XFOIL Version 6.96 Calculated polar for: E184 (8.33%) 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.9883 0.04151 0.03971 0.0044 1.0000 0.0044 -10.000 -1.0108 0.03281 0.03036 0.0057 1.0000 0.0046 -9.750 -1.0002 0.03117 0.02843 0.0075 0.9050 0.0047 -9.500 -0.9841 0.02998 0.02703 0.0087 0.8767 0.0048 -9.250 -0.9634 0.02939 0.02631 0.0093 0.8551 0.0050 -9.000 -0.9435 0.02840 0.02514 0.0100 0.8369 0.0051 -8.750 -0.9228 0.02741 0.02398 0.0105 0.8208 0.0052 -8.500 -0.9021 0.02627 0.02262 0.0111 0.8066 0.0054 -8.250 -0.8799 0.02539 0.02158 0.0116 0.7938 0.0056 -8.000 -0.8581 0.02429 0.02029 0.0122 0.7820 0.0059 -7.750 -0.8365 0.02296 0.01874 0.0128 0.7712 0.0062 -7.500 -0.8148 0.02146 0.01699 0.0135 0.7614 0.0065 -7.250 -0.7927 0.01998 0.01525 0.0142 0.7521 0.0067 -7.000 -0.7695 0.01868 0.01373 0.0149 0.7434 0.0069 -6.750 -0.7457 0.01754 0.01236 0.0155 0.7354 0.0070 -6.500 -0.7213 0.01651 0.01115 0.0160 0.7275 0.0072 -6.250 -0.6959 0.01583 0.01033 0.0164 0.7203 0.0074 -6.000 -0.6701 0.01525 0.00964 0.0167 0.7129 0.0076 -5.750 -0.6442 0.01465 0.00891 0.0171 0.7064 0.0078 -5.500 -0.6183 0.01403 0.00818 0.0174 0.6997 0.0079 -5.250 -0.5921 0.01351 0.00755 0.0177 0.6936 0.0080 -5.000 -0.5697 0.01184 0.00566 0.0187 0.6876 0.0088 -4.500 -0.5173 0.01085 0.00450 0.0194 0.6761 0.0096 -4.250 -0.4906 0.01049 0.00406 0.0197 0.6703 0.0099 -4.000 -0.4638 0.01016 0.00367 0.0199 0.6651 0.0102 -3.750 -0.4368 0.00984 0.00329 0.0201 0.6595 0.0104 -3.500 -0.4096 0.00958 0.00296 0.0203 0.6543 0.0106 -3.250 -0.3823 0.00932 0.00264 0.0205 0.6492 0.0110 -3.000 -0.3549 0.00911 0.00238 0.0206 0.6439 0.0114 -2.750 -0.3274 0.00891 0.00212 0.0208 0.6391 0.0116 -2.500 -0.2998 0.00872 0.00189 0.0209 0.6340 0.0119 -2.250 -0.2721 0.00858 0.00170 0.0210 0.6287 0.0123 -2.000 -0.2443 0.00844 0.00152 0.0211 0.6240 0.0130 -1.750 -0.2164 0.00832 0.00137 0.0212 0.6189 0.0158 -1.500 -0.1892 0.00808 0.00123 0.0213 0.6137 0.0408 -1.250 -0.1620 0.00783 0.00111 0.0214 0.6089 0.0790 -1.000 -0.1349 0.00757 0.00100 0.0215 0.6037 0.1255 -0.500 -0.0814 0.00698 0.00083 0.0218 0.5934 0.2567 -0.250 -0.0560 0.00649 0.00076 0.0221 0.5879 0.3834 0.000 -0.0319 0.00591 0.00069 0.0226 0.5825 0.5401 0.250 -0.0067 0.00556 0.00065 0.0231 0.5752 0.6367 0.500 0.0173 0.00520 0.00062 0.0239 0.5671 0.7362 0.750 0.0400 0.00484 0.00060 0.0252 0.5587 0.8396 1.000 0.0729 