XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1094R8 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.250 -0.5162 0.08550 0.08327 -0.0068 1.0000 0.0258 -7.000 -0.5160 0.08099 0.07879 -0.0106 1.0000 0.0262 -6.750 -0.5167 0.07541 0.07322 -0.0173 1.0000 0.0266 -6.500 -0.5126 0.06923 0.06697 -0.0236 1.0000 0.0274 -6.250 -0.5172 0.05604 0.05336 -0.0334 1.0000 0.0287 -6.000 -0.5045 0.05365 0.05098 -0.0334 1.0000 0.0290 -5.750 -0.4900 0.05147 0.04878 -0.0334 1.0000 0.0293 -5.500 -0.4748 0.04913 0.04639 -0.0335 1.0000 0.0297 -5.250 -0.4599 0.04648 0.04365 -0.0334 1.0000 0.0303 -5.000 -0.4499 0.04082 0.03724 -0.0318 1.0000 0.0335 -4.750 -0.4434 0.03665 0.03309 -0.0304 1.0000 0.0340 -4.500 -0.4320 0.03512 0.03156 -0.0285 1.0000 0.0344 -4.250 -0.4111 0.03354 0.02995 -0.0282 0.9988 0.0349 -4.000 -0.3750 0.03136 0.02763 -0.0306 0.9955 0.0362 -3.750 -0.3370 0.02705 0.02275 -0.0328 0.9912 0.0403 -3.500 -0.2987 0.02533 0.02100 -0.0353 0.9871 0.0413 -3.250 -0.2628 0.01765 0.01196 -0.0346 0.9839 0.0286 -3.000 -0.2301 0.01571 0.00990 -0.0352 0.9787 0.0281 -2.750 -0.1964 0.01441 0.00845 -0.0357 0.9735 0.0281 -2.500 -0.1668 0.01358 0.00750 -0.0354 0.9649 0.0283 -2.250 -0.1404 0.01266 0.00651 -0.0345 0.9549 0.0287 -2.000 -0.1159 0.01187 0.00573 -0.0332 0.9438 0.0295 -1.750 -0.0920 0.01140 0.00527 -0.0317 0.9319 0.0304 -1.500 -0.0686 0.01099 0.00483 -0.0300 0.9172 0.0313 -1.250 -0.0449 0.01063 0.00442 -0.0284 0.8988 0.0326 -1.000 -0.0205 0.01020 0.00394 -0.0269 0.8791 0.0342 -0.750 0.0049 0.00989 0.00361 -0.0258 0.8601 0.0363 -0.500 0.0311 0.00965 0.00331 -0.0247 0.8397 0.0385 -0.250 0.0574 0.00934 0.00294 -0.0237 0.8178 0.0412 0.000 0.0845 0.00919 0.00273 -0.0229 0.7921 0.0453 0.250 0.1114 0.00901 0.00248 -0.0221 0.7621 0.0520 0.500 0.1385 0.00883 0.00225 -0.0213 0.7246 0.0709 0.750 0.1647 0.00823 0.00207 -0.0209 0.6811 0.2386 1.000 0.1851 0.00660 0.00203 -0.0197 0.6326 0.7622 1.250 0.2044 0.00656 0.00212 -0.0170 0.5786 0.8733 1.500 0.2229 0.00675 0.00218 -0.0140 0.5244 0.9294 1.750 0.2455 0.00699 0.00220 -0.0121 0.4740 0.9645 2.000 0.2884 0.00728 0.00222 -0.0145 0.4196 0.9895 2.250 0.3389 0.00764 0.00229 -0.0186 0.3689 1.0000 2.500 0.3630 0.00784 0.00231 -0.0177 0.3375 1.0000 2.750 0.3873 0.00805 0.00234 -0.0167 0.3099 1.0000 3.000 0.4118 0.00825 0.00239 -0.0157 0.2833 1.0000 3.250 0.4368 0.00848 0.00246 -0.0149 0.2562 1.0000 3.500 0.4623 0.00874 0.00255 -0.0142 0.2284 1.0000 3.750 0.4885 0.00901 0.00266 -0.0135 0.2041 1.0000 4.000 0.5150 0.00929 0.00280 -0.0130 0.1860 1.0000 4.250 0.5420 0.00954 0.00296 -0.0125 0.1729 1.0000 4.500 0.5691 0.00980 0.00313 -0.0120 0.1627 1.0000 4.750 0.5961 0.01009 0.00333 -0.0115 0.1534 1.0000 5.000 0.6235 0.01031 0.00351 -0.0110 0.1467 1.0000 5.250 0.6506 0.01060 0.00372 -0.0105 0.1399 1.0000 5.500 0.6778 0.01086 0.00396 -0.0101 0.1345 