XFOIL Version 6.96 Calculated polar for: Smoothed ATR airfoil coordinates obtained using 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 ------ -------- --------- --------- -------- -------- -------- -18.250 -0.7936 0.12983 0.12744 -0.0175 1.0000 0.0133 -18.000 -0.8480 0.11534 0.11278 -0.0256 1.0000 0.0132 -17.750 -0.9335 0.09646 0.09369 -0.0367 1.0000 0.0132 -17.500 -1.0731 0.06841 0.06519 -0.0541 1.0000 0.0129 -17.250 -1.1251 0.05531 0.05181 -0.0635 1.0000 0.0129 -17.000 -1.1497 0.04787 0.04417 -0.0688 1.0000 0.0128 -16.750 -1.1598 0.04321 0.03939 -0.0716 1.0000 0.0130 -16.500 -1.1675 0.03937 0.03542 -0.0734 1.0000 0.0130 -16.250 -1.1714 0.03630 0.03225 -0.0743 1.0000 0.0130 -16.000 -1.1730 0.03378 0.02962 -0.0746 1.0000 0.0131 -15.750 -1.1718 0.03173 0.02748 -0.0742 1.0000 0.0132 -15.500 -1.1701 0.02993 0.02559 -0.0733 1.0000 0.0133 -15.250 -1.1652 0.02852 0.02411 -0.0721 1.0000 0.0133 -15.000 -1.1612 0.02716 0.02267 -0.0705 1.0000 0.0134 -14.750 -1.1551 0.02604 0.02147 -0.0687 1.0000 0.0135 -14.500 -1.1475 0.02508 0.02044 -0.0667 1.0000 0.0136 -14.250 -1.1403 0.02416 0.01946 -0.0645 1.0000 0.0137 -14.000 -1.1323 0.02336 0.01860 -0.0621 1.0000 0.0138 -13.750 -1.1247 0.02263 0.01780 -0.0593 1.0000 0.0139 -13.500 -1.1173 0.02200 0.01711 -0.0563 1.0000 0.0140 -13.250 -1.1100 0.02145 0.01652 -0.0530 1.0000 0.0142 -13.000 -1.1004 0.02085 0.01587 -0.0502 1.0000 0.0143 -12.750 -1.0884 0.02034 0.01531 -0.0476 1.0000 0.0145 -12.500 -1.0634 0.01968 0.01459 -0.0477 0.9907 0.0146 -12.250 -1.0344 0.01901 0.01387 -0.0485 0.9852 0.0147 -12.000 -1.0034 0.01838 0.01318 -0.0496 0.9809 0.0149 -11.750 -0.9733 0.01777 0.01252 -0.0505 0.9753 0.0150 -11.500 -0.9425 0.01703 0.01171 -0.0517 0.9698 0.0153 -11.250 -0.9133 0.01639 0.01103 -0.0524 0.9629 0.0156 -11.000 -0.8843 0.01586 0.01046 -0.0529 0.9563 0.0158 -10.750 -0.8585 0.01540 0.00995 -0.0527 0.9476 0.0161 -10.500 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0.0304 -5.500 -0.3572 0.01053 0.00361 -0.0339 0.5777 0.0351 -5.250 -0.3316 0.01043 0.00346 -0.0333 0.5586 0.0379 -5.000 -0.3057 0.01037 0.00333 -0.0328 0.5362 0.0404 -4.750 -0.2802 0.01031 0.00319 -0.0322 0.5098 0.0434 -4.500 -0.2548 0.01031 0.00307 -0.0315 0.4726 0.0460 -4.250 -0.2298 0.01036 0.00297 -0.0309 0.4304 0.0480 -4.000 -0.2044 0.01036 0.00287 -0.0303 0.4017 0.0508 -3.750 -0.1784 0.01035 0.00278 -0.0298 0.3812 0.0532 -3.500 -0.1521 0.01032 0.00269 -0.0293 0.3659 0.0561 -3.250 -0.1258 0.01027 0.00261 -0.0288 0.3534 0.0597 -3.000 -0.0989 0.01022 0.00253 -0.0285 0.3449 0.0632 -2.500 -0.0457 0.01006 0.00238 -0.0277 0.3300 0.0773 -2.250 -0.0190 0.01000 0.00231 -0.0273 0.3228 0.0856 -2.000 0.0077 0.00994 0.00225 -0.0269 0.3163 0.0954 -1.750 0.0345 0.00986 0.00220 -0.0265 0.3104 0.1089 -1.500 0.0611 0.00981 0.00216 -0.0262 0.3047 0.1229 -1.250 0.0880 0.00974 0.00213 -0.0258 0.3003 0.1379 -1.000 0.1147 0.00965 0.00209 -0.0255 0.2964 0.1575 -0.750 0.1413 0.00957 0.00206 -0.0251 0.2921 0.1815 -0.500 0.1676 0.00949 0.00204 -0.0247 0.2873 0.2086 -0.250 0.1935 0.00934 0.00201 -0.0242 0.2834 0.2520 0.000 0.2168 0.00894 0.00196 -0.0234 0.2800 0.3638 0.250 0.2416 0.00872 0.00195 -0.0228 0.2763 0.4365 0.500 0.2666 0.00857 0.00195 -0.0222 0.2728 0.4953 0.750 0.2900 0.00833 0.00196 -0.0212 0.2691 0.5813 1.000 0.3138 0.00813 0.00201 -0.0203 0.2670 0.6601 1.250 0.3393 0.00806 0.00205 -0.0197 0.2644 0.6999 1.500 0.3653 0.00804 0.00208 -0.0191 0.2608 0.7274 1.750 0.3907 0.00801 0.00213 -0.0184 0.2574 0.7573 2.000 0.4154 0.00798 0.00220 -0.0176 0.2540 0.7930 2.250 0.4394 0.00794 0.00231 -0.0165 0.2518 0.8433 2.500 0.4645 0.00796 0.00243 -0.0157 0.2499 0.8805 2.750 0.4910 0.00803 0.00251 -0.0152 0.2475 0.8960 3.000 0.5177 0.00811 0.00258 -0.0148 0.2448 0.9051 3.250 0.5445 0.00821 0.00267 -0.0144 0.2417 0.9129 3.500 0.5707 0.00833 0.00276 -0.0140 0.2383 0.9208 3.750 0.5977 0.00843 0.00285 -0.0137 0.2362 0.9274 4.000 0.6242 0.00851 0.00295 -0.0133 0.2344 0.9357 4.250 0.6511 0.00861 0.00305 -0.0129 0.2324 0.9441 4.500 0.6771 0.00872 0.00315 -0.0124 0.2300 0.9528 4.750 0.7059 0.00884 0.00326 -0.0126 0.2273 0.9582 5.000 0.7347 0.00899 0.00338 -0.0128 0.2241 0.9625 5.250 0.7618 0.00912 0.00350 -0.0126 0.2216 0.9669 5.500 0.7917 0.00924 0.00362 -0.0130 0.2201 0.9700 5.750 0.8236 0.00937 0.00375 -0.0139 0.2182 0.9723 6.000 0.8550 0.00951 0.00388 -0.0147 0.2159 0.9746 6.250 0.8851 0.00966 0.00402 -0.0153 0.2132 0.9772 6.500 0.9139 0.00983 0.00417 -0.0156 0.2103 0.9803 6.750 0.9445 0.01002 0.00434 -0.0163 0.2075 0.9824 7.000 0.9778 0.01017 0.00450 -0.0176 0.2061 0.9836 7.250 1.0104 0.01033 0.00467 -0.0187 0.2043 0.9851 7.500 1.0420 0.01049 0.00483 -0.0197 0.2017 0.9869 7.750 1.0728 0.01068 0.00501 -0.0205 0.1991 0.9890 8.000 1.1028 0.01088 0.00521 -0.0211 0.1966 0.9915 8.250 1.1323 0.01110 0.00542 -0.0217 0.1937 0.9939 8.500 1.1628 0.01128 0.00561 -0.0225 0.1918 0.9961 8.750 1.1935 0.01146 0.00581 -0.0233 0.1900 0.9981 9.000 1.2243 0.01166 0.00602 -0.0242 0.1876 0.9996 9.250 1.2454 0.01184 0.00621 -0.0230 0.1852 1.0000 9.500 1.2625 0.01204 0.00641 -0.0211 0.1828 1.0000 9.750 1.2801 0.01226 0.00663 -0.0193 0.1801 1.0000 10.000 1.2990 0.01245 0.00684 -0.0177 0.1783 1.0000 10.250 1.3186 0.01263 0.00705 -0.0163 0.1765 1.0000 10.500 1.3378 0.01283 0.00727 -0.0148 0.1744 1.0000 10.750 1.3565 0.01306 0.00752 -0.0133 0.1718 1.0000 11.000 1.3730 0.01332 0.00778 -0.0114 0.1691 1.0000 11.250 1.3879 0.01360 0.00806 -0.0092 0.1665 1.0000 11.500 1.4047 0.01383 0.00833 -0.0074 0.1646 1.0000 11.750 1.4219 0.01408 0.00862 -0.0057 0.1624 1.0000 12.000 1.4390 0.01437 0.00893 -0.0041 0.1601 1.0000 12.250 1.4553 0.01471 0.00928 -0.0024 0.1570 1.0000 12.500 1.4708 0.01510 0.00968 -0.0007 0.1540 1.0000 12.750 1.4875 0.01546 0.01007 0.0007 0.1513 1.0000 13.000 1.5043 0.01583 0.01048 0.0021 0.1486 1.0000 13.250 1.5183 0.01635 0.01098 0.0038 0.1431 1.0000 13.500 1.5323 0.01689 0.01153 0.0054 0.1386 1.0000 13.750 1.5451 0.01751 0.01214 0.0070 0.1319 1.0000 14.000 1.5562 0.01825 0.01288 0.0087 0.1254 1.0000 14.250 1.5670 0.01903 0.01365 0.0104 0.1195 1.0000 14.500 1.5772 0.01987 0.01450 0.0120 0.1146 1.0000 14.750 1.5866 0.02081 0.01544 0.0135 0.1089 1.0000 15.000 1.5939 0.02192 0.01656 0.0151 0.1036 1.0000 15.250 1.6013 0.02307 0.01773 0.0165 0.0985 1.0000 15.500 1.6062 0.02446 0.01914 0.0178 0.0938 1.0000 15.750 1.6114 0.02592 0.02062 0.0190 0.0888 1.0000 16.000 1.6126 0.02776 0.02248 0.0200 0.0842 1.0000 16.250 1.6135 0.02976 0.02451 0.0208 0.0789 1.0000 16.500 1.6105 0.03223 0.02701 0.0214 0.0745 1.0000 16.750 1.6107 0.03454 0.02939 0.0216 0.0712 1.0000 17.000 1.6049 0.03760 0.03251 0.0216 0.0676 1.0000 17.250 1.5941 0.04136 0.03633 0.0211 0.0631 1.0000 17.500 1.5847 0.04518 0.04023 0.0204 0.0606 1.0000 17.750 1.5641 0.05044 0.04557 0.0191 0.0571 1.0000 18.000 1.5484 0.05532 0.05056 0.0177 0.0553 1.0000 18.250 1.5222 0.06172 0.05709 0.0157 0.0530 1.0000 18.500 1.4989 0.06791 0.06341 0.0136 0.0525 1.0000 19.000 1.4354 0.08276 0.07852 0.0085 0.0508 1.0000 19.250 1.4056 0.09005 0.08593 0.0059 0.0501 1.0000