841 -0.0660 0.2957 1.0000 7.000 1.0563 0.01684 0.00879 -0.0641 0.2862 1.0000 7.250 1.0714 0.01724 0.00918 -0.0620 0.2767 1.0000 7.500 1.0871 0.01760 0.00958 -0.0599 0.2660 1.0000 7.750 1.1007 0.01803 0.01001 -0.0576 0.2524 1.0000 8.000 1.1124 0.01855 0.01047 -0.0551 0.2329 1.0000 8.250 1.1250 0.01910 0.01100 -0.0528 0.2120 1.0000 8.500 1.1321 0.01996 0.01167 -0.0499 0.1772 1.0000 8.750 1.1332 0.02128 0.01269 -0.0465 0.1348 1.0000 9.000 1.1118 0.02420 0.01494 -0.0409 0.0404 1.0000 9.250 1.1116 0.02591 0.01651 -0.0380 0.0216 1.0000 9.500 1.1205 0.02707 0.01774 -0.0360 0.0190 1.0000 9.750 1.1307 0.02815 0.01894 -0.0343 0.0178 1.0000 10.000 1.1399 0.02934 0.02026 -0.0327 0.0170 1.0000 10.250 1.1476 0.03069 0.02174 -0.0310 0.0159 1.0000 10.500 1.1538 0.03220 0.02338 -0.0294 0.0151 1.0000 10.750 1.1580 0.03392 0.02523 -0.0279 0.0144 1.0000 11.000 1.1586 0.03601 0.02749 -0.0263 0.0137 1.0000 11.250 1.1562 0.03846 0.03009 -0.0248 0.0132 1.0000 11.500 1.1530 0.04108 0.03285 -0.0236 0.0129 1.0000 11.750 1.1536 0.04344 0.03533 -0.0226 0.0127 1.0000 12.000 1.1524 0.04606 0.03809 -0.0219 0.0124 1.0000 12.250 1.1507 0.04883 0.04097 -0.0213 0.0123 1.0000 12.500 1.1492 0.05168 0.04394 -0.0208 0.0121 1.0000 12.750 1.1474 0.05468 0.04705 -0.0206 0.0115 1.0000 13.000 1.1431 0.05806 0.05054 -0.0204 0.0114 1.0000 13.250 1.1401 0.06139 0.05397 -0.0205 0.0111 1.0000 13.500 1.1379 0.06473 0.05741 -0.0207 0.0107 1.0000 13.750 1.1354 0.06819 0.06097 -0.0210 0.0105 1.0000 14.000 1.1320 0.07182 0.06467 -0.0214 0.0101 1.0000 14.250 1.1306 0.07521 0.06815 -0.0218 0.0100 1.0000 14.500 1.1288 0.07869 0.07170 -0.0222 0.0098 1.0000 14.750 1.1292 0.08186 0.07494 -0.0224 0.0097 1.0000 15.000 1.1297 0.08492 0.07803 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