XFOIL Version 6.96 Calculated polar for: RAF 30 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1864 0.10873 0.10565 -0.0119 1.0000 0.0082 -19.500 -1.2154 0.09996 0.09674 -0.0164 1.0000 0.0081 -19.250 -1.2405 0.09204 0.08869 -0.0204 1.0000 0.0082 -19.000 -1.2643 0.08453 0.08105 -0.0242 1.0000 0.0082 -18.750 -1.2858 0.07749 0.07387 -0.0277 1.0000 0.0082 -18.500 -1.3027 0.07139 0.06764 -0.0306 1.0000 0.0083 -18.250 -1.3169 0.06582 0.06194 -0.0333 1.0000 0.0083 -18.000 -1.3296 0.06067 0.05667 -0.0356 1.0000 0.0083 -17.750 -1.3375 0.05639 0.05228 -0.0373 1.0000 0.0084 -17.500 -1.3458 0.05219 0.04797 -0.0390 1.0000 0.0086 -17.250 -1.3530 0.04833 0.04400 -0.0402 1.0000 0.0087 -17.000 -1.3582 0.04484 0.04042 -0.0412 1.0000 0.0089 -16.750 -1.3603 0.04183 0.03731 -0.0419 1.0000 0.0090 -16.500 -1.3613 0.03906 0.03447 -0.0423 1.0000 0.0093 -16.250 -1.3602 0.03660 0.03192 -0.0424 1.0000 0.0095 -16.000 -1.3576 0.03441 0.02965 -0.0424 1.0000 0.0098 -15.750 -1.3531 0.03249 0.02766 -0.0421 1.0000 0.0101 -15.500 -1.3482 0.03068 0.02577 -0.0417 1.0000 0.0103 -15.250 -1.3419 0.02909 0.02410 -0.0410 1.0000 0.0106 -15.000 -1.3349 0.02764 0.02257 -0.0402 1.0000 0.0109 -14.750 -1.3272 0.02631 0.02117 -0.0392 1.0000 0.0111 -14.500 -1.3193 0.02508 0.01988 -0.0380 1.0000 0.0116 -14.250 -1.3101 0.02402 0.01878 -0.0367 1.0000 0.0120 -14.000 -1.2999 0.02308 0.01779 -0.0353 1.0000 0.0126 -13.750 -1.2892 0.02223 0.01689 -0.0337 1.0000 0.0130 -13.500 -1.2780 0.02147 0.01608 -0.0320 1.0000 0.0135 -13.250 -1.2664 0.02078 0.01533 -0.0302 1.0000 0.0139 -13.000 -1.2549 0.02014 0.01464 -0.0281 1.0000 0.0144 -12.750 -1.2431 0.01956 0.01403 -0.0260 1.0000 0.0149 -12.500 -1.2300 0.01909 0.01356 -0.0239 1.0000 0.0157 -12.250 -1.2181 0.01864 0.01306 -0.0214 1.0000 0.0163 -12.000 -1.2061 0.01822 0.01262 -0.0188 1.0000 0.0168 -11.750 -1.1919 0.01782 0.01217 -0.0167 1.0000 0.0174 -11.500 -1.1756 0.01741 0.01172 -0.0148 1.0000 0.0178 -11.250 -1.1602 0.01695 0.01123 -0.0128 1.0000 0.0183 -11.000 -1.1438 0.01654 0.01079 -0.0110 1.0000 0.0189 -10.750 -1.1264 0.01617 0.01041 -0.0093 1.0000 0.0195 -10.500 -1.1086 0.01582 0.01005 -0.0076 1.0000 0.0202 -10.250 -1.0900 0.01552 0.00972 -0.0060 1.0000 0.0209 -10.000 -1.0713 0.01522 0.00939 -0.0044 1.0000 0.0215 -9.750 -1.0526 0.01492 0.00906 -0.0028 1.0000 0.0219 -9.500 -1.0338 0.01462 0.00873 -0.0012 1.0000 