XFOIL Version 6.96 Calculated polar for: GOE 626 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.7819 0.12369 0.12084 -0.0577 1.0000 0.0245 -19.500 -0.7921 0.11876 0.11583 -0.0602 1.0000 0.0247 -19.250 -0.7960 0.11486 0.11188 -0.0621 1.0000 0.0249 -19.000 -0.7955 0.11171 0.10871 -0.0635 1.0000 0.0250 -18.750 -0.7985 0.10796 0.10492 -0.0653 1.0000 0.0252 -18.500 -0.8006 0.10439 0.10131 -0.0670 1.0000 0.0253 -18.250 -0.8012 0.10118 0.09806 -0.0684 1.0000 0.0254 -18.000 -0.8022 0.09785 0.09469 -0.0699 1.0000 0.0256 -17.750 -0.8051 0.09426 0.09106 -0.0715 1.0000 0.0258 -17.500 -0.8060 0.09110 0.08786 -0.0728 1.0000 0.0259 -17.250 -0.8065 0.08809 0.08481 -0.0740 1.0000 0.0260 -17.000 -0.8092 0.08468 0.08136 -0.0755 1.0000 0.0263 -16.750 -0.8082 0.08206 0.07870 -0.0763 1.0000 0.0264 -16.500 -0.8077 0.07942 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3.000 0.9231 0.00983 0.00324 -0.1327 0.3890 0.2957 3.250 0.9487 0.00994 0.00333 -0.1320 0.3828 0.2973 3.500 0.9737 0.01007 0.00343 -0.1313 0.3764 0.2991 3.750 0.9998 0.01015 0.00352 -0.1308 0.3703 0.3009 4.000 1.0245 0.01029 0.00362 -0.1300 0.3630 0.3024 4.250 1.0494 0.01041 0.00374 -0.1293 0.3559 0.3037 4.500 1.0743 0.01054 0.00385 -0.1286 0.3485 0.3048 4.750 1.0979 0.01068 0.00396 -0.1276 0.3416 0.3078 5.000 1.1231 0.01074 0.00406 -0.1270 0.3364 0.3112 5.250 1.1467 0.01088 0.00420 -0.1260 0.3291 0.3139 5.500 1.1691 0.01104 0.00434 -0.1248 0.3224 0.3163 5.750 1.1920 0.01116 0.00447 -0.1237 0.3155 0.3187 6.000 1.2124 0.01137 0.00463 -0.1222 0.3065 0.3209 6.250 1.2348 0.01151 0.00478 -0.1210 0.2985 0.3228 6.500 1.2549 0.01175 0.00498 -0.1195 0.2889 0.3256 6.750 1.2758 0.01195 0.00517 -0.1181 0.2785 0.3299 7.000 1.2953 0.01222 0.00542 -0.1165 0.2660 0.3336 7.250 1.3132 0.01258 0.00571 -0.1147 0.2495 0.3374 7.500 1.3276 0.01311 0.00610 -0.1123 0.2261 0.3407 7.750 1.3377 0.01382 0.00664 -0.1092 0.1954 0.3442 8.000 1.3507 0.01439 0.00713 -0.1067 0.1782 0.3508 8.250 1.3656 0.01486 0.00756 -0.1046 0.1684 0.3574 8.500 1.3827 0.01524 0.00796 -0.1028 0.1623 0.3667 8.750 1.3996 0.01561 0.00836 -0.1010 0.1576 0.3796 9.250 1.4326 0.01634 0.00926 -0.0974 0.1488 0.4457 9.500 1.4495 0.01661 0.00972 -0.0957 0.1452 0.5339 9.750 1.4699 0.01644 0.01036 -0.0950 0.1400 1.0000 10.000 1.4855 0.01694 0.01085 -0.0932 0.1346 1.0000 10.250 1.5001 0.01752 0.01139 -0.0913 0.1270 1.0000 10.500 1.5129 0.01819 0.01203 -0.0893 0.1173 1.0000 10.750 1.5101 0.01970 0.01331 -0.0854 0.0869 1.0000 11.000 1.5075 0.02129 0.01478 -0.0818 0.0701 1.0000 11.250 1.5148 0.02239 0.01587 -0.0795 0.0657 1.0000 11.500 1.5247 0.02338 0.01687 -0.0776 0.0632 1.0000 11.750 1.5336 0.02445 0.01797 -0.0757 0.0614 1.0000 12.000 1.5412 0.02566 0.01920 -0.0738 0.0596 1.0000 12.250 1.5491 0.02690 0.02047 -0.0720 0.0583 1.0000 12.500 1.5569 0.02820 0.02180 -0.0703 0.0573 1.0000 12.750 1.5669 0.02937 0.02302 -0.0690 0.0567 1.0000 13.000 1.5759 0.03067 0.02437 -0.0676 0.0562 1.0000 13.250 1.5834 0.03213 0.02588 -0.0663 0.0557 1.0000 13.500 1.5902 0.03370 0.02751 -0.0650 0.0550 1.0000 13.750 1.5964 0.03540 0.02926 -0.0639 0.0546 1.0000 14.000 1.6011 0.03730 0.03121 -0.0628 0.0542 1.0000 14.250 1.6052 0.03934 0.03331 -0.0619 0.0536 1.0000 14.500 1.6080 0.04160 0.03562 -0.0611 0.0530 1.0000 14.750 1.6095 0.04407 0.03816 -0.0605 0.0525 1.0000 15.000 1.6093 0.04683 0.04098 -0.0599 0.0519 1.0000 15.250 1.6063 0.04998 0.04421 -0.0596 0.0512 1.0000 15.500 1.6049 0.05303 0.04734 -0.0594 0.0510 1.0000 15.750 1.6053 0.05592 0.05030 -0.0593 0.0506 1.0000 16.000 1.6077 0.05862 0.05307 -0.0592 0.0504 1.0000 16.250 1.6092 0.06146 0.05599 -0.0593 0.0502 1.0000 16.500 1.6090 0.06458 0.05919 -0.0594 0.0500 1.0000 16.750 1.6090 0.06772 0.06240 -0.0597 0.0496 1.0000 17.000 1.6081 0.07103 0.06578 -0.0601 0.0493 1.0000 17.250 1.6070 0.07441 0.06925 -0.0605 0.0490 1.0000 17.500 1.6045 0.07808 0.07299 -0.0612 0.0487 1.0000 17.750 1.6021 0.08177 0.07675 -0.0619 0.0484 1.0000 18.000 1.6008 0.08534 0.08039 -0.0627 0.0480 1.0000 18.250 1.5978 0.08922 0.08434 -0.0636 0.0476 1.0000 18.500 1.5944 0.09322 0.08842 -0.0647 0.0473 1.0000 18.750 1.5913 0.09720 0.09246 -0.0658 0.0468 1.0000 19.000 1.5871 0.10138 0.09671 -0.0671 0.0464 1.0000 19.250 1.5811 0.10589 0.10129 -0.0686 0.0459 1.0000