XFOIL Version 6.96 Calculated polar for: GOE 795 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.9779 0.03496 0.03267 -0.0602 1.0000 0.0019 -12.000 -0.9878 0.03046 0.02783 -0.0581 1.0000 0.0019 -11.750 -0.9860 0.02766 0.02477 -0.0560 1.0000 0.0019 -11.500 -0.9793 0.02554 0.02242 -0.0538 1.0000 0.0020 -11.250 -0.9707 0.02366 0.02031 -0.0517 1.0000 0.0020 -11.000 -0.9520 0.02204 0.01848 -0.0512 0.9994 0.0021 -10.750 -0.9258 0.02057 0.01681 -0.0522 0.9979 0.0022 -10.500 -0.8987 0.01923 0.01526 -0.0531 0.9961 0.0024 -10.250 -0.8702 0.01822 0.01412 -0.0541 0.9946 0.0027 -10.000 -0.8423 0.01742 0.01326 -0.0547 0.9930 0.0033 -9.750 -0.8092 0.01834 0.01450 -0.0557 0.9920 0.0041 -9.500 -0.7839 0.01739 0.01336 -0.0557 0.9898 0.0056 -9.250 -0.7565 0.01676 0.01261 -0.0561 0.9877 0.0060 -9.000 -0.7271 0.01644 0.01224 -0.0567 0.9859 0.0065 -8.750 -0.6966 0.01626 0.01202 -0.0575 0.9843 0.0067 -8.500 -0.6644 0.01645 0.01224 -0.0585 0.9831 0.0069 -8.250 -0.6364 0.01585 0.01154 -0.0590 0.9811 0.0072 -8.000 -0.6141 0.01491 0.01045 -0.0582 0.9764 0.0072 -7.750 -0.5884 0.01387 0.00925 -0.0583 0.9730 0.0077 -7.500 -0.5589 0.01346 0.00881 -0.0589 0.9706 0.0082 -7.250 -0.5314 0.01277 0.00799 -0.0591 0.9677 0.0082 -7.000 -0.5057 0.01231 0.00747 -0.0588 0.9625 0.0085 -6.750 -0.4754 0.01194 0.00703 -0.0595 0.9593 0.0089 -6.500 -0.4437 0.01132 0.00629 -0.0605 0.9568 0.0089 -6.250 -0.4119 0.01097 0.00590 -0.0616 0.9534 0.0094 -6.000 -0.3793 0.01060 0.00548 -0.0627 0.9494 0.0099 -5.750 -0.3451 0.01023 0.00506 -0.0643 0.9454 0.0104 -5.500 -0.3113 0.00972 0.00446 -0.0657 0.9408 0.0105 -5.250 -0.2801 0.00930 0.00393 -0.0665 0.9338 0.0106 -5.000 -0.2482 0.00893 0.00347 -0.0674 0.9267 0.0107 -4.750 -0.2189 0.00864 0.00310 -0.0677 0.9173 0.0108 -4.500 -0.1907 0.00839 0.00277 -0.0677 0.9072 0.0110 -4.250 -0.1631 0.00818 0.00249 -0.0676 0.8962 0.0112 -4.000 -0.1360 0.00802 0.00224 -0.0674 0.8844 0.0114 -3.750 -0.1096 0.00786 0.00201 -0.0670 0.8709 0.0119 -3.500 -0.0838 0.00773 0.00178 -0.0664 0.8547 0.0130 -3.250 -0.0585 0.00764 0.00161 -0.0658 0.8353 0.0147 -3.000 -0.0336 0.00756 0.00147 -0.0650 0.8161 0.0166 -2.750 -0.0090 0.00745 0.00133 -0.0643 0.7968 0.0243 -2.250 0.0407 0.00737 0.00114 -0.0628 0.7596 0.0349 -2.000 0.0659 0.00735 0.00106 -0.0622 0.7430 0.0389 -1.750 0.0910 0.00729 0.00098 -0.0615 0.7281 0.0498 -1.500 0.1156 0.00715 0.00093 -0.0608 0.7140 0.0849 -1.250 0.1411 0.00711 0.00088 -0.0603 0.7016 0.0978 -1.000 0.1669 0.00705 0.00084 -0.0598 0.6916 0.1135 -0.750 0.1929 0.00701 0.00080 -0.0594 0.6820 0.1239 -0.500 0.2189 0.00693 0.00077 -0.0590 0.6735 0.1470 -0.250 0.2442 0.00685 0.00076 -0.0584 0.6620 0.1852 0.000 0.2690 0.00685 0.00075 -0.0577 0.6409 0.2064 0.250 0.2937 0.00680 0.00075 -0.0571 0.6225 0.2444 0.500 0.3176 0.00669 0.00076 -0.0563 0.6023 0.3064 0.750 0.3397 0.00645 0.00078 -0.0552 0.5812 0.4253 1.000 0.3591 0.00612 0.00082 -0.0535 0.5547 0.5854 1.250 0.3781 0.00593 0.00087 -0.0517 0.5229 0.7032 1.500 0.3948 0.00575 0.00094 -0.0491 0.4894 0.8193 2.000 0.5130 0.00667 0.00145 -0.0640 0.3142 0.9834 2.250 0.5477 0.00702 0.00161 -0.0657 0.2725 