XFOIL Version 6.96 Calculated polar for: NREL's S834 Airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -0.4955 0.15770 0.15391 -0.0431 1.0000 0.0434 -15.750 -0.6803 0.10053 0.09656 -0.0669 1.0000 0.0229 -15.500 -0.7112 0.09158 0.08748 -0.0715 1.0000 0.0226 -15.250 -0.7383 0.08400 0.07974 -0.0751 1.0000 0.0225 -15.000 -0.7622 0.07752 0.07312 -0.0778 1.0000 0.0222 -14.750 -0.7833 0.07195 0.06740 -0.0798 1.0000 0.0221 -14.500 -0.8051 0.06674 0.06201 -0.0813 1.0000 0.0223 -14.250 -0.8223 0.06265 0.05776 -0.0821 1.0000 0.0226 -14.000 -0.8412 0.05848 0.05341 -0.0821 1.0000 0.0226 -13.750 -0.8559 0.05516 0.04992 -0.0814 1.0000 0.0227 -13.500 -0.8702 0.05274 0.04734 -0.0804 1.0000 0.0232 -13.000 -0.9055 0.04602 0.04030 -0.0762 1.0000 0.0245 -12.750 -0.9154 0.04394 0.03816 -0.0736 1.0000 0.0252 -12.500 -0.9242 0.04235 0.03652 -0.0708 1.0000 0.0259 -12.250 -0.9335 0.04097 0.03508 -0.0675 1.0000 0.0268 -12.000 -0.9437 0.03961 0.03362 -0.0638 1.0000 0.0277 -11.750 -0.9546 0.03847 0.03238 -0.0596 1.0000 0.0288 -11.500 -0.9651 0.03728 0.03106 -0.0552 1.0000 0.0298 -11.250 -0.9756 0.03621 0.02985 -0.0504 1.0000 0.0306 -11.000 -0.9894 0.03553 0.02903 -0.0447 1.0000 0.0314 -10.750 -1.0009 0.03406 0.02740 -0.0394 1.0000 0.0327 -10.500 -1.0069 0.03269 0.02601 -0.0350 1.0000 0.0345 -10.250 -1.0086 0.03193 0.02522 -0.0311 1.0000 0.0366 -10.000 -1.0068 0.03105 0.02424 -0.0275 1.0000 0.0389 -9.750 -0.9973 0.03022 0.02320 -0.0252 0.9993 0.0416 -9.500 -0.9759 0.02855 0.02154 -0.0258 0.9957 0.0466 -9.250 -0.9495 0.02782 0.02065 -0.0266 0.9923 0.0523 -9.000 -0.9307 0.02646 0.01928 -0.0263 0.9882 0.0578 -8.750 -0.9029 0.02595 0.01861 -0.0272 0.9846 0.0653 -8.500 -0.8788 0.02495 0.01767 -0.0278 0.9811 0.0743 -8.250 -0.8601 0.02411 0.01679 -0.0270 0.9762 0.0836 -8.000 -0.8339 0.02343 0.01609 -0.0276 0.9724 0.0956 -7.750 -0.8027 0.02291 0.01559 -0.0293 0.9698 0.1108 -7.500 -0.7873 0.02225 0.01495 -0.0276 0.9639 0.1241 -7.250 -0.7606 0.02175 0.01446 -0.0282 0.9600 0.1413 -7.000 -0.7286 0.02135 0.01407 -0.0297 0.9572 0.1624 -6.750 -0.7105 0.02086 0.01363 -0.0285 0.9518 0.1802 -6.500 -0.6845 0.02051 0.01329 -0.0288 0.9474 0.2032 -6.250 -0.6536 0.02013 0.01301 -0.0301 0.9445 0.2276 -6.000 -0.6269 0.01982 0.01276 -0.0305 0.9406 0.2518 -5.750 -0.6068 0.01951 0.01247 -0.0295 0.9350 0.2754 -5.500 -0.5763 0.01923 0.01224 -0.0306 0.9317 