XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1094 R8 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5385 0.08673 0.08514 0.0023 1.0000 0.0178 -8.250 -0.5383 0.08219 0.08061 -0.0014 1.0000 0.0180 -8.000 -0.5416 0.07637 0.07481 -0.0084 1.0000 0.0183 -7.750 -0.5393 0.06922 0.06760 -0.0164 1.0000 0.0189 -7.500 -0.5531 0.05147 0.04944 -0.0279 1.0000 0.0197 -7.250 -0.5398 0.04869 0.04660 -0.0286 1.0000 0.0198 -7.000 -0.5242 0.04615 0.04398 -0.0290 1.0000 0.0200 -6.750 -0.5078 0.04361 0.04136 -0.0293 1.0000 0.0201 -6.500 -0.4918 0.04106 0.03871 -0.0292 1.0000 0.0204 -6.250 -0.4981 0.02330 0.01957 -0.0280 0.9969 0.0200 -6.000 -0.4682 0.02012 0.01610 -0.0292 0.9940 0.0188 -5.750 -0.4367 0.01692 0.01244 -0.0305 0.9908 0.0186 -5.500 -0.4043 0.01511 0.01035 -0.0314 0.9841 0.0186 -5.250 -0.3743 0.01393 0.00898 -0.0317 0.9739 0.0186 -5.000 -0.3501 0.01308 0.00801 -0.0306 0.9626 0.0187 -4.750 -0.3258 0.01239 0.00720 -0.0296 0.9541 0.0189 -4.500 -0.3006 0.01179 0.00653 -0.0287 0.9443 0.0191 -4.250 -0.2753 0.01142 0.00607 -0.0278 0.9352 0.0194 -4.000 -0.2499 0.01084 0.00541 -0.0270 0.9244 0.0197 -3.750 -0.2246 0.01018 0.00473 -0.0262 0.9138 0.0201 -3.500 -0.1985 0.00982 0.00435 -0.0255 0.9028 0.0206 -3.250 -0.1716 0.00951 0.00401 -0.0250 0.8891 0.0211 -3.000 -0.1450 0.00924 0.00368 -0.0244 0.8718 0.0218 -2.750 -0.1179 0.00904 0.00339 -0.0239 0.8519 0.0224 -2.500 -0.0910 0.00870 0.00298 -0.0234 0.8296 0.0232 -2.250 -0.0633 0.00852 0.00274 -0.0231 0.8079 0.0242 -2.000 -0.0354 0.00840 0.00252 -0.0228 0.7843 0.0253 -1.750 -0.0073 0.00821 0.00227 -0.0226 0.7575 0.0267 -1.500 0.0208 0.00815 0.00210 -0.0224 0.7258 0.0283 -1.250 0.0490 0.00809 0.00192 -0.0223 0.6881 0.0304 -1.000 0.0772 0.00813 0.00180 -0.0221 0.6393 0.0330 -0.750 0.1054 0.00821 0.00170 -0.0221 0.5841 0.0366 -0.500 0.1336 0.00829 0.00162 -0.0220 0.5277 0.0431 0.000 0.1899 0.00823 0.00154 -0.0222 0.4304 0.1408 0.250 0.2170 0.00732 0.00148 -0.0228 0.3911 0.4728 0.500 0.2431 0.00662 0.00152 -0.0227 0.3590 0.7400 0.750 0.2688 0.00652 0.00160 -0.0220 0.3323 0.8353 1.000 0.2931 0.00652 0.00169 -0.0208 0.3099 0.8928 1.250 0.3152 0.00661 0.00177 -0.0191 0.2882 0.9318 1.500 0.3374 0.00674 0.00182 -0.0174 0.2655 0.9592 1.750 0.3636 0.00687 0.00183 -0.0167 0.2406 0.9807 2.000 0.4069 0.00709 0.00190 -0.0198 0.2105 0.9967 2.250 0.4415 0.00733 0.00198 -0.0213 0.1876 1.0000 2.500 0.4663 0.00752 0.00206 -0.0206 0.1728 1.0000 2.750 0.4926 0.00768 0.00214 -0.0203 0.1622 1.0000 3.000 0.5199 0.00784 0.00224 -0.0201 0.1533 1.0000 3.250 0.5476 0.00804 0.00235 -0.0200 0.1443 1.0000 3.500 0.5757 0.00819 0.00245 -0.0200 0.1380 1.0000 3.750 0.6038 0.00838 0.00258 -0.0200 0.1310 1.0000 4.000 0.6321 0.00855 0.00270 -0.0200 0.1255 1.0000 4.250 0.6602 0.00876 0.00286 -0.0200 0.1197 1.0000 4.500 0.6885 0.00892 0.00299 -0.0201 0.1161 1.0000 4.750 0.7166 0.00914 0.00315 -0.0201 0.1117 1.0000 5.000 0.7447 0.00934 0.00333 -0.0201 0.1084 1.0000 5.250 