Airfoil: M06-13-128 (B) Builder: M. Allen Comment: gurney flap (h/c = 1.0%) Number of Reynolds #'s: 2 Average Reynolds #: 200400 Number of angles of attack: 51 alpha / Cl / Cm -5.11 -0.119 0.0040 -3.41 0.139 0.0040 -2.40 0.258 0.0040 -1.58 0.345 0.0040 -0.50 0.458 0.0040 0.46 0.462 0.0040 1.43 0.522 0.0040 2.62 0.603 0.0040 3.59 0.687 0.0040 4.60 0.796 0.0040 5.86 0.993 0.0040 6.57 1.105 0.0040 7.67 1.238 0.0040 8.86 1.375 0.0040 9.65 1.463 0.0040 10.67 1.568 0.0040 11.87 1.634 0.0040 12.82 1.592 0.0040 13.82 1.520 0.0040 14.70 1.474 0.0040 15.70 1.413 0.0040 16.86 1.368 0.0040 17.60 1.365 0.0040 18.72 1.364 0.0040 19.71 1.364 0.0040 20.65 1.371 0.0040 19.08 1.368 0.0040 18.22 1.349 0.0040 17.19 1.363 0.0040 16.22 1.383 0.0040 15.15 1.444 0.0040 14.24 1.497 0.0040 13.22 1.569 0.0040 12.08 1.627 0.0040 11.14 1.608 0.0040 9.99 1.493 0.0040 9.09 1.393 0.0040 7.98 1.266 0.0040 7.03 1.155 0.0040 5.94 0.998 0.0040 4.80 0.818 0.0040 4.03 0.732 0.0040 2.71 0.603 0.0040 1.99 0.547 0.0040 0.80 0.466 0.0040 -0.35 0.453 0.0040 -1.04 0.405 0.0040 -2.45 0.245 0.0040 -3.36 0.137 0.0040 -4.40 -0.002 0.0040 -5.33 -0.155 0.0040 Tabulated from data in file PG00914.DAT & reduced using program Q02.00L Average Reynolds #: 300400 Number of angles of attack: 51 alpha / Cl / Cm -5.13 -0.093 0.0040 -3.37 0.142 0.0040 -2.73 0.213 0.0040 -1.47 0.382 0.0040 -0.72 0.484 0.0040 0.41 0.516 0.0040 1.57 0.642 0.0040 2.49 0.742 0.0040 3.40 0.837 0.0040 4.60 0.966 0.0040 5.62 1.075 0.0040 6.66 1.186 0.0040 7.74 1.301 0.0040 8.67 1.403 0.0040 9.84 1.528 0.0040 10.82 1.618 0.0040 11.66 1.645 0.0040 12.71 1.588 0.0040 13.76 1.517 0.0040 14.70 1.477 0.0040 15.62 1.424 0.0040 16.69 1.399 0.0040 17.65 1.372 0.0040 18.58 1.391 0.0040 19.56 1.385 0.0040 20.58 1.389 0.0040 18.95 1.380 0.0040 18.00 1.385 0.0040 17.16 1.391 0.0040 16.18 1.404 0.0040 15.06 1.447 0.0040 14.24 1.490 0.0040 13.14 1.553 0.0040 12.28 1.611 0.0040 11.03 1.633 0.0040 10.20 1.562 0.0040 9.08 1.445 0.0040 8.21 1.350 0.0040 6.97 1.215 0.0040 5.99 1.109 0.0040 4.94 0.996 0.0040 3.86 0.882 0.0040 2.93 0.781 0.0040 1.92 0.671 0.0040 0.91 0.563 0.0040 -0.10 0.495 0.0040 -1.06 0.432 0.0040 -2.14 0.276 0.0040 -3.33 0.135 0.0040 -4.10 0.059 0.0040 -5.30 -0.131 0.0040 Tabulated from data in file PG00917.DAT & reduced using program Q02.00L File m06gf1.lft created on 09-12-1997 at 13:46:17 using program FORMAT