XFOIL Version 6.96 Calculated polar for: NACA M23 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4193 0.11724 0.11410 0.0275 0.6280 0.0079 -8.750 -0.4133 0.11405 0.11089 0.0261 0.6239 0.0077 -8.500 -0.4077 0.11067 0.10751 0.0245 0.6196 0.0075 -8.250 -0.4023 0.10724 0.10407 0.0227 0.6154 0.0075 -8.000 -0.3972 0.10375 0.10058 0.0209 0.6115 0.0074 -7.750 -0.3925 0.10021 0.09702 0.0187 0.6079 0.0075 -7.500 -0.3887 0.09666 0.09349 0.0163 0.6040 0.0075 -7.250 -0.3825 0.09299 0.08979 0.0135 0.6000 0.0076 -7.000 -0.3729 0.08885 0.08563 0.0101 0.5963 0.0078 -6.750 -0.3617 0.08400 0.08075 0.0061 0.5929 0.0083 -6.500 -0.3460 0.08188 0.07860 0.0042 0.5883 0.0086 -6.250 -0.3297 0.07906 0.07573 0.0018 0.5841 0.0090 -6.000 -0.3126 0.07548 0.07209 -0.0012 0.5804 0.0094 -5.750 -0.2941 0.07159 0.06813 -0.0043 0.5767 0.0096 -5.500 -0.2739 0.06757 0.06405 -0.0073 0.5727 0.0100 -5.250 -0.2518 0.06278 0.05914 -0.0107 0.5690 0.0106 -4.750 -0.2061 0.05750 0.05370 -0.0144 0.5613 0.0121 -4.500 -0.1817 0.05436 0.05046 -0.0163 0.5573 0.0128 -4.250 -0.1557 0.05069 0.04664 -0.0183 0.5534 0.0136 -4.000 -0.1276 0.04643 0.04219 -0.0202 0.5500 0.0150 -3.750 -0.1036 0.04515 0.04086 -0.0209 0.5457 0.0157 -3.500 -0.0773 0.04281 0.03839 -0.0219 0.5418 0.0166 -3.250 -0.0496 0.03994 0.03535 -0.0228 0.5381 0.0175 -3.000 -0.0182 0.03611 0.03125 -0.0236 0.5349 0.0198 -2.750 0.0060 0.03509 0.03019 -0.0240 0.5306 0.0205 -2.500 0.0328 0.03328 0.02825 -0.0244 0.5265 0.0212 -2.250 0.0605 0.03124 0.02603 -0.0246 0.5229 0.0219 -2.000 0.0891 0.02924 0.02385 -0.0248 0.5195 0.0232 -1.750 0.1182 0.02694 0.02134 -0.0247 0.5158 0.0240 -1.500 0.1472 0.02475 0.01891 -0.0245 0.5119 0.0245 -1.250 0.1757 0.02281 0.01674 -0.0243 0.5082 0.0248 -1.000 0.2045 0.01997 0.01354 -0.0238 0.5051 0.0263 -0.750 0.2328 0.01828 0.01160 -0.0235 0.5016 0.0260 -0.500 0.2606 0.01654 0.00958 -0.0234 0.4977 0.0263 -0.250 0.2886 0.01540 0.00822 -0.0234 0.4938 0.0268 0.000 0.3168 0.01463 0.00729 -0.0235 0.4903 0.0272 0.250 0.3453 0.01396 0.00651 -0.0236 0.4867 0.0276 0.500 0.3738 0.01340 0.00583 -0.0238 0.4827 0.0278 0.750 0.4022 0.01301 0.00535 -0.0239 0.4787 0.0285 1.000 0.4305 0.01267 0.00494 -0.0241 0.4751 0.0291 1.250 0.4589 0.01222 0.00442 -0.0242 0.4715 0.0290 1.500 0.4870 0.01184 0.00398 -0.0243 0.4676 0.0289 1.750 0.5149 0.01155 0.00363 -0.0243 0.4637 0.0288 2.000 0.5427 0.01131 0.00336 -0.0244 0.4601 0.0290 2.250 0.5704 0.01111 0.00315 -0.0244 0.4565 0.0292 2.500 0.5981 0.01095 0.00299 -0.0245 0.4527 0.0297 2.750 0.6258 0.01085 0.00287 -0.0246 0.4489 0.0305 3.000 0.6536 0.01077 0.00280 -0.0248 0.4452 0.0315 3.250 0.6816 0.01072 0.00276 -0.0249 0.4413 0.0326 3.500 0.7096 0.01070 0.00274 -0.0251 0.4376 0.0334 3.750 0.7376 0.01072 0.00276 -0.0254 0.4338 0.0341 4.000 0.7657 0.01075 0.00280 -0.0256 0.4301 0.0354 4.250 0.7938 0.01076 0.00283 -0.0259 0.4261 0.0373 4.500 0.8219 0.01081 0.00289 -0.0261 0.4223 0.0385 4.750 0.8499 0.01089 