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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5472 0.08753 0.08521 0.0014 1.0000 0.0148 -8.500 -0.5530 0.08136 0.07906 -0.0036 1.0000 0.0147 -8.250 -0.5658 0.07259 0.07028 -0.0136 1.0000 0.0145 -8.000 -0.5645 0.06621 0.06384 -0.0194 1.0000 0.0146 -7.750 -0.5596 0.06052 0.05805 -0.0233 1.0000 0.0148 -7.500 -0.5540 0.05435 0.05171 -0.0264 1.0000 0.0149 -7.250 -0.5536 0.04483 0.04183 -0.0290 1.0000 0.0148 -7.000 -0.5539 0.03374 0.03011 -0.0294 1.0000 0.0149 -6.750 -0.5550 0.02248 0.01765 -0.0274 1.0000 0.0155 -6.500 -0.5312 0.01988 0.01463 -0.0273 0.9969 0.0158 -6.250 -0.5008 0.01805 0.01246 -0.0281 0.9921 0.0161 -6.000 -0.4690 0.01674 0.01090 -0.0291 0.9880 0.0164 -5.750 -0.4382 0.01578 0.00973 -0.0297 0.9826 0.0168 -5.500 -0.4067 0.01502 0.00893 -0.0305 0.9775 0.0170 -5.250 -0.3747 0.01438 0.00824 -0.0314 0.9724 0.0173 -5.000 -0.3476 0.01384 0.00765 -0.0311 0.9625 0.0175 -4.750 -0.3215 0.01334 0.00709 -0.0304 0.9478 0.0179 -4.500 -0.2976 0.01287 0.00654 -0.0292 0.9286 0.0182 -4.250 -0.2732 0.01242 0.00601 -0.0281 0.9117 0.0186 -4.000 -0.2476 0.01200 0.00551 -0.0273 0.8995 0.0191 -3.750 -0.2214 0.01162 0.00505 -0.0266 0.8863 0.0195 -3.500 -0.1952 0.01123 0.00464 -0.0260 0.8728 0.0200 -3.250 -0.1687 0.01094 0.00432 -0.0255 0.8587 0.0206 -3.000 -0.1420 0.01068 0.00401 -0.0249 0.8430 0.0213 -2.750 -0.1147 0.01043 0.00370 -0.0245 0.8270 0.0221 -2.250 -0.0611 0.01008 0.00316 -0.0235 0.7709 0.0241 -2.000 -0.0342 0.01001 0.00293 -0.0230 0.7302 0.0255 -1.750 -0.0070 0.00994 0.00271 -0.0226 0.6866 0.0270 -1.500 0.0206 0.00993 0.00252 -0.0223 0.6421 0.0287 -1.250 0.0482 0.00995 0.00237 -0.0221 0.5912 0.0307 -1.000 0.0759 0.01003 0.00225 -0.0220 0.5383 0.0339 -0.750 0.1037 0.01012 0.00216 -0.0219 0.4871 0.0384 -0.500 0.1317 0.01020 0.00210 -0.0219 0.4399 0.0466 -0.250 0.1596 0.01025 0.00205 -0.0219 0.3975 0.0656 0.000 0.1876 0.01025 0.00203 -0.0219 0.3629 0.1005 0.250 0.2156 0.01016 0.00202 -0.0220 0.3341 0.1650 0.500 0.2410 0.00886 0.00196 -0.0225 0.3107 0.5854 0.750 0.2655 0.00841 0.00205 -0.0216 0.2902 0.7674 1.000 0.2868 0.00829 0.00218 -0.0196 0.2700 0.8700 1.250 0.3067 0.00836 0.00227 -0.0172 0.2492 0.9270 1.500 0.3309 0.00849 0.00231 -0.0160 0.2268 0.9652 1.750 0.3688 0.00868 0.00235 -0.0179 0.2036 0.9876 2.000 0.4050 0.00889 0.00242 -0.0196 0.1850 0.9953 2.250 0.4366 0.00909 0.00250 -0.0204 0.1710 1.0000 2.500 0.4626 0.00927 0.00258 -0.0200 0.1608 1.0000 2.750 0.4894 0.00944 0.00268 -0.0198 0.1531 1.0000 3.000 0.5164 0.00963 0.00279 -0.0196 0.1453 1.0000 3.250 0.5439 0.00980 0.00291 -0.0194 0.1388 1.0000 3.750 0.5990 0.01019 0.00318 -0.0192 0.1271 1.0000 4.000 0.6266 0.01040 0.00333 -0.0191 0.1221 1.0000 4.250 0.6543 0.01061 0.00349 -0.0191 0.1181 1.0000 4.500 0.6819 0.01081 0.00366 -0.0190 0.1141 1.0000 4.750 0.7094 0.01105 0.00385 -0.0189 0.1101 1.0000 5.000 0.7371 0.01126 0.00404 -0.0189 0.1071 1.0000 5.250 0.7646 