0.0222 -9.250 -1.0156 0.01429 0.00837 0.0005 1.0000 0.0227 -9.000 -0.9894 0.01381 0.00788 0.0004 0.9990 0.0237 -8.750 -0.9583 0.01342 0.00747 -0.0006 0.9969 0.0245 -8.250 -0.8984 0.01275 0.00677 -0.0021 0.9907 0.0260 -8.000 -0.8684 0.01243 0.00643 -0.0028 0.9867 0.0267 -7.750 -0.8377 0.01214 0.00612 -0.0037 0.9826 0.0273 -7.500 -0.8098 0.01186 0.00581 -0.0038 0.9759 0.0277 -7.250 -0.7788 0.01153 0.00546 -0.0047 0.9697 0.0284 -7.000 -0.7457 0.01116 0.00508 -0.0060 0.9622 0.0296 -6.750 -0.7076 0.01082 0.00473 -0.0085 0.9545 0.0307 -6.500 -0.6665 0.01050 0.00440 -0.0116 0.9440 0.0319 -6.250 -0.6259 0.01021 0.00408 -0.0145 0.9278 0.0333 -6.000 -0.5922 0.01002 0.00381 -0.0158 0.9056 0.0344 -5.750 -0.5654 0.00986 0.00357 -0.0156 0.8835 0.0367 -5.500 -0.5409 0.00969 0.00336 -0.0149 0.8646 0.0404 -5.250 -0.5175 0.00948 0.00313 -0.0140 0.8476 0.0496 -5.000 -0.4957 0.00915 0.00288 -0.0129 0.8316 0.0757 -4.750 -0.4724 0.00892 0.00269 -0.0120 0.8175 0.0945 -4.500 -0.4480 0.00875 0.00253 -0.0113 0.8040 0.1074 -4.250 -0.4240 0.00855 0.00236 -0.0105 0.7907 0.1253 -4.000 -0.4006 0.00829 0.00218 -0.0097 0.7781 0.1517 -3.750 -0.3769 0.00806 0.00202 -0.0089 0.7657 0.1787 -3.500 -0.3533 0.00782 0.00187 -0.0080 0.7534 0.2102 -3.250 -0.3291 0.00762 0.00174 -0.0073 0.7393 0.2396 -3.000 -0.3051 0.00747 0.00163 -0.0065 0.7213 0.2677 -2.750 -0.2805 0.00735 0.00153 -0.0058 0.7019 0.2912 -2.500 -0.2556 0.00723 0.00144 -0.0052 0.6860 0.3128 -2.000 -0.2046 0.00701 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3.500 0.3532 0.00783 0.00187 0.0080 0.2097 0.7533 3.750 0.3768 0.00806 0.00202 0.0089 0.1778 0.7658 4.000 0.4005 0.00829 0.00218 0.0097 0.1514 0.7785 4.250 0.4239 0.00855 0.00237 0.0106 0.1244 0.7909 4.500 0.4480 0.00875 0.00253 0.0113 0.1072 0.8038 4.750 0.4723 0.00892 0.00269 0.0120 0.0939 0.8172 5.000 0.4955 0.00915 0.00288 0.0129 0.0750 0.8318 5.250 0.5173 0.00949 0.00314 0.0141 0.0484 0.8475 5.500 0.5409 0.00969 0.00336 0.0149 0.0402 0.8648 5.750 0.5654 0.00985 0.00357 0.0156 0.0368 0.8835 6.000 0.5922 0.01002 0.00381 0.0158 0.0343 0.9057 6.250 0.6261 0.01022 0.00408 0.0145 0.0332 0.9282 6.500 0.6663 0.01050 0.00440 0.0116 0.0319 0.9440 6.750 0.7074 0.01083 0.00474 0.0085 0.0307 0.9544 7.000 0.7454 0.01115 0.00507 0.0061 0.0297 0.9620 7.250 0.7788 0.01153 0.00546 0.0047 0.0285 0.9697 7.500 0.8098 0.01186 0.00581 0.0038 