0.3040 -5.250 -0.5414 0.01900 0.01209 -0.0324 0.9294 0.3339 -5.000 -0.5265 0.01873 0.01190 -0.0304 0.9229 0.3569 -4.750 -0.4975 0.01850 0.01174 -0.0310 0.9190 0.3858 -4.500 -0.4634 0.01830 0.01161 -0.0326 0.9165 0.4175 -4.250 -0.4425 0.01814 0.01152 -0.0316 0.9112 0.4440 -4.000 -0.4170 0.01796 0.01142 -0.0315 0.9065 0.4731 -3.750 -0.3840 0.01779 0.01132 -0.0327 0.9037 0.5044 -3.500 -0.3478 0.01763 0.01125 -0.0345 0.9018 0.5374 -3.250 -0.3351 0.01756 0.01126 -0.0318 0.8940 0.5622 -3.000 -0.3034 0.01743 0.01122 -0.0327 0.8908 0.5929 -2.750 -0.2681 0.01730 0.01117 -0.0341 0.8887 0.6247 -2.500 -0.2520 0.01733 0.01130 -0.0320 0.8817 0.6500 -2.250 -0.2221 0.01727 0.01132 -0.0323 0.8779 0.6782 -2.000 -0.1877 0.01721 0.01133 -0.0334 0.8755 0.7056 -1.750 -0.1651 0.01730 0.01149 -0.0323 0.8702 0.7300 -1.500 -0.1409 0.01738 0.01161 -0.0314 0.8648 0.7535 -1.250 -0.1075 0.01739 0.01167 -0.0321 0.8621 0.7744 -1.000 -0.0712 0.01740 0.01171 -0.0332 0.8604 0.7932 -0.750 -0.0612 0.01775 0.01207 -0.0297 0.8513 0.8107 -0.500 -0.0288 0.01779 0.01212 -0.0301 0.8484 0.8263 -0.250 0.0071 0.01780 0.01213 -0.0310 0.8466 0.8398 0.000 0.0161 0.01817 0.01251 -0.0271 0.8373 0.8545 0.250 0.0480 0.01816 0.01251 -0.0273 0.8345 0.8659 0.500 0.0845 0.01803 0.01237 -0.0282 0.8327 0.8765 0.750 0.1200 0.01786 0.01220 -0.0290 0.8309 0.8875 1.000 0.1270 0.01811 0.01247 -0.0247 0.8206 0.9012 1.250 0.1674 0.01784 0.01220 -0.0263 0.8191 0.9096 1.500 0.2125 0.01749 0.01186 -0.0290 0.8181 0.9170 1.750 0.2653 0.01717 0.01156 -0.0333 0.8173 0.9224 2.000 0.2809 0.01732 0.01174 -0.0308 0.8071 0.9334 2.250 0.3408 0.01692 0.01136 -0.0366 0.8059 0.9370 2.500 0.3967 0.01645 0.01092 -0.0417 0.8043 0.9416 2.750 0.4470 0.01630 0.01082 -0.0460 0.7976 0.9446 3.000 0.5082 0.01589 0.01046 -0.0524 0.7930 0.9462 3.250 0.5760 0.01533 0.00996 -0.0600 0.7892 0.9468 3.500 0.6040 0.01519 0.00986 -0.0599 0.7784 0.9553 3.750 0.6570 0.01486 0.00961 -0.0648 0.7689 0.9576 4.000 0.7092 0.01448 0.00926 -0.0694 0.7586 0.9603 4.250 0.7496 0.01421 0.00903 -0.0718 0.7458 0.9656 4.500 0.7848 0.01402 0.00890 -0.0732 0.7296 0.9713 4.750 0.8216 0.01384 0.00879 -0.0750 0.7104 0.9767 5.000 0.8560 0.01366 0.00862 -0.0762 0.6894 0.9824 5.250 0.8935 0.01351 0.00847 -0.0783 0.6617 0.9871 5.500 0.9239 0.01349 0.00840 -0.0788 0.6274 0.9931 5.750 0.9565 0.01355 0.00837 -0.0800 0.5840 0.9982 6.000 