6.1	Flight Stability
	Static and dynamic stability were both evaluted when investigating the aircraft's flight stability.  Within static stability, lateral, longitudinal, and directional axes were all given consideration, with the greatest emphasis placed on the longitudinal axis.
Control surface sizes were equated based on a common range of fraction and span chords.  To obtain maximum control authority, the upper limit of these ranges were chosen for each control surface fraction value.  The elevator sizes slected were a chord fraction of 0.4 and a span fraction of 1.0.  After sizing and design, pitching moment coefficient as a functions of angle of attack was plotted for various CG locations, elevator positions, and horizontal tail incidence angles.  After sizing and design, pitching moment coefficient as a functions of angle of attack was plotted for various CG locations, elevator positions, and horizontal tail incidence angles.  Figures #, #, and #, below, show these plots.
INSERT PLOTS HERE
The yaw axis was also investigated to ensure directional stability.  The rudder, the main contributor to this phenomenon, was designed with root chord and span fractions of 0.4 and 1.0, respectiviely.  Figure #, diplays the yawing moment coefficient as a function of sideslip.  It is evident from the negative slope of the plots, that the aicraft is directionally stable
Finally, aileron sizes were also selected based upon common aircraft control surfaces sizes.  Their chord and span fractions were selected to be 0.2 and 0.4, respectively..  The ailerons were positioned such that the outer edge of the control surfaces were located a distance from the wing tip equal to 10% of the half span.  The sizing and location were selected for maximum roll control authority.  Additionally, cofficient of rolling moment was plotted as a function of sideslip.  Figure #, below, displays the aircrafts static roll stability as Cl = 0 and b = 0, and Clb is inherently negative.
	Dynamic stability was evaluted through stability derivatives.  Most derivates were calculated in a program, Tornado, which uses vortex lattice method.  The remaining ones were calculated from these computer-produced values.  The table below lists thes dynamic stability values. 
INSERT TABLE OF DYNAMIC STABILITY VALUES HERE

6.2	Control System
	The radio control (RC) system is built around a Futaba 9CAP controller and receiver unit.  Futaba servos were also used, and specific models were selected based on calculated torque needs for the various control surfaces.  Digital servos were chosen over analog due to their increased torque capabilities with a lesser weight than analog ones.  One servo was used for each of the left and right ailerons, and for the elevator.  However, due to the large size of the rudder, two servos were needed for this control surface. INSERT REST OF CRAP ABOUT ROD AND LINKAGE CONFIGURATION WHEN AIRCRAFT IS PUT TOGETHER.