XFOIL Version 6.96 Calculated polar for: NASA LRN 1015 (NASA TM 102840) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.1234 0.08652 0.08339 -0.1057 0.7222 0.0067 -11.250 -0.1286 0.08138 0.07825 -0.1079 0.7210 0.0065 -11.000 -0.1372 0.07592 0.07283 -0.1106 0.7198 0.0067 -10.750 -0.1534 0.06906 0.06600 -0.1143 0.7184 0.0067 -10.500 -0.3021 0.04185 0.03859 -0.1297 0.7159 0.0068 -10.250 -0.2364 0.04723 0.04410 -0.1296 0.7148 0.0069 -10.000 -0.2956 0.04044 0.03709 -0.1260 0.7124 0.0069 -9.750 -0.4093 0.02335 0.01879 -0.1153 0.7105 0.0073 -9.500 -0.3943 0.02196 0.01722 -0.1140 0.7091 0.0074 -9.250 -0.3800 0.02025 0.01527 -0.1125 0.7077 0.0076 -9.000 -0.3624 0.01890 0.01371 -0.1114 0.7063 0.0077 -8.750 -0.3425 0.01779 0.01243 -0.1104 0.7049 0.0078 -8.500 -0.3213 0.01683 0.01133 -0.1096 0.7035 0.0080 -8.250 -0.2986 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1.0902 0.01266 0.00688 -0.0691 0.2457 0.8844 6.750 1.0961 0.01340 0.00761 -0.0661 0.2318 0.8942 7.000 1.1051 0.01408 0.00830 -0.0637 0.2206 0.9072 7.250 1.1166 0.01474 0.00900 -0.0618 0.2104 0.9294 7.500 1.1492 0.01551 0.00976 -0.0646 0.1960 0.9643 7.750 1.1639 0.01626 0.01048 -0.0635 0.1868 1.0000 8.000 1.1773 0.01702 0.01121 -0.0621 0.1775 1.0000 8.250 1.1890 0.01788 0.01202 -0.0606 0.1672 1.0000 8.500 1.2024 0.01866 0.01277 -0.0593 0.1594 1.0000 8.750 1.2159 0.01944 0.01353 -0.0581 0.1524 1.0000 9.000 1.2300 0.02020 0.01427 -0.0569 0.1458 1.0000 9.250 1.2429 0.02104 0.01509 -0.0556 0.1394 1.0000 9.500 1.2570 0.02181 0.01585 -0.0545 0.1337 1.0000 9.750 1.2694 0.02270 0.01672 -0.0533 0.1271 1.0000 10.000 1.2836 0.02349 0.01752 -0.0523 0.1226 1.0000 10.250 1.2965 0.02436 0.01838 -0.0511 0.1172 1.0000 10.500 1.3094 0.02524 0.01925 -0.0501 0.1119 1.0000 10.750 1.3222 0.02616 0.02017 -0.0490 0.1071 1.0000 11.000 1.3339 0.02715 0.02114 -0.0479 0.1017 1.0000 11.250 1.3479 0.02800 0.02202 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0.0450 1.0000 16.250 1.5565 0.05473 0.04916 -0.0333 0.0430 1.0000 16.500 1.5621 0.05674 0.05121 -0.0329 0.0407 1.0000 16.750 1.5687 0.05864 0.05315 -0.0326 0.0381 1.0000 17.000 1.5704 0.06112 0.05564 -0.0322 0.0343 1.0000 17.250 1.5736 0.06347 0.05802 -0.0320 0.0307 1.0000 17.500 1.5720 0.06641 0.06096 -0.0317 0.0261 1.0000 17.750 1.5689 0.06958 0.06415 -0.0316 0.0221 1.0000 18.000 1.5651 0.07291 0.06751 -0.0316 0.0188 1.0000 18.250 1.5624 0.07621 0.07086 -0.0318 0.0168 1.0000 18.500 1.5585 0.07975 0.07446 -0.0321 0.0143 1.0000 18.750 1.5554 0.08325 0.07803 -0.0326 0.0125 1.0000 19.000 1.5495 0.08719 0.08203 -0.0332 0.0100 1.0000 19.250 1.5375 0.09209 0.08698 -0.0342 0.0068 1.0000