0.7729 0.00951 0.00349 -0.0201 0.1056 1.0000 5.500 0.8008 0.00973 0.00368 -0.0201 0.1027 1.0000 5.750 0.8284 0.01001 0.00392 -0.0201 0.0994 1.0000 6.000 0.8565 0.01017 0.00409 -0.0201 0.0978 1.0000 6.250 0.8843 0.01038 0.00429 -0.0201 0.0958 1.0000 6.500 0.9119 0.01061 0.00450 -0.0201 0.0939 1.0000 6.750 0.9390 0.01093 0.00479 -0.0200 0.0916 1.0000 7.000 0.9663 0.01120 0.00508 -0.0199 0.0901 1.0000 7.250 0.9938 0.01141 0.00530 -0.0199 0.0890 1.0000 7.500 1.0211 0.01164 0.00554 -0.0198 0.0877 1.0000 7.750 1.0482 0.01189 0.00580 -0.0197 0.0863 1.0000 8.000 1.0750 0.01218 0.00608 -0.0196 0.0848 1.0000 8.250 1.1010 0.01259 0.00648 -0.0194 0.0832 1.0000 8.500 1.1270 0.01296 0.00688 -0.0192 0.0821 1.0000 8.750 1.1538 0.01321 0.00716 -0.0191 0.0814 1.0000 9.000 1.1802 0.01349 0.00747 -0.0189 0.0805 1.0000 9.250 1.2063 0.01380 0.00781 -0.0188 0.0796 1.0000 9.500 1.2323 0.01412 0.00815 -0.0185 0.0787 1.0000 9.750 1.2579 0.01445 0.00850 -0.0183 0.0779 1.0000 10.000 1.2832 0.01483 0.00889 -0.0181 0.0769 1.0000 10.250 1.3073 0.01533 0.00941 -0.0177 0.0758 1.0000 10.500 1.3301 0.01599 0.01009 -0.0171 0.0747 1.0000 10.750 1.3553 0.01631 0.01047 -0.0168 0.0743 1.0000 11.000 1.3800 0.01667 0.01089 -0.0165 0.0738 1.0000 11.250 1.4043 0.01707 0.01133 -0.0161 0.0732 1.0000 11.500 1.4284 0.01746 0.01177 -0.0157 0.0725 1.0000 11.750 1.4525 0.01781 0.01216 -0.0153 0.0716 1.0000 12.000 1.4765 0.01816 0.01254 -0.0150 0.0707 1.0000 12.250 1.4997 0.01857 0.01297 -0.0145 0.0698 1.0000 12.500 1.5208 0.01917 0.01359 -0.0138 0.0688 1.0000 12.750 1.5391 0.02005 0.01452 -0.0128 0.0678 1.0000 13.000 1.5622 0.02037 0.01492 -0.0123 0.0673 1.0000 13.250 1.5847 0.02074 0.01535 -0.0118 0.0667 1.0000 13.500 1.6061 0.02117 0.01586 -0.0111 0.0659 1.0000 13.750 1.6269 0.02163 0.01637 -0.0104 0.0652 1.0000 14.000 1.6471 0.02210 0.01689 -0.0096 0.0644 1.0000 14.250 1.6665 0.02259 0.01743 -0.0087 0.0637 1.0000 14.500 1.6839 0.02318 0.01806 -0.0077 0.0628 1.0000 14.750 1.6940 0.02411 0.01902 -0.0057 0.0618 1.0000 15.000 1.7086 0.02470 0.01969 -0.0042 0.0610 1.0000 15.250 1.7256 0.02516 0.02024 -0.0031 0.0602 1.0000 15.500 1.7406 0.02577 0.02093 -0.0019 0.0593 1.0000 15.750 1.7554 0.02643 0.02164 -0.0009 0.0584 1.0000 16.000 1.7689 0.02720 0.02247 0.0002 0.0575 1.0000 16.250 1.7790 0.02828 0.02359 0.0014 0.0566 1.0000 16.500 1.7829 0.02990 0.02528 0.0027 0.0557 1.0000 16.750 1.7952 0.03095 0.02644 0.0033 0.0550 1.0000 17.000 1.8077 0.03203 0.02762 0.0039 0.0541 1.0000 17.250 1.8191 0.03324 0.02890 0.0043 0.0529 1.0000 17.500 1.8280 0.03475 0.03048 0.0046 0.0518 1.0000 17.750 1.8318 0.03685 0.03263 0.0048 0.0507 1.0000 18.000 1.8339 0.03924 0.03512 0.0047 0.0498 1.0000 18.250 1.8404 0.04125 0.03725 0.0044 0.0486 1.0000 18.500 1.8426 0.04385 0.03994 0.0039 0.0473 1.0000 18.750 1.8395 0.04724 0.04341 0.0029 0.0461 1.0000 19.000 1.8293 0.05177 0.04804 0.0011 0.0451 1.0000 19.250 1.8217 0.05606 0.05248 -0.0006 0.0441 1.0000