XFOIL Version 6.96 Calculated polar for: AH 79-K-143/18 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.1568 0.11114 0.10811 -0.0828 0.8156 0.0238 -13.250 -0.1641 0.10656 0.10353 -0.0860 0.8153 0.0247 -13.000 -0.1670 0.10220 0.09918 -0.0883 0.8149 0.0249 -12.750 -0.1669 0.09833 0.09531 -0.0901 0.8143 0.0249 -12.500 -0.1727 0.09299 0.08999 -0.0914 0.8139 0.0254 -12.250 -0.1699 0.08995 0.08694 -0.0923 0.8131 0.0256 -12.000 -0.1687 0.08630 0.08331 -0.0935 0.8125 0.0258 -11.750 -0.1644 0.08346 0.08048 -0.0942 0.8118 0.0262 -11.500 -0.1662 0.07924 0.07628 -0.0958 0.8112 0.0263 -11.250 -0.1640 0.07606 0.07311 -0.0967 0.8104 0.0272 -11.000 -0.2668 0.04547 0.04250 -0.1119 0.8109 0.0192 -10.750 -0.3012 0.03823 0.03514 -0.1161 0.8099 0.0192 -10.500 -0.3292 0.03369 0.03050 -0.1166 0.8087 0.0190 -10.250 -0.4753 0.03887 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0.01609 0.00922 -0.0742 0.7787 0.0318 -5.250 -0.2087 0.01571 0.00885 -0.0733 0.7771 0.0355 -5.000 -0.1847 0.01552 0.00861 -0.0727 0.7758 0.0389 -4.750 -0.1628 0.01513 0.00825 -0.0717 0.7746 0.0458 -4.500 -0.1407 0.01481 0.00795 -0.0707 0.7736 0.0557 -4.250 -0.1197 0.01455 0.00775 -0.0696 0.7714 0.0735 -4.000 -0.0991 0.01427 0.00761 -0.0685 0.7683 0.0967 -3.750 -0.0768 0.01403 0.00747 -0.0677 0.7661 0.1228 -3.500 -0.0542 0.01372 0.00728 -0.0669 0.7642 0.1589 -3.250 -0.0327 0.01329 0.00709 -0.0660 0.7626 0.2206 -3.000 -0.0135 0.01268 0.00686 -0.0647 0.7611 0.3222 -2.750 0.0002 0.01181 0.00658 -0.0624 0.7598 0.4809 -2.500 0.0093 0.01088 0.00641 -0.0588 0.7587 0.6821 -2.250 0.0266 0.01098 0.00697 -0.0561 0.7548 0.7857 -2.000 0.0512 0.01116 0.00715 -0.0551 0.7515 0.8201 -1.750 0.0780 0.01131 0.00724 -0.0545 0.7494 0.8362 -1.500 0.1052 0.01148 0.00735 -0.0540 0.7477 0.8475 -1.250 0.1331 0.01165 0.00748 -0.0535 0.7464 0.8547 -1.000 0.1609 0.01173 0.00751 -0.0531 0.7453 0.8626 -0.750 0.1889 0.01181 0.00753 -0.0528 0.7443 0.8682 -0.500 0.2144 0.01209 0.00782 -0.0518 0.7420 0.8753 -0.250 0.2357 0.01236 0.00810 -0.0501 0.7377 0.8836 0.000 0.2624 0.01260 0.00834 -0.0490 0.7354 0.8929 0.250 0.2932 0.01268 0.00840 -0.0489 0.7337 0.8999 0.500 0.3248 0.01257 0.00826 -0.0494 0.7322 0.9037 0.750 0.3493 0.01238 0.00803 -0.0489 0.7309 0.9085 1.000 0.3775 0.01215 0.00776 -0.0490 0.7297 0.9112 1.250 0.4029 0.01213 0.00776 -0.0486 0.7254 0.9133 1.500 0.4316 0.01201 0.00766 -0.0488 0.7220 0.9159 1.750 0.4598 0.01181 0.00744 -0.0489 0.7196 0.9190 2.000 0.4815 0.01159 0.00720 -0.0477 0.7175 0.9235 2.250 0.5121 0.01131 0.00689 -0.0483 0.7158 0.9252 2.500 0.5385 0.01120 0.00683 -0.0481 0.7111 0.9271 2.750 0.5668 0.01104 0.00668 -0.0483 0.7070 0.9291 3.000 0.5964 0.01082 0.00646 -0.0487 0.7039 0.9312 3.250 0.6244 0.01059 0.00621 -0.0488 0.7012 0.9334 3.500 0.6359 0.01051 0.00618 -0.0457 0.6944 0.9378 3.750 0.6646 0.01027 0.00595 -0.0459 0.6896 0.9391 4.000 0.6939 0.01010 0.00578 -0.0464 0.6851 0.9402 4.250 0.7175 0.00999 0.00573 -0.0457 