1.0000 5.750 0.7052 0.01109 0.00416 -0.0096 0.1296 1.0000 6.000 0.7319 0.01145 0.00444 -0.0091 0.1243 1.0000 6.250 0.7590 0.01173 0.00472 -0.0086 0.1211 1.0000 6.500 0.7862 0.01197 0.00497 -0.0081 0.1181 1.0000 6.750 0.8132 0.01225 0.00522 -0.0076 0.1151 1.0000 7.000 0.8395 0.01264 0.00557 -0.0070 0.1120 1.0000 7.250 0.8652 0.01313 0.00605 -0.0064 0.1091 1.0000 7.500 0.8922 0.01339 0.00634 -0.0059 0.1076 1.0000 7.750 0.9188 0.01369 0.00666 -0.0053 0.1056 1.0000 8.000 0.9453 0.01399 0.00698 -0.0048 0.1036 1.0000 8.250 0.9714 0.01433 0.00731 -0.0042 0.1016 1.0000 8.500 0.9969 0.01478 0.00775 -0.0036 0.0997 1.0000 8.750 1.0205 0.01560 0.00856 -0.0027 0.0973 1.0000 9.000 1.0463 0.01598 0.00898 -0.0021 0.0965 1.0000 9.250 1.0720 0.01634 0.00940 -0.0015 0.0955 1.0000 9.500 1.0974 0.01676 0.00986 -0.0008 0.0944 1.0000 9.750 1.1226 0.01720 0.01035 -0.0001 0.0932 1.0000 10.000 1.1474 0.01767 0.01086 0.0006 0.0920 1.0000 10.250 1.1720 0.01815 0.01137 0.0013 0.0909 1.0000 10.500 1.1964 0.01863 0.01189 0.0021 0.0898 1.0000 10.750 1.2204 0.01915 0.01242 0.0028 0.0886 1.0000 11.000 1.2434 0.01988 0.01317 0.0037 0.0873 1.0000 11.250 1.2643 0.02124 0.01458 0.0046 0.0858 1.0000 11.500 1.2874 0.02190 0.01532 0.0054 0.0853 1.0000 11.750 1.3106 0.02246 0.01597 0.0063 0.0848 1.0000 12.000 1.3333 0.02309 0.01670 0.0072 0.0842 1.0000 12.250 1.3554 0.02378 0.01748 0.0081 0.0835 1.0000 12.500 1.3770 0.02451 0.01831 0.0091 0.0827 1.0000 12.750 1.3980 0.02528 0.01919 0.0101 0.0820 1.0000 13.000 1.4185 0.02602 0.02002 0.0111 0.0811 1.0000 13.250 1.4388 0.02660 0.02067 0.0122 0.0801 1.0000 13.500 1.4588 0.02715 0.02127 0.0132 0.0791 1.0000 13.750 1.4784 0.02768 0.02183 0.0143 0.0780 1.0000 14.000 1.4967 0.02844 0.02261 0.0155 0.0770 1.0000 14.250 1.5111 0.03012 0.02437 0.0168 0.0757 1.0000 14.500 1.5239 0.03158 0.02598 0.0183 0.0749 1.0000 14.750 1.5383 0.03222 0.02676 0.0198 0.0744 1.0000 15.000 1.5499 0.03301 0.02768 0.0217 0.0737 1.0000 15.250 1.5579 0.03392 0.02872 0.0238 0.0730 1.0000 15.500 1.5646 0.03502 0.02994 0.0258 0.0723 1.0000 15.750 1.5705 0.03622 0.03126 0.0276 0.0716 1.0000 16.000 1.5762 0.03748 0.03264 0.0291 0.0708 1.0000 16.250 1.5821 0.03878 0.03403 0.0303 0.0700 1.0000 16.500 1.5883 0.04015 0.03549 0.0312 0.0693 1.0000 16.750 1.5944 0.04164 0.03704 0.0319 0.0686 1.0000 17.000 1.6004 0.04324 0.03869 0.0324 0.0678 1.0000 17.250 1.6038 0.04527 0.04077 0.0328 0.0671 1.0000 17.500 1.5961 0.04878 0.04439 0.0328 0.0661 1.0000 17.750 1.5882 0.05234 0.04814 0.0319 0.0655 1.0000 18.000 1.5826 0.05582 0.05179 0.0304 0.0651 1.0000 18.250 1.5744 0.05994 0.05608 0.0284 0.0646 1.0000 18.500 1.5617 0.06495 0.06128 0.0256 0.0640 1.0000 18.750 1.5445 0.07092 0.06743 0.0219 0.0634 1.0000 19.000 1.5228 0.07793 0.07462 0.0174 0.0629 1.0000 19.250 1.4932 0.08662 0.08350 0.0117 0.0624 1.0000