XFOIL Version 6.96 Calculated polar for: NYU/GRUMMAN K-1 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.9911 0.11130 0.10901 -0.0137 1.0000 0.0150 -17.000 -1.0388 0.09733 0.09480 -0.0221 1.0000 0.0149 -16.750 -1.0651 0.08818 0.08548 -0.0276 1.0000 0.0149 -16.500 -1.0839 0.08066 0.07782 -0.0323 1.0000 0.0149 -16.250 -1.0990 0.07408 0.07110 -0.0365 1.0000 0.0150 -16.000 -1.1101 0.06836 0.06526 -0.0400 1.0000 0.0151 -15.750 -1.1195 0.06314 0.05991 -0.0433 1.0000 0.0152 -15.500 -1.1270 0.05847 0.05512 -0.0461 1.0000 0.0153 -15.250 -1.1328 0.05427 0.05081 -0.0486 1.0000 0.0154 -15.000 -1.1367 0.05043 0.04685 -0.0508 1.0000 0.0155 -14.750 -1.1387 0.04696 0.04325 -0.0527 1.0000 0.0156 -14.500 -1.1386 0.04379 0.03996 -0.0545 1.0000 0.0158 -14.250 -1.1364 0.04093 0.03699 -0.0560 1.0000 0.0159 -14.000 -1.1317 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0.8057 0.5988 0.250 0.3278 0.00526 0.00126 -0.0859 0.7945 0.6051 0.500 0.3570 0.00526 0.00128 -0.0860 0.7829 0.6121 0.750 0.3859 0.00530 0.00130 -0.0861 0.7686 0.6186 1.000 0.4147 0.00537 0.00131 -0.0861 0.7474 0.6242 1.250 0.4427 0.00551 0.00133 -0.0859 0.7073 0.6296 1.500 0.4695 0.00582 0.00143 -0.0856 0.6542 0.6351 1.750 0.4925 0.00675 0.00171 -0.0849 0.4892 0.6402 2.000 0.5170 0.00752 0.00198 -0.0845 0.3711 0.6448 2.250 0.5427 0.00809 0.00221 -0.0843 0.2876 0.6492 2.500 0.5687 0.00857 0.00243 -0.0841 0.2222 0.6543 2.750 0.5956 0.00892 0.00262 -0.0840 0.1844 0.6589 3.000 0.6231 0.00920 0.00279 -0.0839 0.1630 0.6635 3.250 0.6508 0.00944 0.00295 -0.0839 0.1474 0.6673 3.500 0.6785 0.00963 0.00310 -0.0838 0.1356 0.6719 3.750 0.7063 0.00981 0.00327 -0.0838 0.1263 0.6764 4.000 0.7340 0.01000 0.00344 -0.0837 0.1184 0.6806 4.250 0.7616 0.01021 0.00362 -0.0836 0.1110 0.6847 4.500 0.7891 0.01044 0.00381 -0.0835 0.1034 0.6882 4.750 0.8166 0.01062 0.00398 -0.0834 0.0931 0.6926 5.000 0.8434 0.01090 0.00419 -0.0832 0.0790 0.6966 5.250 0.8687 0.01139 0.00453 -0.0829 0.0518 0.7006 5.500 0.8940 0.01189 0.00493 -0.0825 0.0356 0.7045 5.750 0.9201 0.01228 0.00529 -0.0821 0.0302 0.7078 6.000 0.9464 0.01261 0.00562 -0.0818 0.0274 0.7118 6.250 0.9728 0.01291 0.00594 -0.0815 0.0256 0.7159 6.500 0.9989 0.01326 0.00631 -0.0812 0.0243 0.7197 6.750 1.0250 0.01359 0.00666 -0.0808 0.0233 0.7234 7.000 1.0506 0.01398 0.00704 -0.0804 0.0223 0.7269 7.250 