RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=500,000 Ncrit=5
Details | Polar file |
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Airfoil: RAF 27 AIRFOIL (raf27-il) Reynolds number: 500,000 Max Cl/Cd: 58.45 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf27-il-500000-n5.txt Download as CSV file: xf-raf27-il-500000-n5.csv |
XFOIL Version 6.96 Calculated polar for: RAF 27 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 ------ -------- --------- --------- -------- -------- -------- -15.000 -0.9236 0.09409 0.09144 -0.0096 1.0000 0.0053 -14.750 -0.9710 0.07975 0.07690 -0.0178 1.0000 0.0051 -14.500 -1.0040 0.06880 0.06574 -0.0247 1.0000 0.0050 -14.250 -1.0233 0.06106 0.05783 -0.0298 1.0000 0.0050 -14.000 -1.0425 0.05397 0.05054 -0.0344 1.0000 0.0050 -13.750 -1.0530 0.04895 0.04538 -0.0374 1.0000 0.0051 -13.500 -1.0668 0.04411 0.04033 -0.0395 1.0000 0.0051 -13.250 -1.0736 0.04068 0.03674 -0.0403 1.0000 0.0051 -13.000 -1.0805 0.03764 0.03353 -0.0402 1.0000 0.0052 -12.750 -1.0827 0.03541 0.03116 -0.0393 1.0000 0.0053 -12.500 -1.0859 0.03329 0.02887 -0.0376 1.0000 0.0054 -12.250 -1.0881 0.03143 0.02685 -0.0353 1.0000 0.0054 -12.000 -1.0873 0.02995 0.02523 -0.0326 1.0000 0.0055 -11.750 -1.0851 0.02867 0.02380 -0.0296 1.0000 0.0057 -11.500 -1.0827 0.02739 0.02235 -0.0263 1.0000 0.0058 -11.250 -1.0740 0.02624 0.02106 -0.0240 1.0000 0.0060 -11.000 -1.0618 0.02529 0.01997 -0.0220 1.0000 0.0063 -10.750 -1.0499 0.02424 0.01877 -0.0199 1.0000 0.0064 -10.500 -1.0395 0.02300 0.01738 -0.0175 1.0000 0.0067 -10.250 -1.0284 0.02181 0.01608 -0.0152 1.0000 0.0069 -10.000 -1.0128 0.02101 0.01521 -0.0135 1.0000 0.0073 -9.750 -0.9968 0.02020 0.01431 -0.0117 1.0000 0.0076 -9.500 -0.9800 0.01946 0.01348 -0.0101 1.0000 0.0079 -9.250 -0.9628 0.01873 0.01266 -0.0084 1.0000 0.0083 -9.000 -0.9453 0.01803 0.01182 -0.0067 1.0000 0.0087 -8.750 -0.9272 0.01737 0.01107 -0.0051 1.0000 0.0091 -8.500 -0.9091 0.01672 0.01033 -0.0035 1.0000 0.0095 -8.250 -0.8917 0.01598 0.00954 -0.0017 1.0000 0.0105 -8.000 -0.8721 0.01548 0.00901 -0.0003 1.0000 0.0115 -7.750 -0.8523 0.01501 0.00848 0.0011 1.0000 0.0124 -7.500 -0.8324 0.01455 0.00795 0.0025 1.0000 0.0134 -7.250 -0.8132 0.01401 0.00735 0.0041 1.0000 0.0148 -7.000 -0.7932 0.01358 0.00691 0.0055 1.0000 0.0171 -6.750 -0.7724 0.01323 0.00653 0.0068 1.0000 0.0192 -6.500 -0.7518 0.01288 0.00615 0.0082 1.0000 0.0217 -6.250 -0.7314 0.01252 0.00578 0.0095 1.0000 0.0249 -6.000 -0.7103 0.01225 0.00548 0.0108 1.0000 0.0279 -5.750 -0.6807 0.01195 0.00513 0.0102 0.9985 0.0308 -5.500 -0.6486 0.01157 0.00474 0.0090 0.9959 0.0349 -5.250 -0.6166 0.01129 0.00442 0.0079 0.9932 0.0387 -5.000 -0.5843 0.01093 0.00409 0.0068 0.9895 0.0455 -4.750 -0.5492 0.01056 0.00378 0.0050 0.9857 0.0595 -4.500 -0.5175 0.01021 0.00349 0.0040 0.9796 0.0773 -4.250 -0.4841 0.00986 0.00320 0.0026 0.9753 0.0965 -4.000 -0.4560 0.00948 0.00294 0.0024 0.9685 0.1233 -3.750 -0.4246 0.00902 0.00267 0.0014 0.9636 0.1724 -3.500 -0.3959 0.00864 0.00246 0.0010 0.9557 0.2178 -3.250 -0.3618 0.00829 0.00227 -0.0006 0.9501 0.2578 -3.000 -0.3308 0.00797 0.00208 -0.0014 0.9411 0.2973 -2.750 -0.2965 0.00768 0.00192 -0.0030 0.9326 0.3352 -2.500 -0.2628 0.00739 0.00176 -0.0043 0.9217 0.3779 -2.250 -0.2320 0.00703 0.00162 -0.0051 0.9077 0.4433 -1.750 -0.1755 0.00658 0.00141 -0.0052 0.8723 0.5348 -1.500 -0.1495 0.00645 0.00134 -0.0047 