0.00298 -0.0264 0.4187 0.0413 5.000 0.8777 0.01090 0.00312 -0.0267 0.4149 0.0874 5.250 0.9022 0.01033 0.00334 -0.0266 0.4109 0.5773 5.750 1.0140 0.00997 0.00395 -0.0396 0.3833 0.9991 6.000 1.0454 0.01018 0.00414 -0.0408 0.3709 1.0000 6.250 1.0709 0.01043 0.00433 -0.0408 0.3527 1.0000 6.500 1.0959 0.01078 0.00458 -0.0408 0.3312 1.0000 6.750 1.1198 0.01145 0.00504 -0.0409 0.2877 1.0000 7.250 1.1447 0.01671 0.00881 -0.0407 0.0176 1.0000 7.500 1.1653 0.01727 0.00943 -0.0400 0.0142 1.0000 7.750 1.1856 0.01779 0.01002 -0.0393 0.0128 1.0000 8.000 1.2048 0.01838 0.01069 -0.0385 0.0117 1.0000 8.250 1.2225 0.01908 0.01147 -0.0376 0.0107 1.0000 8.500 1.2378 0.01991 0.01238 -0.0365 0.0099 1.0000 8.750 1.2480 0.02108 0.01365 -0.0349 0.0092 1.0000 9.000 1.2569 0.02226 0.01491 -0.0334 0.0087 1.0000 9.250 1.2617 0.02360 0.01633 -0.0319 0.0083 1.0000 9.500 1.2629 0.02524 0.01805 -0.0301 0.0079 1.0000 9.750 1.2662 0.02715 0.02006 -0.0291 0.0076 1.0000 10.000 1.2697 0.02924 0.02223 -0.0285 0.0073 1.0000 10.250 1.2725 0.03149 0.02456 -0.0280 0.0070 1.0000 10.500 1.2746 0.03388 0.02703 -0.0276 0.0068 1.0000 10.750 1.2753 0.03645 0.02967 -0.0272 0.0066 1.0000 11.000 1.2742 0.03923 0.03253 -0.0268 0.0064 1.0000 11.250 1.2707 0.04230 0.03569 -0.0265 0.0062 1.0000 11.500 1.2639 0.04574 0.03922 -0.0261 0.0061 1.0000 11.750 1.2562 0.04931 0.04287 -0.0258 0.0060 1.0000 12.000 1.2559 0.05210 0.04574 -0.0255 0.0059 1.0000 12.250 1.2565 0.05489 0.04864 -0.0254 0.0057 1.0000 12.500 1.2576 0.05770 0.05153 -0.0253 0.0055 1.0000 12.750 1.2587 0.06050 0.05441 -0.0253 0.0053 1.0000 13.000 1.2596 0.06338 0.05736 -0.0253 0.0051 1.0000 13.250 1.2609 0.06622 0.06028 -0.0253 0.0049 1.0000 13.500 1.2617 0.06910 0.06323 -0.0253 0.0048 1.0000 13.750 1.2632 0.07191 0.06611 -0.0253 0.0046 1.0000 14.000 1.2652 0.07469 0.06896 -0.0253 0.0045 1.0000 14.250 1.2676 0.07742 0.07175 -0.0254 0.0044 1.0000 14.500 1.2698 0.08019 0.07459 -0.0255 0.0043 1.0000 14.750 1.2722 0.08293 0.07739 -0.0256 0.0042 1.0000 15.000 1.2745 0.08566 0.08020 -0.0256 0.0041 1.0000 15.250 1.2765 0.08835 0.08294 -0.0255 0.0040 1.0000 15.500 1.2787 0.09071 0.08537 -0.0249 0.0039 1.0000 15.750 1.2816 0.09336 0.08815 -0.0248 0.0038 1.0000 16.000 1.2842 0.09603 0.09095 -0.0246 0.0038 1.0000 16.250 1.2860 0.09884 0.09390 -0.0244 0.0037 1.0000 16.500 1.2865 0.10192 0.09714 -0.0243 0.0036 1.0000 16.750 1.2850 0.10534 0.10072 -0.0244 0.0035 1.0000 17.000 1.2820 0.10914 0.10469 -0.0248 0.0035 1.0000 17.250 1.2772 0.11344 0.10917 -0.0257 0.0034 1.0000 17.500 1.2712 0.11809 0.11399 -0.0269 0.0033 1.0000 17.750 1.2641 0.12309 0.11915 -0.0286 0.0032 1.0000 18.000 1.2561 0.12836 0.12459 -0.0306 0.0031 1.0000 18.250 1.2474 0.13394 0.13032 -0.0330 0.0031 1.0000 18.500 1.2385 0.13975 0.13628 -0.0357 0.0030 1.0000 18.750 1.2281 0.14605 0.14275 -0.0388 0.0030 1.0000 19.000 1.2169 0.15276 0.14963 -0.0423 0.0030 1.0000 19.250 1.2057 0.15971 0.15673 -0.0461 0.0029 1.0000