XFOIL Version 6.8 Calculated polar for: RG-15 8.9% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = .000 Re = .200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top Xtr Bot Xtr ------- -------- --------- --------- -------- ------- ------- -2.000 -.0729 .01013 .00523 -.0414 .9884 .7726 -1.500 -.0080 .01026 .00540 -.0422 .9697 .8436 -1.000 .0579 .01013 .00523 -.0431 .9526 .8979 -.500 .1281 .00988 .00493 -.0446 .9364 .9454 .500 .3317 .00904 .00394 -.0624 .9065 1.0000 1.000 .3901 .00870 .00353 -.0629 .8727 1.0000 1.500 .4415 .00860 .00333 -.0619 .8323 1.0000 2.000 .4937 .00866 .00323 -.0608 .7886 1.0000 2.500 .5445 .00887 .00330 -.0594 .7392 1.0000 3.000 .5944 .00918 .00345 -.0579 .6849 1.0000 3.500 .6435 .00959 .00367 -.0563 .6274 1.0000 4.000 .6914 .01011 .00401 -.0545 .5644 1.0000 4.500 .7386 .01071 .00444 -.0527 .4961 1.0000 5.000 .7847 .01145 .00501 -.0508 .4229 1.0000 5.500 .8294 .01238 .00568 -.0489 .3408 1.0000 6.000 .8731 .01353 .00655 -.0471 .2528 1.0000 6.500 .9143 .01510 .00777 -.0451 .1661 1.0000 7.000 .9534 .01705 .00941 -.0428 .1004 1.0000 7.500 .9921 .01902 .01122 -.0406 .0581 1.0000 7.000 .9534 .01705 .00941 -.0428 .1004 1.0000 7.500 .9921 .01902 .01122 -.0406 .0581 1.0000