1) The document provides aerodynamic calculations for a wing and tail at a cruise speed of Mach 0.30257 at 30,000 feet, including drag coefficients for the wing, horizontal tail, vertical tail, and fuselage. 2) Calculations are shown for the wing wetted area, reference area, aspect ratio, taper ratio, and Oswald efficiency factor. Drag coefficients are calculated based on laminar flow percentages and Reynolds numbers. 3) Tail drag coefficient calculations are also provided for the horizontal and vertical tails, accounting for laminar flow percentages and Reynolds numbers at the root and tip. 4) Fuselage drag coefficient and wetted area calculations are presented based on the fu