XFOIL Version 6.96 Calculated polar for: HQ 2.1/9.5 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.250 -1.0067 0.04417 0.04189 -0.0659 1.0000 0.0061 -14.000 -1.0338 0.03770 0.03518 -0.0705 1.0000 0.0061 -13.750 -1.0466 0.03429 0.03162 -0.0713 1.0000 0.0061 -13.500 -1.0541 0.03225 0.02947 -0.0698 1.0000 0.0062 -13.250 -1.0486 0.03062 0.02773 -0.0688 1.0000 0.0063 -13.000 -1.0392 0.02917 0.02618 -0.0679 1.0000 0.0064 -12.750 -1.0274 0.02785 0.02475 -0.0670 1.0000 0.0066 -12.500 -1.0142 0.02659 0.02337 -0.0662 1.0000 0.0067 -12.250 -0.9991 0.02550 0.02217 -0.0653 1.0000 0.0069 -12.000 -0.9836 0.02438 0.02093 -0.0644 1.0000 0.0071 -11.750 -0.9660 0.02351 0.01996 -0.0635 1.0000 0.0073 -11.500 -0.9487 0.02254 0.01887 -0.0626 1.0000 0.0075 -11.250 -0.9317 0.02152 0.01772 -0.0615 1.0000 0.0077 -11.000 -0.9121 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0.1158 -1.500 0.1434 0.00678 0.00097 -0.0684 0.7213 0.1739 -1.250 0.1703 0.00628 0.00085 -0.0686 0.7155 0.3061 -1.000 0.1970 0.00574 0.00080 -0.0687 0.7089 0.4623 -0.750 0.2248 0.00564 0.00078 -0.0686 0.7024 0.5017 -0.500 0.2526 0.00551 0.00077 -0.0686 0.6950 0.5486 -0.250 0.2801 0.00540 0.00080 -0.0685 0.6869 0.6039 0.000 0.3078 0.00535 0.00084 -0.0685 0.6776 0.6451 0.250 0.3358 0.00535 0.00085 -0.0684 0.6663 0.6623 0.500 0.3636 0.00539 0.00087 -0.0683 0.6517 0.6725 0.750 0.3910 0.00546 0.00089 -0.0681 0.6302 0.6808 1.000 0.4176 0.00562 0.00092 -0.0678 0.5897 0.6888 1.250 0.4427 0.00594 0.00100 -0.0673 0.5295 0.6959 1.500 0.4682 0.00624 0.00112 -0.0669 0.4806 0.7031 1.750 0.4937 0.00656 0.00125 -0.0665 0.4295 0.7097 2.000 0.5189 0.00691 0.00139 -0.0661 0.3778 0.7173 2.250 0.5452 0.00714 0.00150 -0.0659 0.3445 0.7244 2.500 0.5716 0.00735 0.00162 -0.0656 0.3171 0.7319 2.750 0.5986 0.00748 0.00172 -0.0655 0.3017 0.7397 3.000 0.6256 0.00762 0.00184 -0.0653 0.2868 0.7489 3.250 0.6523 0.00776 0.00196 -0.0651 0.2711 0.7582 3.500 0.6786 0.00796 0.00210 -0.0649 0.2491 0.7681 3.750 0.7034 0.00831 0.00230 -0.0644 0.2066 0.7799 4.000 0.7278 0.00869 0.00254 -0.0639 0.1653 0.7934 4.250 0.7523 0.00905 0.00279 -0.0634 0.1325 0.8082 4.500 0.7768 0.00940 0.00304 -0.0629 0.1048 0.8241 4.750 0.8017 0.00967 0.00328 -0.0624 0.0859 0.8412 5.000 0.8266 0.00990 0.00351 -0.0618 0.0736 0.8593 5.250 0.8513 0.01011 0.00374 -0.0613 0.0647 0.8795 5.500 0.8751 0.01029 0.00396 -0.0605 0.0575 0.9048 5.750 0.9047 0.01040 0.00418 -0.0609 0.0517 0.9728 6.000 0.9305 0.01071 0.00445 -0.0607 0.0438 1.0000 6.250 0.9559 0.01103 0.00472 -0.0603 0.0361 1.0000 6.500 0.9809 0.01138 0.00503 -0.0600 0.0291 1.0000 6.750 1.0060 0.01172 0.00534 -0.0596 