XFOIL Version 6.94 Calculated polar for: USA 22 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2546 0.01068 0.00300 -0.0466 0.5615 0.3215 0.500 0.3089 0.01076 0.00302 -0.0459 0.5280 0.3518 1.000 0.3631 0.01082 0.00302 -0.0452 0.4991 0.3844 1.500 0.4169 0.01072 0.00300 -0.0446 0.4745 0.4243 2.000 0.4933 0.00945 0.00317 -0.0482 0.4533 1.0000 2.500 0.5462 0.00975 0.00331 -0.0472 0.4342 1.0000 3.000 0.5989 0.01011 0.00351 -0.0462 0.4177 1.0000 3.500 0.6520 0.01043 0.00375 -0.0453 0.4005 1.0000 4.000 0.7049 0.01080 0.00403 -0.0444 0.3842 1.0000 4.500 0.7580 0.01113 0.00434 -0.0435 0.3656 1.0000 5.000 0.8107 0.01150 0.00467 -0.0426 0.3470 1.0000 5.500 0.8632 0.01189 0.00504 -0.0417 0.3261 1.0000 6.000 0.9153 0.01232 0.00547 -0.0408 0.3019 1.0000 6.500 0.9663 0.01290 0.00597 -0.0397 0.2766 1.0000 7.000 1.0166 0.01359 0.00661 -0.0387 0.2540 1.0000 7.500 1.0662 0.01435 0.00735 -0.0376 0.2333 1.0000 8.000 1.1151 0.01514 0.00812 -0.0364 0.2148 1.0000 8.500 1.1633 0.01596 0.00896 -0.0352 0.1981 1.0000 9.000 1.2112 0.01679 0.00987 -0.0340 0.1846 1.0000 9.500 1.2581 0.01764 0.01084 -0.0327 0.1695 1.0000 10.000 1.3039 0.01850 0.01181 -0.0314 0.1528 1.0000 10.500 1.3483 0.01945 0.01285 -0.0299 0.1293 1.0000 11.000 1.3772 0.02183 0.01488 -0.0271 0.0653 1.0000 11.500 1.3904 0.02525 0.01814 -0.0227 0.0362 1.0000 12.000 1.3967 0.02839 0.02142 -0.0178 0.0299 1.0000 12.500 1.3940 0.03283 0.02605 -0.0148 0.0260 1.0000 13.000 1.3850 0.03926 0.03275 -0.0150 0.0247 1.0000 13.500 1.3736 0.04723 0.04097 -0.0175 0.0230 1.0000 14.000 1.3471 0.05766 0.05161 -0.0212 0.0223 1.0000 14.500 1.3290 0.06707 0.06129 -0.0243 0.0214 1.0000 15.000 1.3088 0.07669 0.07110 -0.0274 0.0207 1.0000 15.500 1.2903 0.08618 0.08070 -0.0304 0.0196 1.0000 16.000 1.2792 0.09448 0.08911 -0.0325 0.0187 1.0000 16.500 1.2696 0.10319 0.09802 -0.0354 0.0175 1.0000 17.000 1.2705 0.10954 0.10436 -0.0366 0.0164 1.0000 17.500 1.2609 0.11861 0.11367 -0.0401 0.0154 1.0000 18.000 1.2543 0.12738 0.12266 -0.0436 0.0146 1.0000 18.500 1.2556 0.13396 0.12923 -0.0458 0.0134 1.0000 19.000 1.2492 0.14308 0.13860 -0.0501 0.0133 1.0000 19.500 1.2263 0.15689 0.15279 -0.0583 0.0130 1.0000