Initial Design Summary

Based on the results from initial weight estimation and constraint analysis, following table outlines some of the major important quantities for the example airplane:

Parameter	Value	Source
Aspect ratio	8	Initial weight estimation (assumed)
Maximum takeoff weight	5354 lbs	Initial weight estimation
Empty weight	3094 lbs	Initial weight estimation
Fuel weight	1060 lbs	Initial weight estimation
Takeoff Wing loading	40 lbs/\(\text{ft}^2\)	Constraint analysis
Takeoff Power loading	9.25 lbs/hp	Constraint analysis
Wing surface area	134 \(\text{ft}^2\)	Calculated from W/S
Takeoff power	595 hp	Calculated from W/P
Wing span	33 ft	Calculated from \(S\) and \(A\)
Maximum lift coeff. with no flaps, \(C_{L_{max}}\)	1.5	Constraint analysis (assumed)
Maximum lift coeff. with takeoff flaps, \(C_{L_{max_{TO}}}\)	1.8	Constraint analysis (assumed)
Maximum lift coeff. with landing flaps, \(C_{L_{max_{L}}}\)	2.2	Constraint analysis (assumed)

NOTE: The above estimates are based on the initial sizing process. These estimates can be further improved using carpet plots or by running numerical optimization.