XFOIL Version 6.96 Calculated polar for: RAF 28 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.4970 0.09742 0.09015 -0.0292 1.0000 0.0591 -9.500 -0.5013 0.09272 0.08553 -0.0315 1.0000 0.0594 -9.250 -0.5070 0.08781 0.08070 -0.0341 1.0000 0.0592 -9.000 -0.5152 0.08256 0.07554 -0.0372 1.0000 0.0591 -8.750 -0.5282 0.07679 0.06989 -0.0410 1.0000 0.0585 -8.500 -0.5439 0.07152 0.06465 -0.0429 1.0000 0.0578 -8.250 -0.5566 0.06669 0.05977 -0.0441 1.0000 0.0580 -8.000 -0.5668 0.06208 0.05503 -0.0443 1.0000 0.0579 -7.750 -0.5734 0.05779 0.05055 -0.0439 1.0000 0.0587 -7.500 -0.5763 0.05368 0.04617 -0.0430 1.0000 0.0592 -7.250 -0.5758 0.04971 0.04186 -0.0416 1.0000 0.0597 -7.000 -0.5719 0.04598 0.03772 -0.0400 1.0000 0.0604 -6.750 -0.5652 0.04264 0.03382 -0.0383 1.0000 0.0624 -6.500 -0.5560 0.03970 0.03033 -0.0363 1.0000 0.0651 -6.250 -0.5420 0.03757 0.02809 -0.0348 1.0000 0.0676 -6.000 -0.5270 0.03537 0.02559 -0.0332 1.0000 0.0694 -5.750 -0.5107 0.03333 0.02321 -0.0315 1.0000 0.0714 -5.500 -0.4936 0.03169 0.02116 -0.0298 1.0000 0.0758 -5.250 -0.4759 0.03011 0.01933 -0.0283 1.0000 0.0797 -5.000 -0.4573 0.02871 0.01778 -0.0268 1.0000 0.0825 -4.750 -0.4381 0.02745 0.01635 -0.0253 1.0000 0.0856 -4.500 -0.4185 0.02633 0.01500 -0.0237 1.0000 0.0894 -4.250 -0.3994 0.02531 0.01386 -0.0221 1.0000 0.0936 -4.000 -0.3810 0.02444 0.01295 -0.0206 1.0000 0.0999 -3.750 -0.3622 0.02369 0.01214 -0.0193 1.0000 0.1115 -3.500 -0.3422 0.02288 0.01130 -0.0183 1.0000 0.1283 -3.250 -0.3227 0.02198 0.01052 -0.0173 1.0000 0.1556 -3.000 -0.3042 0.02110 0.01000 -0.0163 1.0000 0.2163 -2.750 -0.2818 0.02034 0.00973 -0.0161 0.9975 0.3350 -2.500 -0.2523 0.01942 0.00973 -0.0168 0.9888 0.5150 -2.250 -0.2236 0.01877 0.00989 -0.0160 0.9806 0.7003 -2.000 -0.1380 0.01860 0.00993 -0.0250 0.9833 0.9493 -1.750 -0.0789 0.01875 0.00965 -0.0319 0.9781 1.0000 -1.500 -0.0402 0.01884 0.00940 -0.0350 0.9663 1.0000 -1.250 -0.0028 0.01894 0.00923 -0.0376 0.9543 1.0000 -1.000 0.0341 0.01903 0.00908 -0.0400 0.9422 1.0000 -0.750 0.0718 0.01912 0.00897 -0.0425 0.9306 1.0000 -0.500 0.1132 0.01919 0.00887 -0.0455 0.9207 1.0000 -0.250 0.1496 0.01926 0.00879 -0.0475 0.9087 1.0000 0.000 0.1859 0.01932 0.00875 -0.0494 0.8969 1.0000 0.250 0.2219 0.01938 0.00872 -0.0512 0.8854 1.0000 0.500 0.2585 0.01944 0.00870 -0.0530 0.8746 1.0000 0.750 0.2948 0.01949 0.00870 -0.0546 0.8638 1.0000 1.000 0.3253 0.01961 