0.8495 0.5705 -1.250 -0.1246 0.00637 0.00128 -0.0039 0.8240 0.6024 -1.000 -0.1001 0.00632 0.00124 -0.0030 0.7993 0.6334 -0.750 -0.0751 0.00632 0.00120 -0.0022 0.7762 0.6564 -0.500 -0.0502 0.00632 0.00118 -0.0014 0.7531 0.6759 -0.250 -0.0253 0.00633 0.00116 -0.0007 0.7319 0.6948 0.000 0.0000 0.00633 0.00116 0.0000 0.7133 0.7129 0.250 0.0252 0.00633 0.00116 0.0007 0.6946 0.7319 0.500 0.0502 0.00632 0.00118 0.0014 0.6760 0.7531 0.750 0.0751 0.00632 0.00120 0.0022 0.6566 0.7761 1.000 0.1000 0.00632 0.00124 0.0030 0.6336 0.7998 1.250 0.1245 0.00637 0.00128 0.0039 0.6024 0.8240 1.750 0.1756 0.00658 0.00141 0.0052 0.5360 0.8723 2.250 0.2320 0.00702 0.00162 0.0051 0.4442 0.9077 2.500 0.2629 0.00738 0.00176 0.0043 0.3792 0.9217 2.750 0.2965 0.00768 0.00191 0.0029 0.3361 0.9326 3.000 0.3308 0.00796 0.00208 0.0014 0.3003 0.9411 3.250 0.3618 0.00828 0.00226 0.0006 0.2598 0.9501 3.500 0.3958 0.00864 0.00246 -0.0010 0.2176 0.9557 3.750 0.4247 0.00901 0.00267 -0.0014 0.1742 0.9636 4.000 0.4560 0.00948 0.00294 -0.0024 0.1227 0.9685 4.250 0.4842 0.00986 0.00321 -0.0026 0.0960 0.9754 4.500 0.5175 0.01021 0.00349 -0.0040 0.0771 0.9797 4.750 0.5492 0.01056 0.00379 -0.0050 0.0594 0.9858 5.000 0.5843 0.01094 0.00409 -0.0068 0.0452 0.9895 5.250 0.6167 0.01128 0.00442 -0.0080 0.0387 0.9933 5.500 0.6488 0.01157 0.00474 -0.0091 0.0348 0.9960 5.750 0.6807 0.01196 0.00514 -0.0102 0.0303 0.9986 6.000 0.7101 0.01224 0.00547 -0.0108 0.0278 1.0000 6.250 0.7312 0.01251 0.00578 -0.0095 0.0249 1.0000 6.500 0.7515 0.01288 0.00614 -0.0081 0.0218 1.0000 6.750 0.7721 0.01324 0.00654 -0.0068 0.0193 1.0000 7.000 0.7929 0.01358 0.00691 -0.0055 0.0170 1.0000 7.250 0.8130 0.01401 0.00736 -0.0041 0.0148 1.0000 7.500 0.8321 0.01456 0.00796 -0.0025 0.0134 1.0000 7.750 0.8521 0.01501 0.00848 -0.0011 0.0125 1.0000 8.000 0.8720 0.01548 0.00900 0.0003 0.0115 1.0000 8.250 0.8916 0.01597 0.00953 0.0017 0.0106 1.0000 8.500 0.9092 0.01669 0.01030 0.0035 0.0095 1.0000 8.750 0.9271 0.01737 0.01107 0.0051 0.0091 1.0000 9.000 0.9454 0.01801 0.01181 0.0067 0.0087 1.0000 9.250 0.9629 0.01872 0.01264 0.0084 0.0083 1.0000 9.500 0.9800 0.01947 0.01349 0.0101 0.0079 1.0000 9.750 0.9967 0.02023 0.01434 0.0117 0.0076 1.0000 10.000 1.0130 0.02101 0.01520 0.0134 0.0073 1.0000 10.250 1.0284 0.02183 0.01611 0.0152 0.0070 1.0000 10.500 1.0408 0.02290 0.01729 0.0173 0.0067 1.0000 10.750 1.0509 0.02418 0.01870 0.0197 0.0064 1.0000 11.000 1.0629 0.02523 0.01989 0.0218 0.0063 1.0000 11.250 1.0751 0.02618 0.02099 0.0238 0.0060 1.0000 11.500 1.0832 0.02740 0.02237 0.0262 0.0058 1.0000 11.750 1.0848 0.02876 0.02390 0.0296 0.0058 1.0000 12.000 1.0870 0.03004 0.02533 0.0326 0.0056 1.0000 12.250 1.0867 0.03163 0.02708 0.0354 0.0055 1.0000 12.500 1.0852 0.03345 0.02905 0.0376 0.0054 1.0000 12.750 1.0846 0.03533 0.03107 0.0391 0.0053 1.0000 13.000 1.0773 0.03811 0.03404 0.0401 0.0052 1.0000 13.250 1.0746 0.04071 0.03678 0.0401 0.0051 1.0000 13.500 1.0671 0.04424 0.04048 0.0393 0.0051 1.0000 13.750 1.0564 0.04868 0.04509 0.0373 0.0051 1.0000 14.000 1.0462 0.05366 0.05022 0.0343 0.0050 1.0000 14.250 1.0303 0.06014 0.05688 0.0301 0.0050 1.0000 14.500 1.0001 0.06993 0.06690 0.0236 0.0051 1.0000 14.750 0.9644 0.08152 0.07871 0.0164 0.0052 1.0000 15.000 0.9255 0.09415 0.09151 0.0092 0.0053 1.0000 |
Polar data table (+)
Polar graphs
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