XFOIL Version 6.96 Calculated polar for: OAF117 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -1.2997 0.07607 0.07291 -0.0002 1.0000 0.0123 -16.000 -1.3692 0.06130 0.05792 -0.0096 1.0000 0.0122 -15.750 -1.4288 0.04765 0.04403 -0.0195 1.0000 0.0120 -15.500 -1.4612 0.03535 0.03143 -0.0338 1.0000 0.0120 -15.250 -1.4512 0.03188 0.02778 -0.0379 1.0000 0.0121 -15.000 -1.4359 0.02992 0.02569 -0.0392 1.0000 0.0123 -14.750 -1.4191 0.02807 0.02373 -0.0403 1.0000 0.0126 -14.500 -1.3994 0.02664 0.02222 -0.0409 1.0000 0.0129 -14.250 -1.3780 0.02544 0.02094 -0.0414 1.0000 0.0133 -14.000 -1.3553 0.02439 0.01982 -0.0418 1.0000 0.0136 -13.750 -1.3316 0.02344 0.01879 -0.0422 1.0000 0.0140 -13.500 -1.3072 0.02258 0.01786 -0.0425 1.0000 0.0143 -13.250 -1.2821 0.02180 0.01701 -0.0428 1.0000 0.0147 -13.000 -1.2566 0.02105 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1.250 0.4034 0.00860 0.00219 -0.0556 0.3712 0.3896 1.500 0.4332 0.00864 0.00224 -0.0558 0.3601 0.4047 1.750 0.4630 0.00869 0.00229 -0.0560 0.3488 0.4188 2.000 0.4927 0.00876 0.00235 -0.0562 0.3383 0.4317 2.250 0.5224 0.00882 0.00243 -0.0564 0.3267 0.4485 2.500 0.5521 0.00887 0.00251 -0.0566 0.3153 0.4687 2.750 0.5817 0.00894 0.00259 -0.0568 0.3045 0.4869 3.000 0.6113 0.00904 0.00269 -0.0570 0.2911 0.5037 3.250 0.6409 0.00913 0.00279 -0.0572 0.2792 0.5249 3.500 0.6705 0.00922 0.00291 -0.0575 0.2683 0.5482 3.750 0.7000 0.00931 0.00304 -0.0577 0.2570 0.5766 4.000 0.7294 0.00941 0.00318 -0.0579 0.2413 0.6125 4.250 0.7588 0.00957 0.00336 -0.0582 0.2173 0.6575 4.500 0.7879 0.00971 0.00356 -0.0585 0.1961 0.7171 4.750 0.8166 0.00980 0.00377 -0.0586 0.1784 0.7880 5.000 0.8409 0.00970 0.00394 -0.0576 0.1650 0.9096 5.250 0.8671 0.00978 0.00403 -0.0571 0.1522 1.0000 5.500 0.8960 0.01006 0.00424 -0.0572 0.1395 1.0000 5.750 0.9249 0.01036 0.00446 -0.0574 0.1269 1.0000 6.000 0.9536 0.01066 0.00469 -0.0576 0.1145 1.0000 6.250 0.9823 0.01095 0.00493 -0.0577 0.1034 1.0000 6.500 1.0107 0.01130 0.00521 -0.0579 0.0907 1.0000 6.750 1.0389 0.01168 0.00550 -0.0580 0.0786 1.0000 7.000 1.0671 0.01204 0.00580 -0.0581 0.0688 1.0000 7.250 1.0951 0.01242 0.00613 -0.0582 0.0600 1.0000 7.500 1.1230 0.01278 0.00645 -0.0582 0.0531 1.0000 7.750 1.1508 0.01314 0.00678 -0.0583 0.0479 1.0000 8.000 1.1784 0.01351 0.00713 -0.0583 0.0434 1.0000 8.250 1.2059 0.01387 0.00747 -0.0583 0.0398 1.0000 8.500 1.2333 0.01425 0.00784 -0.0583 0.0367 1.0000 8.750 1.2605 0.01461 0.00821 -0.0582 0.0343 1.0000 9.000 1.2874 0.01502 0.00860 -0.0582 0.0321 1.0000 9.250 1.3143 0.01538 0.00898 -0.0581 0.0306 1.0000 9.500 1.3408 0.01579 0.00940 -0.0580 0.0289 1.0000 9.750 1.3670 0.01624 0.00985 -0.0578 0.0273 1.0000 10.000 1.3933 0.01664 0.01027 -0.0577 0.0261 1.0000 10.250 1.4191 0.01708 0.01073 -0.0575 0.0249 1.0000 10.500 1.4444 0.01758 0.01123 -0.0572 0.0238 1.0000 10.750 1.4695 0.01807 0.01175 -0.0570 0.0229 1.0000 11.000 1.4945 0.01853 0.01225 -0.0567 0.0222 1.0000 11.250 1.5190 0.01904 0.01279 -0.0564 0.0215 1.0000 11.500 1.5429 0.01958 0.01336 -0.0560 0.0207 1.0000 11.750 1.5661 0.02019 0.01399 -0.0555 0.0200 1.0000 12.000 1.5886 0.02083 0.01467 -0.0550 0.0194 1.0000 12.250 1.6113 0.02140 0.01529 -0.0544 0.0190 1.0000 12.500 1.6331 0.02202 0.01595 -0.0538 0.0184 1.0000 12.750 1.6541 0.02269 0.01666 -0.0531 0.0179 1.0000 13.000 1.6740 0.02341 0.01744 -0.0523 0.0174 1.0000 13.250 1.6925 0.02421 0.01827 -0.0514 0.0170 1.0000 13.500 1.7091 0.02511 0.01922 -0.0503 0.0166 1.0000 13.750 1.7236 0.02609 0.02026 -0.0489 0.0162 1.0000 14.000 1.7371 0.02701 0.02125 -0.0474 0.0160 1.0000 14.250 1.7478 0.02805 0.02238 -0.0457 0.0158 1.0000 14.500 1.7513 0.02936 0.02377 -0.0432 0.0156 1.0000 14.750 1.7544 0.03104 0.02555 -0.0416 0.0154 1.0000 15.000 1.7579 0.03306 0.02766 -0.0408 0.0152 1.0000 15.250 1.7608 0.03542 0.03011 -0.0405 0.0150 1.0000 15.500 1.7626 0.03814 0.03293 -0.0408 0.0148 1.0000 15.750 1.7627 0.04124 0.03613 -0.0413 0.0146 1.0000 16.000 1.7608 0.04475 0.03974 -0.0422 0.0144 1.0000 16.250 1.7563 0.04869 0.04379 -0.0433 0.0142 1.0000 16.500 1.7486 0.05314 0.04834 -0.0447 0.0141 1.0000 16.750 1.7377 0.05809 0.05341 -0.0463 0.0140 1.0000 17.000 1.7234 0.06354 0.05898 -0.0481 0.0138 1.0000 17.250 1.7063 0.06947 0.06504 -0.0501 0.0138 1.0000 17.500 1.6862 0.07588 0.07158 -0.0523 0.0137 1.0000 17.750 1.6646 0.08274 0.07857 -0.0549 0.0136 1.0000 18.000 1.6424 0.08988 0.08584 -0.0577 0.0136 1.0000 18.250 1.6198 0.09731 0.09339 -0.0608 0.0135 1.0000 18.500 1.5965 0.10499 0.10120 -0.0641 0.0134 1.0000