XFOIL Version 6.96 Calculated polar for: S2062 8% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5030 0.08471 0.08129 -0.0327 1.0000 0.0522 -8.250 -0.5140 0.07948 0.07611 -0.0390 1.0000 0.0524 -8.000 -0.5214 0.07461 0.07115 -0.0431 1.0000 0.0525 -7.750 -0.5287 0.06795 0.06454 -0.0440 1.0000 0.0534 -7.500 -0.5211 0.06529 0.06193 -0.0419 1.0000 0.0544 -7.250 -0.5163 0.06251 0.05916 -0.0411 1.0000 0.0555 -7.000 -0.5130 0.05910 0.05571 -0.0413 1.0000 0.0566 -6.750 -0.5099 0.05537 0.05190 -0.0417 1.0000 0.0582 -6.500 -0.5062 0.05137 0.04776 -0.0420 1.0000 0.0603 -6.250 -0.5183 0.03406 0.02892 -0.0425 1.0000 0.0308 -6.000 -0.5040 0.03075 0.02541 -0.0411 1.0000 0.0284 -5.750 -0.4898 0.02676 0.02091 -0.0398 1.0000 0.0271 -5.500 -0.4717 0.02353 0.01715 -0.0384 1.0000 0.0262 -5.250 -0.4511 0.02110 0.01429 -0.0371 1.0000 0.0262 -5.000 -0.4292 0.01925 0.01213 -0.0359 1.0000 0.0267 -4.750 -0.4068 0.01797 0.01062 -0.0348 1.0000 0.0286 -4.500 -0.3844 0.01650 0.00900 -0.0339 1.0000 0.0318 -4.250 -0.3619 0.01549 0.00796 -0.0330 1.0000 0.0355 -4.000 -0.3383 0.01440 0.00676 -0.0321 1.0000 0.0424 -3.750 -0.3146 0.01340 0.00589 -0.0315 1.0000 0.0718 -3.500 -0.2916 0.01300 0.00552 -0.0309 1.0000 0.1045 -3.250 -0.2689 0.01263 0.00531 -0.0304 1.0000 0.1377 -3.000 -0.2460 0.01222 0.00502 -0.0298 1.0000 0.1754 -2.750 -0.2232 0.01176 0.00478 -0.0294 1.0000 0.2283 -2.500 -0.1993 0.01131 0.00467 -0.0292 0.9996 0.3079 -2.250 -0.1613 0.01079 0.00468 -0.0319 0.9950 0.4467 -2.000 -0.1280 0.01018 0.00478 -0.0332 0.9896 0.6223 -1.750 -0.0955 0.00995 0.00505 -0.0335 0.9841 0.7786 -1.500 -0.0666 0.00986 0.00514 -0.0329 0.9766 0.8721 -1.250 -0.0161 0.00981 0.00511 -0.0369 0.9738 0.9606 -1.000 0.0396 0.00983 0.00498 -0.0428 0.9710 1.0000 -0.750 0.0779 0.00983 0.00488 -0.0452 0.9628 1.0000 -0.500 0.1244 0.00982 0.00477 -0.0491 0.9576 1.0000 -0.250 0.1630 0.00978 0.00466 -0.0513 0.9491 1.0000 0.000 0.2107 0.00968 0.00452 -0.0553 0.9441 1.0000 0.250 0.2507 0.00956 0.00437 -0.0577 0.9355 1.0000 0.500 0.2956 0.00936 0.00416 -0.0609 0.9292 1.0000 0.750 0.3292 0.00922 0.00400 -0.0617 0.9180 1.0000 1.250 0.3925 0.00894 0.00373 -0.0624 0.8936 1.0000 1.500 0.4207 0.00883 0.00361 -0.0620 0.8792 1.0000 1.750 0.4475 0.00875 0.00352 -0.0612 0.8632 1.0000 2.000 0.4738 0.00869 0.00346 -0.0604 0.8459 1.0000 2.250 0.4991 0.00866 0.00343 -0.0593 0.8260 1.0000 2.500 0.5243 0.00866 0.00340 -0.0583 0.8037 1.0000 2.750 0.5492 0.00869 0.00340 -0.0572 0.7781 1.0000 3.000 0.5740 0.00876 0.00342 -0.0561 0.7496 1.0000 3.250 0.5986 0.00887 0.00348 -0.0550 0.7177 1.0000 3.500 0.6228 0.00904 0.00357 -0.0538 0.6809 1.0000 3.750 0.6465 0.00927 0.00368 -0.0527 0.6391 1.0000 4.000 0.6694 0.00960 0.00383 -0.0514 0.5907 1.0000 4.250 0.6909 0.01003 0.00404 -0.0499 0.5278 1.0000 4.500 0.7113 0.01058 0.00429 -0.0484 0.4565 1.0000 4.750 0.7318 0.01122 0.00461 -0.0471 0.3850 1.0000 5.000 0.7526 0.01190 0.00500 -0.0460 0.3168 1.0000 5.250 0.7731 0.01268 0.00547 -0.0450 0.2443 1.0000 5.500 0.7932 0.01362 0.00602 -0.0440 0.1665 1.0000 5.750 0.8079 0.01556 0.00722 -0.0422 0.0575 1.0000 6.000 0.8282 0.01673 0.00838 -0.0408 0.0441 1.0000 6.250 0.8462 0.01820 0.00986 -0.0391 0.0394 1.0000 6.500 0.8684 0.01913 0.01090 -0.0381 0.0366 1.0000 6.750 0.8902 0.02016 0.01203 -0.0371 0.0337 1.0000 7.000 0.9116 0.02150 0.01342 -0.0360 0.0320 1.0000 7.250 0.9334 0.02322 0.01519 -0.0350 0.0308 1.0000 7.500 0.9564 0.02558 0.01767 -0.0341 0.0300 1.0000 7.750 0.9796 0.02832 0.02064 -0.0333 0.0297 1.0000 8.000 0.9997 0.03195 0.02462 -0.0322 0.0293 1.0000 8.250 1.0182 0.03343 0.02646 -0.0307 0.0283 1.0000 8.500 1.0337 0.03647 0.02994 -0.0291 0.0282 1.0000 8.750 1.0438 0.04102 0.03491 -0.0272 0.0287 1.0000 9.000 1.0592 0.04419 0.03834 -0.0257 0.0298 1.0000 14.000 0.7118 0.16216 0.15923 -0.0563 0.0509 1.0000 14.250 0.7048 0.16611 0.16317 -0.0601 0.0506 1.0000