XFOIL Version 6.96 Calculated polar for: GOE 600 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.9027 0.13128 0.12919 -0.0020 1.0000 0.0096 -17.500 -0.9469 0.11778 0.11551 -0.0093 1.0000 0.0095 -17.250 -0.9827 0.10651 0.10409 -0.0153 1.0000 0.0094 -17.000 -1.0170 0.09587 0.09329 -0.0210 1.0000 0.0093 -16.750 -1.0477 0.08624 0.08353 -0.0263 1.0000 0.0093 -16.500 -1.0772 0.07731 0.07444 -0.0313 1.0000 0.0092 -16.250 -1.1022 0.06926 0.06624 -0.0359 1.0000 0.0092 -16.000 -1.1229 0.06205 0.05890 -0.0402 1.0000 0.0092 -15.750 -1.1398 0.05559 0.05230 -0.0442 1.0000 0.0093 -15.500 -1.1519 0.05001 0.04659 -0.0477 1.0000 0.0093 -15.250 -1.1597 0.04523 0.04168 -0.0507 1.0000 0.0094 -15.000 -1.1643 0.04104 0.03737 -0.0533 1.0000 0.0094 -14.750 -1.1659 0.03748 0.03368 -0.0554 1.0000 0.0095 -14.500 -1.1651 0.03451 0.03059 -0.0568 1.0000 0.0097 -14.250 -1.1632 0.03201 0.02798 -0.0575 1.0000 0.0098 -14.000 -1.1598 0.02998 0.02585 -0.0573 1.0000 0.0099 -13.750 -1.1555 0.02831 0.02407 -0.0564 1.0000 0.0101 -13.500 -1.1501 0.02694 0.02260 -0.0549 1.0000 0.0103 -13.250 -1.1437 0.02580 0.02136 -0.0528 1.0000 0.0104 -13.000 -1.1319 0.02476 0.02023 -0.0514 1.0000 0.0106 -12.750 -1.1169 0.02384 0.01922 -0.0503 1.0000 0.0108 -12.500 -1.0999 0.02302 0.01831 -0.0493 1.0000 0.0110 -12.250 -1.0865 0.02181 0.01699 -0.0480 1.0000 0.0112 -12.000 -1.0744 0.02044 0.01551 -0.0464 1.0000 0.0116 -11.750 -1.0565 0.01959 0.01462 -0.0454 1.0000 0.0120 -11.500 -1.0369 0.01893 0.01391 -0.0445 1.0000 0.0123 -11.250 -1.0176 0.01836 0.01329 -0.0435 1.0000 0.0127 -11.000 -1.0006 0.01786 0.01274 -0.0419 1.0000 0.0132 -10.750 -0.9732 0.01729 0.01211 -0.0424 0.9980 0.0136 -10.500 -0.9413 0.01676 0.01151 -0.0438 0.9955 0.0140 -10.250 -0.9135 0.01564 0.01031 -0.0447 0.9916 0.0149 -10.000 -0.8837 0.01504 0.00968 -0.0457 0.9864 0.0156 -9.750 -0.8531 0.01454 0.00914 -0.0467 0.9816 0.0164 -9.500 -0.8251 0.01411 0.00865 -0.0471 0.9740 0.0171 -9.250 -0.7989 0.01357 0.00805 -0.0470 0.9660 0.0180 -9.000 -0.7747 0.01309 0.00754 -0.0465 0.9567 0.0194 -8.750 -0.7499 0.01278 0.00719 -0.0460 0.9476 0.0207 -8.500 -0.7255 0.01247 0.00681 -0.0454 0.9391 0.0220 -8.250 -0.7010 0.01204 0.00637 -0.0449 0.9305 0.0242 -8.000 -0.6754 0.01180 0.00608 -0.0445 0.9230 0.0261 -7.750 -0.6499 0.01142 0.00569 -0.0442 0.9149 0.0291 -7.500 -0.6236 0.01123 0.00546 -0.0439 0.9075 0.0319 -7.250 -0.5973 0.01091 0.00513 -0.0437 0.8993 0.0354 -7.000 -0.5706 0.01072 0.00491 -0.0435 0.8916 0.0384 -6.750 -0.5435 0.01049 0.00463 -0.0434 0.8831 0.0411 -6.500 -0.5168 0.01021 0.00433 -0.0432 0.8751 0.0448 -6.250 -0.4892 0.01003 0.00411 -0.0432 