1.0759 0.01439 0.00749 -0.0800 0.0214 0.7307 7.500 1.1015 0.01472 0.00785 -0.0796 0.0204 0.7347 7.750 1.1264 0.01514 0.00830 -0.0791 0.0194 0.7384 8.000 1.1506 0.01566 0.00886 -0.0786 0.0186 0.7422 8.250 1.1756 0.01606 0.00929 -0.0781 0.0179 0.7460 8.500 1.2001 0.01650 0.00977 -0.0775 0.0173 0.7498 8.750 1.2236 0.01702 0.01034 -0.0769 0.0167 0.7539 9.000 1.2447 0.01785 0.01122 -0.0759 0.0161 0.7577 9.250 1.2688 0.01826 0.01170 -0.0753 0.0157 0.7619 9.500 1.2920 0.01877 0.01225 -0.0746 0.0153 0.7658 9.750 1.3147 0.01928 0.01284 -0.0738 0.0149 0.7703 10.000 1.3368 0.01983 0.01345 -0.0730 0.0145 0.7748 10.250 1.3583 0.02042 0.01408 -0.0721 0.0142 0.7794 10.500 1.3780 0.02117 0.01487 -0.0710 0.0139 0.7839 10.750 1.3936 0.02229 0.01608 -0.0693 0.0135 0.7892 11.000 1.4148 0.02278 0.01666 -0.0683 0.0133 0.7949 11.250 1.4349 0.02335 0.01732 -0.0673 0.0131 0.8005 11.500 1.4539 0.02397 0.01803 -0.0660 0.0128 0.8067 11.750 1.4721 0.02461 0.01877 -0.0647 0.0125 0.8145 12.000 1.4884 0.02521 0.01946 -0.0631 0.0121 0.8235 12.250 1.5037 0.02581 0.02014 -0.0614 0.0119 0.8358 12.500 1.5189 0.02640 0.02083 -0.0597 0.0116 0.8553 12.750 1.5243 0.02703 0.02171 -0.0564 0.0113 1.0000 13.000 1.5307 0.02838 0.02314 -0.0539 0.0110 1.0000 13.250 1.5476 0.02897 0.02380 -0.0527 0.0108 1.0000 13.500 1.5611 0.02981 0.02472 -0.0511 0.0105 1.0000 13.750 1.5730 0.03078 0.02577 -0.0495 0.0102 1.0000 14.000 1.5859 0.03168 0.02673 -0.0480 0.0099 1.0000 14.250 1.5975 0.03270 0.02781 -0.0465 0.0097 1.0000 14.500 1.6070 0.03391 0.02908 -0.0450 0.0095 1.0000 14.750 1.6158 0.03519 0.03043 -0.0435 0.0093 1.0000 15.000 1.6212 0.03682 0.03213 -0.0419 0.0091 1.0000 15.250 1.6220 0.03890 0.03429 -0.0402 0.0089 1.0000 15.500 1.6170 0.04162 0.03713 -0.0385 0.0087 1.0000 15.750 1.6182 0.04388 0.03951 -0.0373 0.0086 1.0000 16.000 1.6172 0.04646 0.04221 -0.0364 0.0085 1.0000 16.250 1.6136 0.04947 0.04535 -0.0358 0.0084 1.0000 16.500 1.6083 0.05285 0.04886 -0.0356 0.0083 1.0000 16.750 1.5978 0.05715 0.05330 -0.0360 0.0083 1.0000 17.000 1.5881 0.06167 0.05796 -0.0370 0.0082 1.0000 17.250 1.5730 0.06745 0.06389 -0.0390 0.0081 1.0000 17.500 1.5496 0.07532 0.07195 -0.0428 0.0081 1.0000 17.750 1.5215 0.08493 0.08175 -0.0482 0.0081 1.0000 18.000 1.4722 0.09940 0.09648 -0.0566 0.0082 1.0000 18.250 1.4183 0.11469 0.11200 -0.0652 0.0083 1.0000