0.0246 1.0000 7.000 1.0308 0.01207 0.00569 -0.0592 0.0220 1.0000 7.250 1.0556 0.01242 0.00604 -0.0587 0.0200 1.0000 7.500 1.0805 0.01273 0.00638 -0.0583 0.0191 1.0000 7.750 1.1051 0.01308 0.00675 -0.0579 0.0183 1.0000 8.000 1.1293 0.01346 0.00715 -0.0574 0.0173 1.0000 8.250 1.1529 0.01388 0.00758 -0.0568 0.0163 1.0000 8.500 1.1759 0.01436 0.00810 -0.0561 0.0154 1.0000 8.750 1.1998 0.01472 0.00850 -0.0556 0.0149 1.0000 9.000 1.2233 0.01510 0.00892 -0.0551 0.0144 1.0000 9.250 1.2464 0.01551 0.00938 -0.0544 0.0139 1.0000 9.500 1.2690 0.01594 0.00985 -0.0537 0.0133 1.0000 9.750 1.2912 0.01640 0.01033 -0.0530 0.0127 1.0000 10.000 1.3125 0.01693 0.01088 -0.0522 0.0120 1.0000 10.250 1.3327 0.01753 0.01153 -0.0512 0.0113 1.0000 10.500 1.3542 0.01797 0.01203 -0.0503 0.0110 1.0000 10.750 1.3749 0.01845 0.01257 -0.0494 0.0106 1.0000 11.000 1.3950 0.01895 0.01312 -0.0484 0.0101 1.0000 11.250 1.4144 0.01948 0.01370 -0.0473 0.0096 1.0000 11.500 1.4329 0.02005 0.01430 -0.0462 0.0091 1.0000 11.750 1.4499 0.02070 0.01498 -0.0448 0.0085 1.0000 12.000 1.4649 0.02132 0.01566 -0.0430 0.0082 1.0000 12.250 1.4786 0.02192 0.01634 -0.0410 0.0078 1.0000 12.500 1.4913 0.02257 0.01705 -0.0390 0.0074 1.0000 12.750 1.5029 0.02330 0.01785 -0.0369 0.0071 1.0000 13.000 1.5140 0.02409 0.01869 -0.0349 0.0067 1.0000 13.250 1.5239 0.02499 0.01964 -0.0328 0.0064 1.0000 13.500 1.5320 0.02605 0.02077 -0.0308 0.0060 1.0000 13.750 1.5400 0.02714 0.02195 -0.0289 0.0059 1.0000 14.000 1.5477 0.02830 0.02320 -0.0271 0.0057 1.0000 14.250 1.5543 0.02961 0.02460 -0.0254 0.0055 1.0000 14.500 1.5602 0.03102 0.02612 -0.0238 0.0054 1.0000 14.750 1.5647 0.03261 0.02781 -0.0223 0.0052 1.0000 15.000 1.5682 0.03438 0.02967 -0.0210 0.0050 1.0000 15.250 1.5711 0.03627 0.03166 -0.0199 0.0049 1.0000 15.500 1.5722 0.03844 0.03392 -0.0189 0.0048 1.0000 15.750 1.5722 0.04082 0.03641 -0.0182 0.0046 1.0000 16.000 1.5701 0.04354 0.03923 -0.0178 0.0045 1.0000 16.250 1.5663 0.04661 0.04242 -0.0176 0.0043 1.0000 16.500 1.5600 0.05017 0.04609 -0.0179 0.0043 1.0000 16.750 1.5496 0.05450 0.05056 -0.0187 0.0041 1.0000 17.000 1.5382 0.05933 0.05554 -0.0202 0.0041 1.0000 17.250 1.5248 0.06490 0.06126 -0.0224 0.0040 1.0000 17.500 1.5102 0.07117 0.06768 -0.0255 0.0040 1.0000 17.750 1.4942 0.07810 0.07477 -0.0291 0.0040 1.0000 18.000 1.4703 0.08687 0.08370 -0.0340 0.0040 1.0000 18.250 1.4459 0.09606 0.09306 -0.0393 0.0040 1.0000 18.500 1.4137 0.10706 0.10424 -0.0457 0.0040 1.0000 18.750 1.3832 0.11806 0.11541 -0.0522 0.0041 1.0000 19.000 1.3508 0.12981 0.12733 -0.0592 0.0041 1.0000 19.250 1.3207 0.14150 0.13917 -0.0663 0.0042 1.0000