Final answer:
Factors crucial for analyzing a finite wing with a NACA 23012 airfoil include the airfoil geometry, lift coefficient, aspect ratio, angle of attack, and vortex shedding, with emphasis on the air density and velocity to ensure the wing produces the standard lift of 1000 N per square meter.
Step-by-step explanation:
When analyzing a finite wing with a NACA 23012 airfoil and a given measured lift slope of 0.1080 degrees^-1, several factors are crucial for a thorough analysis. Considering a span loading ranging from 0 up to 1.3, one must account for the airfoil geometry, lift coefficient, and aspect ratio of the wing. Other important factors include the angle of attack, the vortex shedding as the span loading changes, and viscous effects, which can affect the lift characteristics. Additionally, the air density and velocity will also have significant impacts on the lift generated. Applying the rule of thumb that wings should produce about 1000 N of lift per square meter, calculations can be made using Bernoulli's principle and the continuity equation to determine airspeeds required for lift in various flight conditions. The influence of the aircraft's speed, engine thrust, and the Reynolds number should also be considered in such analyses, as they contribute to the overall lift production.