0.6773 0.9420 4.500 0.7456 0.00984 0.00556 -0.0458 0.6719 0.9434 4.750 0.7650 0.00977 0.00555 -0.0442 0.6626 0.9460 5.000 0.7832 0.00963 0.00541 -0.0423 0.6506 0.9487 5.250 0.8022 0.00953 0.00529 -0.0406 0.6383 0.9512 5.500 0.8245 0.00947 0.00521 -0.0396 0.6235 0.9528 5.750 0.8453 0.00948 0.00521 -0.0384 0.6095 0.9545 6.000 0.8622 0.00951 0.00522 -0.0363 0.5902 0.9568 6.250 0.8733 0.00961 0.00522 -0.0331 0.5660 0.9591 6.500 0.8793 0.00977 0.00528 -0.0290 0.5379 0.9617 6.750 0.8850 0.01000 0.00539 -0.0250 0.5048 0.9643 7.000 0.8911 0.01022 0.00555 -0.0211 0.4776 0.9680 7.250 0.8931 0.01051 0.00576 -0.0165 0.4534 0.9718 7.500 0.8984 0.01104 0.00618 -0.0130 0.4209 0.9749 7.750 0.9055 0.01186 0.00685 -0.0106 0.3810 0.9780 8.000 0.9117 0.01320 0.00797 -0.0092 0.3285 0.9816 8.250 0.9163 0.01537 0.00968 -0.0090 0.2431 0.9844 8.500 0.9219 0.01738 0.01123 -0.0085 0.1618 0.9869 8.750 0.9262 0.01940 0.01281 -0.0077 0.0864 0.9897 9.000 0.9349 0.02110 0.01425 -0.0072 0.0453 0.9928 9.250 0.9446 0.02263 0.01570 -0.0062 0.0312 1.0000 9.500 0.9565 0.02347 0.01658 -0.0048 0.0281 1.0000 9.750 0.9625 0.02480 0.01792 -0.0031 0.0241 1.0000 10.000 0.9771 0.02564 0.01883 -0.0023 0.0227 1.0000 10.250 0.9891 0.02671 0.01994 -0.0013 0.0211 1.0000 10.500 0.9979 0.02807 0.02131 -0.0002 0.0194 1.0000 10.750 1.0045 0.02961 0.02293 0.0010 0.0183 1.0000 11.000 1.0149 0.03093 0.02432 0.0019 0.0180 1.0000 11.250 1.0249 0.03231 0.02578 0.0027 0.0178 1.0000 11.500 1.0361 0.03363 0.02715 0.0033 0.0167 1.0000 11.750 1.0462 0.03510 0.02867 0.0040 0.0162 1.0000 12.000 1.0550 0.03671 0.03034 0.0047 0.0160 1.0000 12.250 1.0640 0.03834 0.03203 0.0054 0.0157 1.0000 12.500 1.0691 0.04025 0.03397 0.0064 0.0150 1.0000 12.750 1.0785 0.04183 0.03561 0.0073 0.0150 1.0000 13.000 1.0873 0.04340 0.03725 0.0088 0.0146 1.0000 13.250 1.0998 0.04480 0.03875 0.0093 0.0145 1.0000 13.500 1.1117 0.04629 0.04034 0.0098 0.0142 1.0000 13.750 1.1230 0.04784 0.04199 0.0101 0.0138 1.0000 14.000 1.1348 0.04937 0.04363 0.0109 0.0137 1.0000 14.250 1.1454 0.05106 0.04542 0.0115 0.0134 1.0000 14.500 1.1559 0.05286 0.04737 0.0125 0.0133 1.0000 14.750 1.1633 0.05488 0.04952 0.0129 0.0130 1.0000 15.000 1.1701 0.05704 0.05181 0.0133 0.0129 1.0000 15.250 1.1745 0.05960 0.05455 0.0139 0.0128 1.0000 15.500 1.1762 0.06245 0.05757 0.0144 0.0127 1.0000 15.750 1.1734 0.06590 0.06123 0.0148 0.0127 1.0000 16.000 1.1646 0.07027 0.06588 0.0153 0.0130 1.0000 16.250 1.1665 0.07287 0.06853 0.0144 0.0125 1.0000 16.500 1.1420 0.07968 0.07573 0.0144 0.0130 1.0000 16.750 1.1266 0.08513 0.08141 0.0132 0.0131 1.0000 17.000 1.1103 0.09093 0.08740 0.0114 0.0130 1.0000 17.250 1.0900 0.09768 0.09437 0.0091 0.0133 1.0000 17.500 1.0672 0.10516 0.10207 0.0060 0.0134 1.0000 17.750 1.0437 0.11316 0.11025 0.0022 0.0137 1.0000 18.000 1.0237 0.12100 0.11825 -0.0020 0.0139 1.0000 18.250 0.9987 0.13035 0.12776 -0.0074 0.0141 1.0000 18.500 0.9739 0.14055 0.13812 -0.0137 0.0142 1.0000