0.00465 0.00068 0.0244 0.5490 0.9271 1.250 0.1242 0.00476 0.00077 0.0193 0.5360 0.9586 1.750 0.1894 0.00494 0.00087 0.0174 0.5141 0.9783 2.000 0.2219 0.00505 0.00093 0.0164 0.4989 0.9840 2.250 0.2588 0.00514 0.00097 0.0144 0.4826 0.9877 2.500 0.2935 0.00526 0.00104 0.0128 0.4635 0.9912 2.750 0.3277 0.00542 0.00111 0.0114 0.4366 0.9942 3.000 0.3655 0.00560 0.00118 0.0090 0.4021 0.9964 3.250 0.4015 0.00599 0.00131 0.0069 0.3322 0.9985 3.500 0.4357 0.00676 0.00160 0.0048 0.2148 0.9998 3.750 0.4635 0.00724 0.00182 0.0044 0.1515 1.0000 4.000 0.4899 0.00779 0.00208 0.0042 0.0877 1.0000 4.250 0.5160 0.00819 0.00232 0.0043 0.0520 1.0000 4.500 0.5420 0.00860 0.00259 0.0043 0.0235 1.0000 4.750 0.5680 0.00899 0.00292 0.0045 0.0078 1.0000 5.000 0.5939 0.00925 0.00319 0.0048 0.0060 1.0000 5.250 0.6198 0.00954 0.00353 0.0051 0.0052 1.0000 5.500 0.6455 0.00987 0.00391 0.0054 0.0046 1.0000 5.750 0.6710 0.01015 0.00423 0.0057 0.0044 1.0000 6.000 0.6964 0.01050 0.00462 0.0060 0.0042 1.0000 6.250 0.7216 0.01089 0.00508 0.0064 0.0039 1.0000 6.500 0.7465 0.01131 0.00556 0.0067 0.0037 1.0000 6.750 0.7712 0.01179 0.00609 0.0071 0.0035 1.0000 7.000 0.7955 0.01227 0.00662 0.0075 0.0032 1.0000 7.250 0.8195 0.01279 0.00719 0.0079 0.0030 1.0000 7.500 0.8430 0.01340 0.00786 0.0084 0.0028 1.0000 7.750 0.8658 0.01410 0.00864 0.0090 0.0027 1.0000 8.000 0.8869 0.01508 0.00974 0.0097 0.0025 1.0000 8.250 0.9057 0.01646 0.01126 0.0106 0.0024 1.0000 8.500 0.9213 0.01840 0.01340 0.0119 0.0023 1.0000 8.750 0.9391 0.01979 0.01493 0.0130 0.0023 1.0000 9.000 0.9564 0.02120 0.01649 0.0141 0.0023 1.0000 9.250 0.9730 0.02261 0.01806 0.0153 0.0023 1.0000 9.500 0.9875 0.02424 0.01988 0.0165 0.0023 1.0000 9.750 0.9992 0.02618 0.02202 0.0179 0.0023 1.0000 10.000 1.0086 0.02821 0.02426 0.0195 0.0023 1.0000 10.250 1.0140 0.03045 0.02673 0.0211 0.0023 1.0000 10.500 1.0205 0.03213 0.02859 0.0226 0.0023 1.0000 10.750 1.0252 0.03344 0.03003 0.0243 0.0022 1.0000 11.000 1.0083 0.03656 0.03335 0.0266 0.0023 1.0000 11.250 1.0091 0.03847 0.03539 0.0270 0.0022 1.0000 11.500 0.9973 0.04224 0.03935 0.0266 0.0022 1.0000 11.750 0.9927 0.04546 0.04271 0.0257 0.0022 1.0000 12.000 0.9845 0.04945 0.04685 0.0240 0.0022 1.0000 12.250 0.9589 0.05647 0.05406 0.0203 0.0022 1.0000 12.500 0.9492 0.06168 0.05940 0.0171 0.0022 1.0000 12.750 0.9239 0.07035 0.06824 0.0114 0.0022 1.0000