0.9667 0.01381 0.00846 -0.0768 0.5413 1.0000 6.250 0.9618 0.01414 0.00862 -0.0706 0.5001 1.0000 6.500 0.9520 0.01451 0.00879 -0.0635 0.4606 1.0000 6.750 0.9361 0.01481 0.00893 -0.0553 0.4294 1.0000 7.000 0.9177 0.01510 0.00907 -0.0466 0.4009 1.0000 7.250 0.9025 0.01540 0.00924 -0.0388 0.3735 1.0000 7.500 0.8895 0.01575 0.00946 -0.0314 0.3461 1.0000 7.750 0.8805 0.01617 0.00974 -0.0250 0.3175 1.0000 8.000 0.8792 0.01679 0.01020 -0.0203 0.2858 1.0000 8.250 0.8831 0.01755 0.01079 -0.0167 0.2514 1.0000 8.500 0.8891 0.01841 0.01147 -0.0137 0.2174 1.0000 8.750 0.8967 0.01932 0.01225 -0.0112 0.1868 1.0000 9.000 0.9049 0.02030 0.01307 -0.0088 0.1579 1.0000 9.250 0.9136 0.02133 0.01397 -0.0065 0.1317 1.0000 9.500 0.9225 0.02243 0.01496 -0.0044 0.1096 1.0000 9.750 0.9306 0.02362 0.01604 -0.0023 0.0914 1.0000 10.000 0.9381 0.02490 0.01724 -0.0001 0.0773 1.0000 10.250 0.9464 0.02619 0.01850 0.0019 0.0654 1.0000 10.500 0.9550 0.02751 0.01984 0.0038 0.0561 1.0000 10.750 0.9606 0.02913 0.02144 0.0059 0.0492 1.0000 11.000 0.9720 0.03030 0.02270 0.0073 0.0435 1.0000 11.250 0.9773 0.03215 0.02454 0.0092 0.0384 1.0000 11.500 0.9888 0.03333 0.02582 0.0104 0.0339 1.0000 11.750 0.9945 0.03522 0.02768 0.0120 0.0304 1.0000 12.000 1.0063 0.03698 0.02957 0.0133 0.0284 1.0000 12.250 1.0178 0.03858 0.03130 0.0145 0.0262 1.0000 12.500 1.0267 0.04022 0.03302 0.0157 0.0242 1.0000 12.750 1.0352 0.04219 0.03500 0.0167 0.0224 1.0000 13.000 1.0454 0.04485 0.03785 0.0178 0.0210 1.0000 13.250 1.0499 0.04667 0.03987 0.0189 0.0197 1.0000 13.500 1.0571 0.04910 0.04250 0.0199 0.0194 1.0000 13.750 1.0602 0.05161 0.04521 0.0209 0.0186 1.0000 14.000 1.0610 0.05454 0.04839 0.0218 0.0184 1.0000 14.250 1.0588 0.05750 0.05153 0.0225 0.0177 1.0000 14.500 1.0542 0.06097 0.05522 0.0230 0.0176 1.0000 14.750 1.0473 0.06456 0.05901 0.0231 0.0173 1.0000 15.000 1.0359 0.06899 0.06370 0.0229 0.0173 1.0000 15.250 1.0223 0.07390 0.06885 0.0222 0.0174 1.0000 15.500 1.0044 0.07956 0.07477 0.0208 0.0175 1.0000 15.750 0.9822 0.08625 0.08174 0.0183 0.0176 1.0000 16.000 0.9576 0.09385 0.08959 0.0148 0.0178 1.0000 16.250 0.9270 0.10328 0.09929 0.0096 0.0182 1.0000 16.500 0.8965 0.11373 0.10997 0.0031 0.0188 1.0000 16.750 0.8579 0.12740 0.12383 -0.0057 0.0192 1.0000 17.000 0.8080 0.14623 0.14281 -0.0171 0.0203 1.0000 17.250 0.7759 0.16152 0.15808 -0.0247 0.0213 1.0000