XFOIL Version 6.96 Calculated polar for: GOE 620 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.6728 0.07496 0.07225 -0.1074 0.9947 0.0317 -16.500 -0.6913 0.06687 0.06401 -0.1152 0.9930 0.0320 -16.250 -0.7104 0.05985 0.05684 -0.1215 0.9902 0.0321 -16.000 -0.7184 0.05414 0.05099 -0.1275 0.9873 0.0323 -15.750 -0.7212 0.04894 0.04566 -0.1336 0.9844 0.0324 -15.500 -0.7181 0.04421 0.04082 -0.1398 0.9820 0.0325 -15.250 -0.7137 0.04008 0.03657 -0.1450 0.9783 0.0326 -15.000 -0.7162 0.03548 0.03183 -0.1500 0.9718 0.0329 -14.750 -0.7042 0.03176 0.02801 -0.1557 0.9678 0.0332 -14.500 -0.6899 0.02892 0.02509 -0.1601 0.9596 0.0335 -14.250 -0.6606 0.02662 0.02272 -0.1662 0.9544 0.0339 -14.000 -0.6280 0.02457 0.02059 -0.1725 0.9486 0.0342 -13.750 -0.5968 0.02300 0.01891 -0.1773 0.9400 0.0345 -13.500 -0.5704 0.02183 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0.00802 0.00227 -0.1209 0.5596 0.3477 1.000 0.6896 0.00806 0.00232 -0.1191 0.5507 0.3672 1.250 0.7094 0.00811 0.00239 -0.1173 0.5417 0.3865 1.500 0.7283 0.00819 0.00248 -0.1155 0.5326 0.4057 1.750 0.7471 0.00828 0.00258 -0.1136 0.5231 0.4262 2.000 0.7663 0.00836 0.00269 -0.1118 0.5142 0.4523 2.250 0.7852 0.00843 0.00282 -0.1099 0.5058 0.4859 2.500 0.8038 0.00851 0.00296 -0.1081 0.4986 0.5206 2.750 0.8239 0.00856 0.00309 -0.1065 0.4918 0.5568 3.000 0.8408 0.00867 0.00325 -0.1043 0.4843 0.5927 3.250 0.8605 0.00869 0.00338 -0.1027 0.4779 0.6360 3.500 0.9898 0.00842 0.00384 -0.1250 0.4642 0.9840 3.750 1.0094 0.00862 0.00401 -0.1233 0.4573 1.0000 4.000 1.0261 0.00883 0.00416 -0.1211 0.4495 1.0000 4.250 1.0459 0.00900 0.00430 -0.1196 0.4429 1.0000 4.500 1.0646 0.00920 0.00446 -0.1178 0.4347 1.0000 4.750 1.0827 0.00943 0.00464 -0.1160 0.4275 1.0000 5.000 1.1025 0.00963 0.00482 -0.1145 0.4197 1.0000 5.250 1.1198 0.00991 0.00505 -0.1127 0.4115 1.0000 5.500 1.1399 0.01013 0.00524 -0.1113 0.4038 1.0000 6.000 1.1763 0.01071 0.00575 -0.1081 0.3860 1.0000 6.250 1.1921 0.01110 0.00607 -0.1061 0.3756 1.0000 6.500 1.2102 0.01144 0.00637 -0.1046 0.3654 1.0000 6.750 1.2273 0.01183 0.00672 -0.1029 0.3561 1.0000 7.000 1.2428 0.01228 0.00712 -0.1010 0.3449 1.0000 7.250 1.2599 0.01270 0.00750 -0.0995 0.3342 1.0000 7.500 1.2746 0.01323 0.00797 -0.0976 0.3238 1.0000 7.750 1.2909 0.01372 0.00843 -0.0960 0.3135 1.0000 8.000 1.3060 0.01428 0.00894 -0.0943 0.3035 1.0000 8.500 1.3357 0.01548 0.01006 -0.0910 0.2843 1.0000 9.000 1.3656 0.01674 0.01127 -0.0880 0.2689 1.0000 9.250 1.3787 0.01750 0.01199 -0.0863 0.2611 1.0000 9.500 1.3946 0.01813 0.01261 -0.0850 0.2549 1.0000 9.750 1.4081 0.01890 0.01336 -0.0835 0.2480 1.0000 10.000 1.4221 0.01967 0.01411 -0.0821 0.2422 1.0000 10.250 1.4381 0.02033 0.01479 -0.0810 0.2382 1.0000 10.500 1.4520 0.02114 0.01559 -0.0797 0.2326 1.0000 10.750 1.4640 0.02208 0.01652 -0.0782 0.2271 1.0000 11.000 1.4799 0.02280 0.01725 -0.0772 0.2228 1.0000 11.250 1.4927 0.02373 0.01818 -0.0759 0.2175 1.0000 11.500 1.5037 0.02479 0.01922 -0.0745 0.2113 1.0000 11.750 1.5157 0.02580 0.02023 -0.0732 0.2033 1.0000 12.000 1.5240 0.02709 0.02148 -0.0717 0.1925 1.0000 12.250 1.5298 0.02859 0.02292 -0.0700 0.1797 1.0000 12.500 1.5234 0.03099 0.02515 -0.0674 0.1521 1.0000 12.750 1.5174 0.03346 0.02750 -0.0651 0.1349 1.0000 13.000 1.5237 0.03506 0.02910 -0.0637 0.1300 1.0000 13.250 1.5310 0.03662 0.03068 -0.0625 0.1272 1.0000 13.500 1.5382 0.03820 0.03228 -0.0614 0.1249 1.0000 13.750 1.5429 0.04003 0.03412 -0.0602 0.1219 1.0000 14.000 1.5504 0.04165 0.03577 -0.0592 0.1203 1.0000 14.250 1.5556 0.04351 0.03767 -0.0582 0.1181 1.0000 14.500 1.5654 0.04496 0.03917 -0.0574 0.1171 1.0000 14.750 1.5739 0.04655 0.04081 -0.0567 0.1160 1.0000 15.000 1.5806 0.04835 0.04266 -0.0559 0.1147 1.0000 15.250 1.5873 0.05014 0.04449 -0.0551 0.1137 1.0000 15.500 1.5917 0.05221 0.04661 -0.0544 0.1124 1.0000 15.750 1.5957 0.05431 0.04876 -0.0536 0.1111 1.0000 16.000 1.5985 0.05658 0.05107 -0.0529 0.1099 1.0000 16.250 1.5989 0.05912 0.05366 -0.0522 0.1083 1.0000 16.500 1.5989 0.06175 0.05634 -0.0516 0.1068 1.0000 16.750 1.6072 0.06354 0.05820 -0.0513 0.1062 1.0000 17.000 1.6141 0.06547 0.06019 -0.0509 0.1055 1.0000 17.250 1.6201 0.06749 0.06228 -0.0506 0.1047 1.0000 17.500 1.6249 0.06967 0.06452 -0.0503 0.1037 1.0000 17.750 1.6292 0.07192 0.06683 -0.0501 0.1026 1.0000 18.000 1.6313 0.07444 0.06940 -0.0498 0.1012 1.0000 18.250 1.6318 0.07717 0.07218 -0.0497 0.1000 1.0000 18.500 1.6307 0.08008 0.07513 -0.0495 0.0986 1.0000 18.750 1.6262 0.08342 0.07853 -0.0494 0.0970 1.0000 19.000 1.6283 0.08598 0.08115 -0.0494 0.0957 1.0000