0.8662 0.0475 -6.000 -0.4620 0.00978 0.00382 -0.0432 0.8576 0.0513 -5.750 -0.4348 0.00953 0.00354 -0.0431 0.8480 0.0558 -5.500 -0.4071 0.00931 0.00329 -0.0431 0.8379 0.0614 -5.250 -0.3803 0.00895 0.00303 -0.0430 0.8275 0.0827 -5.000 -0.3526 0.00875 0.00288 -0.0431 0.8163 0.1072 -4.750 -0.3245 0.00860 0.00275 -0.0432 0.8053 0.1196 -4.500 -0.2962 0.00848 0.00261 -0.0433 0.7950 0.1277 -4.250 -0.2678 0.00840 0.00248 -0.0434 0.7851 0.1342 -4.000 -0.2392 0.00830 0.00235 -0.0436 0.7759 0.1403 -3.750 -0.2108 0.00819 0.00222 -0.0438 0.7676 0.1475 -3.500 -0.1821 0.00809 0.00211 -0.0440 0.7590 0.1552 -3.250 -0.1538 0.00797 0.00198 -0.0441 0.7506 0.1676 -3.000 -0.1260 0.00768 0.00182 -0.0443 0.7422 0.2060 -2.750 -0.0989 0.00724 0.00168 -0.0444 0.7352 0.2934 -2.500 -0.0707 0.00702 0.00160 -0.0446 0.7285 0.3396 -2.250 -0.0425 0.00687 0.00153 -0.0448 0.7220 0.3795 -2.000 -0.0137 0.00671 0.00148 -0.0451 0.7160 0.4132 -1.750 0.0148 0.00657 0.00144 -0.0453 0.7099 0.4512 -1.500 0.0433 0.00646 0.00142 -0.0455 0.7042 0.4878 -1.250 0.0723 0.00636 0.00141 -0.0457 0.6983 0.5180 -1.000 0.1011 0.00632 0.00140 -0.0459 0.6928 0.5408 -0.750 0.1302 0.00629 0.00139 -0.0462 0.6880 0.5592 -0.500 0.1595 0.00624 0.00139 -0.0465 0.6829 0.5757 -0.250 0.1885 0.00623 0.00139 -0.0467 0.6778 0.5914 0.000 0.2175 0.00620 0.00140 -0.0469 0.6727 0.6092 0.250 0.2467 0.00615 0.00141 -0.0472 0.6674 0.6256 0.500 0.2756 0.00613 0.00141 -0.0474 0.6618 0.6429 0.750 0.3045 0.00610 0.00143 -0.0477 0.6559 0.6620 1.000 0.3332 0.00605 0.00144 -0.0478 0.6467 0.6849 1.250 0.3617 0.00599 0.00146 -0.0479 0.6361 0.7112 1.500 0.3899 0.00596 0.00148 -0.0480 0.6275 0.7405 1.750 0.4182 0.00587 0.00153 -0.0480 0.6203 0.7763 2.000 0.4455 0.00581 0.00158 -0.0479 0.6115 0.8166 2.250 0.4720 0.00574 0.00164 -0.0474 0.5996 0.8618 2.500 0.4974 0.00570 0.00171 -0.0467 0.5873 0.9051 2.750 0.5227 0.00571 0.00177 -0.0459 0.5743 0.9394 3.000 0.5513 0.00578 0.00183 -0.0459 0.5570 0.9630 3.250 0.5838 0.00593 0.00189 -0.0469 0.5319 0.9792 3.500 0.6184 0.00621 0.00200 -0.0486 0.4875 0.9901 3.750 0.6545 0.00661 0.00218 -0.0507 0.4391 0.9964 4.000 0.6891 0.00694 0.00237 -0.0525 0.4056 1.0000 4.250 0.7126 0.00722 0.00252 -0.0518 0.3781 1.0000 4.500 0.7367 0.00747 0.00267 -0.0511 0.3542 1.0000 4.750 0.7613 0.00772 0.00282 -0.0506 0.3318 1.0000 5.000 0.7861 0.00798 0.00299 -0.0502 0.3089 1.0000 5.250 0.8113 0.00825 0.00317 -0.0498 0.2872 1.0000 5.500 0.8364 0.00854 0.00336 -0.0495 0.2644 1.0000 5.750 0.8612 0.00888 0.00359 -0.0491 0.2388 1.0000 6.000 0.8855 0.00926 0.00384 -0.0486 0.2115 1.0000 6.500 0.9342 0.01003 0.00439 -0.0478 