0.0277 0.9759 7.750 0.8376 0.01214 0.00612 0.0037 0.0273 0.9826 8.000 0.8682 0.01243 0.00644 0.0029 0.0267 0.9867 8.250 0.8983 0.01275 0.00677 0.0022 0.0260 0.9906 8.750 0.9584 0.01342 0.00748 0.0006 0.0245 0.9969 9.000 0.9893 0.01381 0.00786 -0.0004 0.0236 0.9989 9.250 1.0158 0.01428 0.00836 -0.0005 0.0227 1.0000 9.500 1.0339 0.01463 0.00873 0.0012 0.0223 1.0000 9.750 1.0530 0.01490 0.00904 0.0028 0.0219 1.0000 10.000 1.0715 0.01521 0.00938 0.0044 0.0215 1.0000 10.250 1.0898 0.01554 0.00975 0.0061 0.0210 1.0000 10.500 1.1082 0.01586 0.01009 0.0077 0.0203 1.0000 10.750 1.1261 0.01619 0.01044 0.0093 0.0197 1.0000 11.000 1.1437 0.01655 0.01081 0.0110 0.0190 1.0000 11.250 1.1604 0.01695 0.01122 0.0128 0.0183 1.0000 11.500 1.1757 0.01740 0.01171 0.0148 0.0178 1.0000 11.750 1.1921 0.01781 0.01216 0.0166 0.0173 1.0000 12.000 1.2061 0.01822 0.01261 0.0188 0.0168 1.0000 12.250 1.2185 0.01861 0.01303 0.0214 0.0162 1.0000 12.500 1.2309 0.01905 0.01350 0.0237 0.0155 1.0000 12.750 1.2432 0.01955 0.01402 0.0260 0.0149 1.0000 13.000 1.2549 0.02014 0.01463 0.0281 0.0142 1.0000 13.250 1.2667 0.02077 0.01531 0.0301 0.0138 1.0000 13.500 1.2784 0.02146 0.01606 0.0320 0.0135 1.0000 13.750 1.2896 0.02222 0.01687 0.0337 0.0130 1.0000 14.000 1.3003 0.02306 0.01777 0.0353 0.0126 1.0000 14.250 1.3105 0.02400 0.01876 0.0367 0.0120 1.0000 14.500 1.3196 0.02507 0.01987 0.0380 0.0115 1.0000 14.750 1.3277 0.02629 0.02115 0.0392 0.0112 1.0000 15.000 1.3352 0.02763 0.02256 0.0402 0.0108 1.0000 15.250 1.3430 0.02902 0.02402 0.0410 0.0105 1.0000 15.500 1.3487 0.03066 0.02575 0.0416 0.0104 1.0000 15.750 1.3541 0.03243 0.02759 0.0421 0.0101 1.0000 16.000 1.3585 0.03437 0.02960 0.0423 0.0097 1.0000 16.250 1.3613 0.03654 0.03186 0.0423 0.0095 1.0000 16.500 1.3622 0.03903 0.03443 0.0422 0.0092 1.0000 16.750 1.3616 0.04177 0.03725 0.0417 0.0090 1.0000 17.000 1.3592 0.04481 0.04039 0.0411 0.0088 1.0000 17.250 1.3543 0.04828 0.04396 0.0401 0.0087 1.0000 17.500 1.3468 0.05220 0.04798 0.0388 0.0086 1.0000 17.750 1.3399 0.05620 0.05209 0.0372 0.0084 1.0000 18.000 1.3301 0.06076 0.05677 0.0353 0.0084 1.0000 18.250 1.3185 0.06577 0.06190 0.0331 0.0083 1.0000 18.500 1.3051 0.07122 0.06747 0.0305 0.0083 1.0000 18.750 1.2891 0.07719 0.07357 0.0276 0.0082 1.0000 19.000 1.2667 0.08437 0.08089 0.0240 0.0082 1.0000 19.250 1.2442 0.09169 0.08834 0.0203 0.0081 1.0000