0.00880 -0.0551 0.8511 1.0000 1.250 0.3551 0.01975 0.00892 -0.0555 0.8385 1.0000 1.500 0.3840 0.01992 0.00909 -0.0556 0.8259 1.0000 1.750 0.4122 0.02010 0.00928 -0.0556 0.8133 1.0000 2.000 0.4404 0.02030 0.00949 -0.0555 0.8009 1.0000 2.250 0.4683 0.02049 0.00974 -0.0554 0.7885 1.0000 2.500 0.4963 0.02068 0.00997 -0.0552 0.7764 1.0000 2.750 0.5205 0.02095 0.01031 -0.0544 0.7629 1.0000 3.000 0.5441 0.02123 0.01068 -0.0534 0.7491 1.0000 3.250 0.5677 0.02150 0.01104 -0.0525 0.7353 1.0000 3.500 0.5914 0.02176 0.01139 -0.0515 0.7214 1.0000 3.750 0.6153 0.02198 0.01173 -0.0504 0.7071 1.0000 4.000 0.6397 0.02215 0.01204 -0.0494 0.6923 1.0000 4.250 0.6648 0.02226 0.01227 -0.0482 0.6765 1.0000 4.500 0.6885 0.02231 0.01243 -0.0467 0.6577 1.0000 4.750 0.7115 0.02227 0.01251 -0.0448 0.6347 1.0000 5.000 0.7338 0.02227 0.01259 -0.0428 0.6101 1.0000 5.250 0.7570 0.02230 0.01270 -0.0410 0.5857 1.0000 5.500 0.7771 0.02257 0.01314 -0.0392 0.5619 1.0000 5.750 0.7981 0.02282 0.01359 -0.0374 0.5379 1.0000 6.000 0.8160 0.02301 0.01390 -0.0349 0.5041 1.0000 6.250 0.8299 0.02316 0.01397 -0.0316 0.4527 1.0000 6.500 0.8397 0.02362 0.01418 -0.0280 0.3832 1.0000 6.750 0.8481 0.02452 0.01470 -0.0247 0.3017 1.0000 7.000 0.8540 0.02595 0.01565 -0.0215 0.2266 1.0000 7.250 0.8573 0.02786 0.01712 -0.0185 0.1620 1.0000 7.500 0.8607 0.02994 0.01882 -0.0157 0.1202 1.0000 7.750 0.8670 0.03184 0.02062 -0.0130 0.0974 1.0000 8.000 0.8753 0.03351 0.02224 -0.0107 0.0822 1.0000 8.250 0.8857 0.03511 0.02392 -0.0085 0.0730 1.0000 8.500 0.8958 0.03678 0.02559 -0.0063 0.0668 1.0000 8.750 0.9097 0.03838 0.02734 -0.0046 0.0601 1.0000 9.000 0.9251 0.04027 0.02922 -0.0031 0.0555 1.0000 9.250 0.9513 0.04240 0.03173 -0.0025 0.0515 1.0000 9.500 0.9693 0.04451 0.03401 -0.0015 0.0476 1.0000 9.750 0.9891 0.04729 0.03679 -0.0010 0.0445 1.0000 10.000 1.0047 0.05026 0.04023 0.0003 0.0432 1.0000 10.250 1.0127 0.05337 0.04376 0.0021 0.0422 1.0000 10.500 1.0127 0.05647 0.04724 0.0043 0.0411 1.0000 10.750 1.0080 0.05955 0.05064 0.0066 0.0401 1.0000 11.000 0.9998 0.06283 0.05421 0.0085 0.0395 1.0000 11.250 0.9885 0.06638 0.05802 0.0098 0.0390 1.0000 11.500 0.9746 0.07024 0.06212 0.0103 0.0385 1.0000 11.750 0.9573 0.07477 0.06689 0.0099 0.0385 1.0000 12.000 0.9361 0.08021 0.07256 0.0083 0.0388 1.0000 12.250 0.9119 0.08672 0.07925 0.0052 0.0393 1.0000 12.500 0.8871 0.09428 0.08697 0.0009 0.0402 1.0000