0.1656 1.0000 6.750 0.9580 0.01046 0.00470 -0.0473 0.1434 1.0000 7.000 0.9816 0.01090 0.00502 -0.0468 0.1197 1.0000 7.250 1.0042 0.01144 0.00541 -0.0461 0.0957 1.0000 7.500 1.0278 0.01185 0.00576 -0.0456 0.0840 1.0000 7.750 1.0519 0.01222 0.00610 -0.0451 0.0757 1.0000 8.000 1.0753 0.01264 0.00647 -0.0445 0.0650 1.0000 8.250 1.0949 0.01337 0.00700 -0.0434 0.0393 1.0000 8.500 1.1159 0.01396 0.00754 -0.0425 0.0314 1.0000 8.750 1.1385 0.01439 0.00799 -0.0418 0.0290 1.0000 9.000 1.1592 0.01496 0.00856 -0.0408 0.0262 1.0000 9.250 1.1809 0.01542 0.00906 -0.0400 0.0246 1.0000 9.500 1.2025 0.01586 0.00953 -0.0392 0.0230 1.0000 9.750 1.2215 0.01647 0.01015 -0.0380 0.0212 1.0000 10.000 1.2405 0.01704 0.01077 -0.0368 0.0200 1.0000 10.250 1.2603 0.01750 0.01126 -0.0357 0.0190 1.0000 10.500 1.2782 0.01801 0.01180 -0.0343 0.0180 1.0000 10.750 1.2919 0.01867 0.01249 -0.0323 0.0171 1.0000 11.000 1.3025 0.01955 0.01343 -0.0299 0.0162 1.0000 11.250 1.3192 0.02010 0.01402 -0.0285 0.0156 1.0000 11.500 1.3347 0.02074 0.01471 -0.0271 0.0150 1.0000 11.750 1.3497 0.02144 0.01544 -0.0257 0.0143 1.0000 12.000 1.3626 0.02231 0.01635 -0.0242 0.0138 1.0000 12.250 1.3697 0.02362 0.01773 -0.0221 0.0131 1.0000 12.500 1.3796 0.02479 0.01897 -0.0205 0.0127 1.0000 12.750 1.3923 0.02578 0.02003 -0.0193 0.0124 1.0000 13.000 1.4036 0.02691 0.02122 -0.0181 0.0121 1.0000 13.250 1.4141 0.02813 0.02251 -0.0170 0.0117 1.0000 13.500 1.4239 0.02945 0.02388 -0.0159 0.0114 1.0000 13.750 1.4327 0.03089 0.02540 -0.0149 0.0111 1.0000 14.000 1.4395 0.03256 0.02713 -0.0139 0.0108 1.0000 14.250 1.4421 0.03467 0.02931 -0.0128 0.0105 1.0000 14.500 1.4370 0.03761 0.03235 -0.0117 0.0102 1.0000 14.750 1.4377 0.04007 0.03491 -0.0110 0.0100 1.0000 15.000 1.4435 0.04208 0.03701 -0.0106 0.0099 1.0000 15.250 1.4474 0.04434 0.03936 -0.0103 0.0097 1.0000 15.500 1.4499 0.04679 0.04190 -0.0101 0.0095 1.0000 15.750 1.4504 0.04952 0.04473 -0.0100 0.0093 1.0000 16.000 1.4500 0.05247 0.04777 -0.0100 0.0091 1.0000 16.250 1.4480 0.05573 0.05113 -0.0103 0.0090 1.0000 16.500 1.4449 0.05921 0.05471 -0.0108 0.0089 1.0000 16.750 1.4407 0.06297 0.05856 -0.0115 0.0087 1.0000 17.000 1.4348 0.06710 0.06280 -0.0125 0.0086 1.0000 17.250 1.4276 0.07156 0.06736 -0.0137 0.0085 1.0000 17.500 1.4192 0.07630 0.07221 -0.0152 0.0084 1.0000 17.750 1.4084 0.08159 0.07760 -0.0170 0.0084 1.0000 18.000 1.3966 0.08717 0.08330 -0.0191 0.0083 1.0000 18.250 1.3831 0.09308 0.08932 -0.0214 0.0082 1.0000 18.500 1.3683 0.09929 0.09563 -0.0239 0.0081 1.0000 18.750 1.3529 0.10568 0.10213 -0.0266 0.0081 1.0000 19.000 1.3373 0.11220 0.10876 -0.0294 0.0080 1.0000