For your independent project, create an instructional presentation. Using/building on your previous drag (i.e., thrust-required) table and graph created in Module 3, generate additional power-required values in the table and depict the power-required curve for your aircraft.   Then, working with your derived thrust-required and/or power-required curves and table data, explain how to find various performance aspects for your aircraft, and provide the specific data for your example. At a minimum cover the following: Maximum range airspeed Maximum endurance airspeed Best climb conditions Best rate of climb (ROC) & associated airspeed Best angle of climb (AOC) & associated airspeed Maximum forward airspeed Best glide airspeed Additionally, discuss and highlight numerically on a specific example of how weight change influences performance events such as the best range or endurance. As in previous assignments, you will need to research additional information such as required formulas and pertinent aircraft data. Again, the emphasis in this project task is on explaining your methodology as if you are attempting to instruct someone unfamiliar with the aerodynamic details and relationships. Therefore, make sure to detail all assumptions, all formulas used, and all steps that were taken. The following will give you some starting points for your search and consideration.  Required formula: Thrust to power relationship Weight change influence on performance airspeeds ROC & AOC relationships Necessary aircraft information: Powerplant output (for simplification, you can assume constant power output at the rated value across the entire speed range); whatever powerplant data you utilize, please make sure to include a short discussion detailing your assumptions. Previous information:  Make sure to detail again all assumed information used/transferred from last week (e.g., aircraft weight, atmospheric conditions, etc.) since performance data are, obviously, only valid for specific cases and conditions.