0.9935 2.500 0.5931 0.00742 0.00174 -0.0700 0.2132 0.9993 2.750 0.6181 0.00785 0.00192 -0.0697 0.1595 1.0000 3.000 0.6407 0.00807 0.00207 -0.0686 0.1404 1.0000 3.250 0.6629 0.00833 0.00223 -0.0675 0.1162 1.0000 3.500 0.6849 0.00862 0.00240 -0.0663 0.0904 1.0000 3.750 0.7070 0.00891 0.00258 -0.0651 0.0676 1.0000 4.000 0.7290 0.00920 0.00278 -0.0640 0.0508 1.0000 4.250 0.7524 0.00938 0.00296 -0.0631 0.0485 1.0000 4.500 0.7757 0.00957 0.00314 -0.0621 0.0463 1.0000 4.750 0.7989 0.00978 0.00334 -0.0612 0.0426 1.0000 5.000 0.8221 0.00998 0.00356 -0.0602 0.0407 1.0000 5.250 0.8457 0.01016 0.00376 -0.0594 0.0403 1.0000 5.500 0.8693 0.01033 0.00396 -0.0585 0.0392 1.0000 5.750 0.8924 0.01054 0.00420 -0.0576 0.0354 1.0000 6.000 0.9146 0.01083 0.00447 -0.0565 0.0304 1.0000 6.250 0.9377 0.01104 0.00470 -0.0556 0.0284 1.0000 6.500 0.9579 0.01148 0.00501 -0.0542 0.0137 1.0000 6.750 0.9787 0.01189 0.00540 -0.0529 0.0083 1.0000 7.000 0.9996 0.01228 0.00580 -0.0516 0.0062 1.0000 7.250 1.0205 0.01267 0.00624 -0.0503 0.0047 1.0000 7.500 1.0418 0.01302 0.00662 -0.0491 0.0039 1.0000 7.750 1.0620 0.01346 0.00708 -0.0477 0.0032 1.0000 8.000 1.0817 0.01395 0.00763 -0.0462 0.0028 1.0000 8.250 1.1018 0.01439 0.00813 -0.0448 0.0026 1.0000 8.500 1.1219 0.01483 0.00862 -0.0435 0.0025 1.0000 8.750 1.1414 0.01532 0.00916 -0.0420 0.0024 1.0000 9.000 1.1610 0.01578 0.00967 -0.0406 0.0022 1.0000 9.250 1.1791 0.01636 0.01035 -0.0390 0.0022 1.0000 9.500 1.1973 0.01692 0.01096 -0.0374 0.0020 1.0000 9.750 1.2147 0.01753 0.01165 -0.0357 0.0019 1.0000 10.000 1.2321 0.01812 0.01230 -0.0340 0.0018 1.0000 10.250 1.2487 0.01875 0.01300 -0.0323 0.0017 1.0000 10.500 1.2641 0.01945 0.01377 -0.0304 0.0017 1.0000 10.750 1.2788 0.02019 0.01458 -0.0284 0.0016 1.0000 11.000 1.2881 0.02118 0.01567 -0.0254 0.0014 1.0000 11.250 1.2899 0.02253 0.01720 -0.0214 0.0013 1.0000 11.500 1.2945 0.02376 0.01857 -0.0180 0.0013 1.0000 11.750 1.3040 0.02465 0.01957 -0.0155 0.0012 1.0000 12.000 1.3087 0.02594 0.02100 -0.0126 0.0012 1.0000 12.250 1.3164 0.02703 0.02219 -0.0103 0.0012 1.0000 12.500 1.3193 0.02853 0.02383 -0.0076 0.0012 1.0000 12.750 1.3288 0.02955 0.02494 -0.0059 0.0012 1.0000 13.000 1.3256 0.03167 0.02723 -0.0034 0.0012 1.0000 13.250 1.3295 0.03329 0.02897 -0.0017 0.0012 1.0000 13.500 1.3303 0.03529 0.03111 -0.0002 0.0011 1.0000 13.750 1.3243 0.03809 0.03407 0.0012 0.0011 1.0000 14.000 1.3192 0.04102 0.03716 0.0020 0.0011 1.0000 14.250 1.3135 0.04423 0.04052 0.0023 0.0011 1.0000 14.500 1.3071 0.04777 0.04420 0.0020 0.0011 1.0000 14.750 1.2950 0.05227 0.04888 0.0012 0.0011 1.0000 15.000 1.2851 0.05682 0.05356 -0.0003 0.0011 1.0000 15.250 1.2664 0.06307 0.05999 -0.0028 0.0011 1.0000 15.500 1.2509 0.06937 0.06644 -0.0058 0.0011 1.0000 15.750 1.2318 0.07681 0.07403 -0.0097 0.0011 1.0000 16.000 1.2084 0.08564 0.08302 -0.0145 0.0011 1.0000 16.250 1.1776 0.09630 0.09386 -0.0202 0.0011 1.0000 16.500 1.1467 0.10728 0.10497 -0.0259 0.0011 1.0000 16.750 1.1214 0.11726 0.11506 -0.0308 0.0011 1.0000 17.000 1.0854 0.13008 0.12801 -0.0370 0.0011 1.0000 17.250 1.0548 0.14190 0.13992 -0.0427 0.0012 1.0000