primary spar carrying the bending load
Research two aircraft that are notably different. Compare and contrast cost, performance, design, material selection, and maintenance requirements. Estimate variables (e.g. cost) which aren’t readily available. Where estimates are used, justify your thought process.
For one of the aircraft, discuss three design features and associated tradeoffs (performance and/or structural) engineers likely contemplated. For one of the tradeoffs, outline the pros and cons of the decision.
Within your report, discuss the relationship between aerodynamic performance and structural design and how each influences one another.
For one of the aircraft, estimate the maximum normal bending stress at the wing-fuselage interface using the following simplifying assumptions:
- There exists a primary spar carrying the bending load.
- The spar can be modeled as an “I-beam.”
- Estimate a reasonable spar size (length, depth, height) and material.
- Note: You will need to look up the Modulus of Elasticity (“E”) based upon your pick of the material you chose for your spar.
- The “Second Moment of Area” (I) from our stress equation, Stress = My/I, can be determined similar to the following image, Figure 1.