XFOIL Version 6.96 Calculated polar for: NACA 16-021 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1016 0.05442 0.04930 -0.1214 0.9854 0.0187 -19.500 -1.0941 0.05238 0.04721 -0.1219 0.9850 0.0191 -19.250 -1.0852 0.05051 0.04528 -0.1223 0.9845 0.0195 -19.000 -1.0751 0.04878 0.04348 -0.1228 0.9840 0.0199 -18.750 -1.0645 0.04709 0.04174 -0.1232 0.9835 0.0204 -18.500 -1.0528 0.04555 0.04014 -0.1235 0.9830 0.0208 -18.250 -1.0450 0.04414 0.03867 -0.1228 0.9816 0.0211 -18.000 -1.0357 0.04284 0.03730 -0.1222 0.9801 0.0214 -17.750 -1.0275 0.04136 0.03577 -0.1216 0.9787 0.0218 -17.500 -1.0174 0.03999 0.03436 -0.1211 0.9775 0.0222 -17.250 -1.0063 0.03869 0.03301 -0.1208 0.9763 0.0227 -17.000 -0.9934 0.03752 0.03181 -0.1205 0.9751 0.0231 -16.750 -0.9802 0.03637 0.03062 -0.1203 0.9741 0.0236 -16.500 -0.9663 0.03532 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0.8454 2.500 0.1339 0.00679 0.00287 0.0308 0.7579 0.8488 2.750 0.1407 0.00687 0.00290 0.0353 0.7421 0.8524 3.000 0.1521 0.00699 0.00297 0.0387 0.7250 0.8551 3.250 0.1675 0.00714 0.00308 0.0412 0.7072 0.8576 3.500 0.1800 0.00733 0.00322 0.0443 0.6861 0.8606 3.750 0.1872 0.00757 0.00338 0.0485 0.6612 0.8641 4.000 0.1926 0.00786 0.00356 0.0531 0.6316 0.8675 4.250 0.1971 0.00824 0.00382 0.0578 0.5994 0.8705 4.500 0.2027 0.00872 0.00417 0.0621 0.5593 0.8736 4.750 0.2067 0.00925 0.00455 0.0666 0.5189 0.8770 5.000 0.2111 0.00980 0.00492 0.0709 0.4707 0.8804 5.250 0.2162 0.01036 0.00529 0.0750 0.4229 0.8835 5.500 0.2200 0.01107 0.00572 0.0792 0.3580 0.8866 5.750 0.2294 0.01169 0.00614 0.0822 0.3038 0.8894 6.000 0.2408 0.01226 0.00652 0.0848 0.2572 0.8921 6.250 0.2561 0.01269 0.00682 0.0866 0.2242 0.8947 6.500 0.2729 0.01307 0.00709 0.0881 0.1980 0.8973 6.750 0.2891 0.01346 0.00737 0.0897 0.1737 0.8998 7.000 0.3073 0.01386 0.00769 0.0909 0.1533 0.9020 7.250 0.3269 0.01422 0.00800 0.0917 0.1376 0.9040 7.500 0.3466 0.01458 0.00832 0.0926 0.1235 0.9061 7.750 0.3665 0.01492 0.00862 0.0934 0.1117 0.9083 8.000 0.3862 0.01525 0.00891 0.0943 0.1017 0.9108 8.250 0.4052 0.01560 0.00923 0.0952 0.0931 0.9132 8.500 0.4238 0.01596 0.00955 0.0962 0.0844 0.9153 8.750 0.4444 0.01632 0.00988 0.0968 0.0769 0.9171 9.000 0.4645 0.01670 0.01025 0.0975 0.0696 0.9190 9.250 0.4841 0.01711 0.01064 0.0982 0.0629 0.9211 9.500 0.5034 0.01750 0.01102 0.0990 0.0576 0.9234 9.750 0.5223 0.01791 0.01141 0.0998 0.0532 0.9257 10.000 0.5411 0.01831 0.01180 0.1007 0.0491 0.9278 10.250 0.5601 0.01870 0.01218 0.1015 0.0461 0.9298 10.500 0.5798 0.01911 0.01260 0.1021 0.0435 0.9316 10.750 0.5986 0.01960 0.01309 0.1028 0.0409 0.9335 11.000 0.6180 0.02004 0.01356 0.1034 0.0394 0.9354 11.250 0.6368 0.02050 0.01404 0.1041 0.0379 0.9374 11.500 0.6551 0.02098 0.01452 0.1049 0.0365 0.9394 11.750 0.6727 0.02148 0.01502 0.1057 0.0352 0.9415 12.000 0.6903 0.02196 0.01554 0.1066 0.0345 0.9436 12.250 0.7083 0.02246 0.01606 0.1073 0.0338 0.9454 12.500 0.7270 0.02300 0.01663 0.1078 0.0329 0.9471 12.750 0.7451 0.02357 0.01722 0.1084 0.0321 0.9488 13.000 0.7619 0.02418 0.01786 0.1092 0.0314 0.9505 13.250 0.7778 0.02483 0.01853 0.1101 0.0306 0.9523 13.500 0.7932 0.02549 0.01921 0.1111 0.0298 0.9543 13.750 0.8096 0.02608 0.01984 0.1119 0.0294 0.9565 14.000 0.8247 0.02671 0.02052 0.1129 0.0290 0.9585 14.250 0.8416 0.02741 0.02125 0.1134 0.0285 0.9599 14.500 0.8584 0.02813 0.02201 0.1139 0.0279 0.9612 14.750 0.8740 0.02891 0.02282 0.1145 0.0273 0.9625 15.000 0.8886 0.02974 0.02368 0.1152 0.0268 0.9640 15.250 0.9026 0.03059 0.02456 0.1160 0.0262 0.9657 15.500 0.9142 0.03157 0.02557 0.1171 0.0256 0.9677 15.750 0.9271 0.03242 0.02647 0.1180 0.0252 0.9697 16.000 0.9400 0.03326 0.02736 0.1189 0.0249 0.9714 16.250 0.9549 0.03425 0.02840 0.1191 0.0245 0.9723 16.500 0.9697 0.03526 0.02945 0.1194 0.0241 0.9732 16.750 0.9840 0.03629 0.03053 0.1196 0.0236 0.9742 17.000 0.9971 0.03744 0.03173 0.1199 0.0231 0.9753 17.250 1.0101 0.03861 0.03293 0.1202 0.0226 0.9764 17.500 1.0211 0.03991 0.03428 0.1205 0.0222 0.9777 17.750 1.0311 0.04128 0.03569 0.1210 0.0217 0.9790 18.000 1.0395 0.04273 0.03719 0.1216 0.0214 0.9803 18.250 1.0486 0.04402 0.03854 0.1223 0.0211 0.9819 18.500 1.0573 0.04546 0.04005 0.1227 0.0208 0.9831 18.750 1.0696 0.04695 0.04159 0.1224 0.0203 0.9836 19.000 1.0800 0.04866 0.04336 0.1220 0.0199 0.9842 19.250 1.0902 0.05040 0.04517 0.1216 0.0195 0.9847