XFOIL Version 6.96 Calculated polar for: FX 74-130 WP1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.1309 0.09252 0.08811 -0.1189 0.8656 0.0260 -10.250 -0.1289 0.08895 0.08455 -0.1212 0.8634 0.0262 -9.250 -0.1257 0.07256 0.06819 -0.1263 0.8554 0.0181 -9.000 -0.1269 0.06904 0.06471 -0.1279 0.8528 0.0174 -8.750 -0.1322 0.06476 0.06045 -0.1309 0.8500 0.0167 -8.500 -0.1432 0.06030 0.05596 -0.1333 0.8472 0.0161 -8.250 -0.1590 0.05672 0.05231 -0.1332 0.8443 0.0156 -7.750 -0.1840 0.04615 0.04129 -0.1310 0.8379 0.0134 -7.500 -0.1840 0.04292 0.03786 -0.1296 0.8354 0.0134 -7.250 -0.1797 0.03988 0.03456 -0.1282 0.8333 0.0133 -7.000 -0.1728 0.03656 0.03087 -0.1266 0.8316 0.0134 -6.750 -0.1645 0.03362 0.02753 -0.1249 0.8296 0.0137 -6.500 -0.1523 0.03189 0.02567 -0.1239 0.8271 0.0144 -6.250 -0.1346 0.03095 0.02462 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4.250 0.8058 0.01710 0.01102 -0.0887 0.7227 0.9109 4.500 0.8417 0.01668 0.01066 -0.0901 0.7204 0.9115 4.750 0.8495 0.01701 0.01107 -0.0869 0.7118 0.9139 5.000 0.8841 0.01652 0.01066 -0.0880 0.7078 0.9145 5.250 0.8957 0.01662 0.01087 -0.0853 0.6987 0.9167 5.500 0.9341 0.01587 0.01020 -0.0869 0.6926 0.9172 5.750 0.9470 0.01589 0.01031 -0.0842 0.6804 0.9195 6.000 0.9686 0.01563 0.01012 -0.0830 0.6668 0.9216 6.250 0.9917 0.01531 0.00986 -0.0819 0.6464 0.9235 6.500 1.0193 0.01487 0.00938 -0.0814 0.6114 0.9249 6.750 1.0440 0.01466 0.00871 -0.0802 0.5259 0.9262 7.000 1.0372 0.01583 0.00938 -0.0747 0.4480 0.9303 7.250 1.0300 0.01721 0.01043 -0.0697 0.3874 0.9348 7.500 1.0231 0.01875 0.01168 -0.0651 0.3278 0.9402 8.000 1.0220 0.02176 0.01418 -0.0588 0.2200 0.9554 8.250 1.0263 0.02326 0.01542 -0.0567 0.1684 0.9711 8.500 1.0316 0.02471 0.01662 -0.0547 0.1227 1.0000 8.750 1.0401 0.02616 0.01787 -0.0532 0.0874 1.0000 9.000 1.0514 0.02744 0.01906 -0.0521 0.0651 1.0000 9.250 1.0630 0.02874 0.02029 -0.0509 0.0509 1.0000 9.500 1.0759 0.02995 0.02155 -0.0499 0.0426 1.0000 9.750 1.0881 0.03123 0.02286 -0.0488 0.0371 1.0000 10.000 1.1013 0.03245 0.02417 -0.0479 0.0335 1.0000 10.250 1.1122 0.03386 0.02563 -0.0468 0.0304 1.0000 10.500 1.1222 0.03536 0.02722 -0.0456 0.0281 1.0000 10.750 1.1350 0.03666 0.02863 -0.0447 0.0258 1.0000 11.000 1.1462 0.03811 0.03018 -0.0438 0.0240 1.0000 11.250 1.1561 0.03971 0.03187 -0.0427 0.0225 1.0000 11.500 1.1621 0.04173 0.03393 -0.0414 0.0208 1.0000 11.750 1.1755 0.04308 0.03544 -0.0407 0.0192 1.0000 12.000 1.1864 0.04473 0.03721 -0.0399 0.0181 1.0000 12.250 1.1970 0.04638 0.03896 -0.0391 0.0167 1.0000 12.500 1.2063 0.04816 0.04080 -0.0384 0.0155 1.0000 12.750 1.2139 0.05030 0.04303 -0.0375 0.0144 1.0000 13.000 1.2249 0.05209 0.04502 -0.0368 0.0135 1.0000 13.250 1.2347 0.05411 0.04723 -0.0360 0.0127 1.0000 13.500 1.2431 0.05626 0.04955 -0.0353 0.0121 1.0000 13.750 1.2503 0.05854 0.05198 -0.0347 0.0114 1.0000 14.000 1.2561 0.06098 0.05456 -0.0342 0.0110 1.0000 14.250 1.2600 0.06363 0.05733 -0.0338 0.0106 1.0000 14.500 1.2611 0.06690 0.06074 -0.0332 0.0101 1.0000 14.750 1.2625 0.07007 0.06419 -0.0329 0.0098 1.0000 15.000 1.2616 0.07359 0.06799 -0.0327 0.0093 1.0000 15.250 1.2583 0.07750 0.07216 -0.0328 0.0090 1.0000 15.500 1.2530 0.08172 0.07663 -0.0331 0.0086 1.0000 15.750 1.2458 0.08635 0.08151 -0.0339 0.0084 1.0000 16.000 1.2365 0.09146 0.08686 -0.0350 0.0082 1.0000 16.250 1.2250 0.09714 0.09278 -0.0366 0.0081 1.0000 16.500 1.2117 0.10335 0.09923 -0.0389 0.0080 1.0000 16.750 1.1966 0.11019 0.10631 -0.0418 0.0080 1.0000 17.000 1.1801 0.11771 0.11407 -0.0456 0.0079 1.0000 17.250 1.1610 0.12628 0.12287 -0.0504 0.0080 1.0000 17.500 1.1388 0.13626 0.13308 -0.0565 0.0080 1.0000 17.750 1.1125 0.14828 0.14533 -0.0643 0.0082 1.0000