0.01148 0.00424 -0.0188 0.1040 1.0000 5.500 0.7919 0.01174 0.00446 -0.0187 0.1013 1.0000 5.750 0.8192 0.01200 0.00470 -0.0186 0.0990 1.0000 6.000 0.8466 0.01223 0.00494 -0.0186 0.0971 1.0000 6.250 0.8738 0.01248 0.00519 -0.0185 0.0950 1.0000 6.500 0.9007 0.01276 0.00545 -0.0184 0.0930 1.0000 6.750 0.9274 0.01309 0.00575 -0.0182 0.0909 1.0000 7.000 0.9543 0.01336 0.00604 -0.0181 0.0895 1.0000 7.250 0.9810 0.01364 0.00634 -0.0180 0.0880 1.0000 7.500 1.0076 0.01394 0.00665 -0.0178 0.0866 1.0000 7.750 1.0339 0.01426 0.00698 -0.0176 0.0853 1.0000 8.000 1.0599 0.01461 0.00734 -0.0174 0.0840 1.0000 8.250 1.0855 0.01502 0.00774 -0.0172 0.0827 1.0000 8.500 1.1113 0.01537 0.00813 -0.0169 0.0818 1.0000 8.750 1.1371 0.01571 0.00852 -0.0167 0.0807 1.0000 9.000 1.1626 0.01606 0.00891 -0.0165 0.0796 1.0000 9.250 1.1879 0.01643 0.00932 -0.0162 0.0786 1.0000 9.500 1.2128 0.01683 0.00975 -0.0159 0.0776 1.0000 9.750 1.2374 0.01726 0.01021 -0.0155 0.0767 1.0000 10.000 1.2615 0.01773 0.01070 -0.0151 0.0759 1.0000 10.250 1.2846 0.01829 0.01128 -0.0147 0.0750 1.0000 10.500 1.3084 0.01876 0.01182 -0.0142 0.0744 1.0000 10.750 1.3320 0.01922 0.01236 -0.0138 0.0738 1.0000 11.000 1.3553 0.01970 0.01290 -0.0133 0.0730 1.0000 11.250 1.3782 0.02019 0.01346 -0.0128 0.0721 1.0000 11.500 1.4007 0.02070 0.01404 -0.0122 0.0714 1.0000 11.750 1.4226 0.02124 0.01465 -0.0116 0.0707 1.0000 12.000 1.4439 0.02181 0.01528 -0.0109 0.0701 1.0000 12.250 1.4644 0.02242 0.01594 -0.0102 0.0695 1.0000 12.500 1.4840 0.02307 0.01664 -0.0094 0.0688 1.0000 12.750 1.5017 0.02387 0.01746 -0.0084 0.0678 1.0000 13.000 1.5219 0.02438 0.01810 -0.0076 0.0670 1.0000 13.250 1.5408 0.02497 0.01880 -0.0067 0.0661 1.0000 13.500 1.5583 0.02563 0.01955 -0.0057 0.0652 1.0000 13.750 1.5738 0.02630 0.02030 -0.0044 0.0644 1.0000 14.000 1.5872 0.02701 0.02109 -0.0028 0.0636 1.0000 14.250 1.5993 0.02783 0.02198 -0.0013 0.0628 1.0000 14.500 1.6096 0.02881 0.02302 0.0002 0.0621 1.0000 14.750 1.6180 0.03001 0.02429 0.0016 0.0614 1.0000 15.000 1.6286 0.03113 0.02554 0.0027 0.0608 1.0000 15.250 1.6380 0.03239 0.02694 0.0037 0.0601 1.0000 15.500 1.6466 0.03379 0.02846 0.0045 0.0594 1.0000 15.750 1.6543 0.03533 0.03013 0.0051 0.0586 1.0000 16.000 1.6610 0.03706 0.03197 0.0055 0.0578 1.0000 16.250 1.6660 0.03905 0.03405 0.0056 0.0571 1.0000 16.500 1.6692 0.04136 0.03645 0.0054 0.0564 1.0000 16.750 1.6693 0.04416 0.03933 0.0049 0.0557 1.0000 17.000 1.6697 0.04709 0.04242 0.0041 0.0550 1.0000 17.250 1.6687 0.05036 0.04586 0.0030 0.0541 1.0000 17.500 1.6649 0.05414 0.04979 0.0014 0.0533 1.0000 17.750 1.6580 0.05853 0.05432 -0.0006 0.0525 1.0000 18.000 1.6472 0.06365 0.05958 -0.0032 0.0518 1.0000 18.250 1.6315 0.06963 0.06569 -0.0062 0.0512 1.0000 18.500 1.6106 0.07656 0.07276 -0.0099 0.0507 1.0000 18.750 1.5848 0.08437 0.08070 -0.0139 0.0503 1.0000 19.000 1.5561 0.09275 0.08924 -0.0183 0.0499 1.0000 19.250 1.5246 0.10177 0.09843 -0.0231 0.0495 1.0000