XFOIL Version 6.96 Calculated polar for: NREL's S835 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -1.1903 0.08602 0.08238 -0.0638 1.0000 0.0981 -19.250 -1.1968 0.08287 0.07918 -0.0643 1.0000 0.1001 -19.000 -1.2076 0.07841 0.07469 -0.0663 0.9997 0.1026 -18.750 -1.2089 0.07503 0.07128 -0.0681 0.9992 0.1052 -18.500 -1.2074 0.07185 0.06803 -0.0700 0.9986 0.1073 -18.250 -1.2068 0.06866 0.06480 -0.0719 0.9979 0.1097 -18.000 -1.2139 0.06477 0.06088 -0.0737 0.9972 0.1124 -17.750 -1.2133 0.06182 0.05789 -0.0751 0.9965 0.1149 -17.500 -1.2085 0.05920 0.05521 -0.0768 0.9957 0.1174 -17.250 -1.2079 0.05603 0.05200 -0.0787 0.9948 0.1202 -17.000 -1.2070 0.05291 0.04886 -0.0807 0.9939 0.1231 -16.750 -1.2027 0.05023 0.04613 -0.0824 0.9932 0.1258 -16.500 -1.1896 0.04837 0.04422 -0.0842 0.9926 0.1282 -16.250 -1.1870 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0.00494 -0.1159 0.9074 0.2664 -6.750 -0.4287 0.00955 0.00472 -0.1176 0.9053 0.2692 -6.500 -0.4074 0.00930 0.00450 -0.1167 0.8994 0.2744 -6.250 -0.3811 0.00908 0.00429 -0.1167 0.8942 0.2788 -6.000 -0.3474 0.00889 0.00409 -0.1181 0.8907 0.2834 -5.750 -0.3131 0.00876 0.00392 -0.1196 0.8869 0.2865 -5.500 -0.2909 0.00857 0.00376 -0.1188 0.8798 0.2920 -5.250 -0.2596 0.00840 0.00358 -0.1197 0.8748 0.2976 -5.000 -0.2253 0.00828 0.00343 -0.1212 0.8702 0.3022 -4.750 -0.2012 0.00819 0.00334 -0.1206 0.8633 0.3062 -4.500 -0.1715 0.00803 0.00320 -0.1212 0.8572 0.3126 -4.250 -0.1397 0.00794 0.00308 -0.1221 0.8517 0.3180 -4.000 -0.1142 0.00789 0.00302 -0.1217 0.8451 0.3219 -3.750 -0.0852 0.00777 0.00291 -0.1221 0.8385 0.3284 -3.500 -0.0554 0.00769 0.00282 -0.1226 0.8323 0.3345 -3.250 -0.0291 0.00763 0.00277 -0.1224 0.8253 0.3393 -3.000 -0.0003 0.00756 0.00268 -0.1227 0.8184 0.3449 -2.750 0.0279 0.00749 0.00262 -0.1229 0.8119 0.3515 -2.500 0.0549 0.00744 0.00258 -0.1227 0.8050 0.3570 -2.250 0.0836 0.00742 0.00252 -0.1229 0.7982 0.3621 -2.000 0.1113 0.00735 0.00248 -0.1230 0.7918 0.3688 -1.750 0.1384 0.00731 0.00245 -0.1228 0.7849 0.3748 -1.500 0.1667 0.00731 0.00241 -0.1229 0.7779 0.3797 -1.250 0.1941 0.00725 0.00239 -0.1229 0.7716 0.3868 -1.000 0.2211 0.00722 0.00237 -0.1227 0.7645 0.3928 -0.750 0.2489 0.00724 0.00235 -0.1227 0.7573 0.3976 -0.500 0.2758 0.00719 0.00234 -0.1225 0.7507 0.4042 -0.250 0.3024 0.00717 0.00233 -0.1222 0.7429 0.4109 0.000 0.3290 0.00721 0.00233 -0.1219 0.7346 0.4164 0.250 0.3548 0.00718 0.00233 -0.1214 0.7264 0.4223 0.500 0.3803 0.00719 0.00233 -0.1209 0.7176 0.4286 0.750 0.4061 0.00720 0.00235 -0.1204 0.7096 0.4342 1.000 0.4310 0.00723 0.00236 -0.1197 0.7005 0.4390 1.250 0.4557 0.00723 0.00238 -0.1190 0.6919 0.4461 1.500 0.4793 0.00724 0.00240 -0.1181 0.6828 0.4524 1.750 0.5018 0.00730 0.00242 -0.1169 0.6736 0.4574 2.000 0.5253 0.00730 0.00245 -0.1159 0.6643 0.4636 2.250 0.5471 0.00737 0.00250 -0.1146 0.6541 0.4696 2.500 0.5712 0.00740 0.00255 -0.1137 0.6443 0.4754 2.750 0.5930 0.00751 0.00261 -0.1124 0.6336 0.4806 3.000 0.6174 0.00754 0.00269 -0.1117 0.6228 0.4876 3.250 0.6393 0.00767 0.00279 -0.1104 0.6114 0.4936 3.500 0.6617 0.00779 0.00289 -0.1092 0.5985 0.4987 3.750 0.6840 0.00790 0.00301 -0.1080 0.5847 0.5054 4.000 0.7052 0.00806 0.00314 -0.1066 0.5702 0.5117 4.250 0.7256 0.00825 0.00328 -0.1051 0.5535 0.5174 4.500 0.7457 0.00845 0.00343 -0.1035 0.5346 0.5229 4.750 0.7652 0.00866 0.00361 -0.1018 0.5145 0.5294 5.000 0.7837 0.00893 0.00381 -0.1000 0.4916 0.5354 5.250 0.8022 0.00924 0.00402 -0.0982 0.4663 0.5404 5.500 0.8190 0.00959 0.00428 -0.0961 0.4377 0.5465 5.750 0.8350 0.00997 0.00456 -0.0940 0.4093 0.5524 6.000 0.8494 0.01046 0.00490 -0.0915 0.3741 0.5583 6.250 0.8644 0.01096 0.00524 -0.0893 0.3394 0.5627 6.500 0.8794 0.01145 0.00560 -0.0871 0.3082 0.5694 6.750 0.8953 0.01191 0.00597 -0.0850 0.2824 0.5753 7.000 0.9106 0.01242 0.00637 -0.0829 0.2569 0.5809 7.250 0.9277 0.01288 0.00673 -0.0812 0.2352 0.5860 7.500 0.9442 0.01335 0.00713 -0.0793 0.2141 0.5928 7.750 0.9596 0.01386 0.00757 -0.0773 0.1940 0.5986 8.000 0.9753 0.01440 0.00802 -0.0754 0.1757 0.6041 8.250 0.9908 0.01495 0.00849 -0.0735 0.1577 0.6101 8.500 1.0059 0.01551 0.00899 -0.0716 0.1413 0.6163 8.750 1.0213 0.01608 0.00950 -0.0698 0.1271 0.6222 9.000 1.0363 0.01670 0.01004 -0.0679 0.1129 0.6273 9.250 1.0505 0.01733 0.01063 -0.0660 0.1008 0.6340 9.500 1.0663 0.01791 0.01120 -0.0643 0.0917 0.6402 9.750 1.0815 0.01854 0.01179 -0.0627 0.0827 0.6463 10.000 1.0960 0.01922 0.01243 -0.0609 0.0742 0.6515 10.250 1.1112 0.01986 0.01307 -0.0593 0.0673 0.6585 10.500 1.1260 0.02055 0.01376 -0.0577 0.0610 0.6649 10.750 1.1402 0.02129 0.01447 -0.0560 0.0556 0.6705 11.000 1.1552 0.02200 0.01519 -0.0545 0.0506 0.6767 11.250 1.1690 0.02278 0.01599 -0.0529 0.0460 0.6834 11.500 1.1834 0.02356 0.01678 -0.0514 0.0424 0.6900 11.750 1.1972 0.02440 0.01761 -0.0499 0.0390 0.6954 12.000 1.2097 0.02532 0.01855 -0.0484 0.0359 0.7023 12.250 1.2240 0.02616 0.01943 -0.0470 0.0334 0.7092 12.500 1.2364 0.02714 0.02042 -0.0455 0.0313 0.7153 12.750 1.2494 0.02810 0.02142 -0.0442 0.0292 0.7221 13.000 1.2616 0.02913 0.02249 -0.0428 0.0275 0.7290 13.250 1.2740 0.03019 0.02357 -0.0415 0.0260 0.7357 13.500 1.2848 0.03137 0.02480 -0.0402 0.0245 0.7426 13.750 1.2972 0.03246 0.02594 -0.0390 0.0233 0.7500 14.000 1.3080 0.03372 0.02722 -0.0378 0.0221 0.7566 14.250 1.3173 0.03510 0.02866 -0.0365 0.0211 0.7638 14.500 1.3288 0.03634 0.02996 -0.0355 0.0202 0.7717 14.750 1.3381 0.03781 0.03147 -0.0344 0.0192 0.7789 15.000 1.3453 0.03946 0.03318 -0.0333 0.0184 0.7866 15.250 1.3553 0.04092 0.03471 -0.0324 0.0177 0.7946 15.500 1.3646 0.04247 0.03633 -0.0315 0.0170 0.8026 15.750 1.3716 0.04426 0.03818 -0.0307 0.0163 0.8116 16.000 1.3763 0.04634 0.04032 -0.0298 0.0157 0.8198 16.250 1.3832 0.04823 0.04229 -0.0292 0.0152 0.8290 16.500 1.3915 0.05002 0.04416 -0.0286 0.0148 0.8385 16.750 1.3973 0.05208 0.04630 -0.0281 0.0143 0.8499 17.000 1.4021 0.05428 0.04859 -0.0276 0.0139 0.8616 17.250 1.4056 0.05663 0.05103 -0.0271 0.0135 0.8758 17.500 1.4040 0.05946 0.05399 -0.0266 0.0131 0.8983 17.750 1.4030 0.06210 0.05682 -0.0262 0.0128 1.0000 18.000 1.4078 0.06470 0.05948 -0.0264 0.0126 1.0000 18.250 1.4094 0.06773 0.06259 -0.0268 0.0125 1.0000 18.500 1.4131 0.07057 0.06549 -0.0272 0.0122 1.0000 18.750 1.4137 0.07386 0.06885 -0.0278 0.0120 1.0000 19.000 1.4135 0.07733 0.07239 -0.0286 0.0118 1.0000 19.250 1.4121 0.08102 0.07616 -0.0295 0.0116 1.0000