spr_sysprob4

# spr_sysprob4 - Lab 4 – Design Problem Formulation Unified...

This preview shows pages 1–2. Sign up to view the full content.

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: Lab 4 – Design Problem Formulation Unified Engineering 4 Mar 06 Learning Objectives • Measure and analyze prototype/baseline UE Competition airplane • Formulate a suitable design space for a new wing • Perform preliminary design and sizing studies. This will be a quantitative continuation of the exercise from Lab 1. Plane Vanilla Measurements for Redesign Baseline (reverse engineering) • Measure the prototype Plane Vanilla airplane in order to determine S , b , W , λ • Note the component weights given • Measure the thickness/chord ratio τ of the root airfoil • For wing weight and deﬂection estimates, the pink foam’s approximate properties are: 3 ρ ≃ 2 . 0 lbm / ft 3 = 0 . 525 g / in 3 = 32 kg / m , E ≃ 2800 psi = 19 . 3 MPa The cross-sectional area of a typical airfoil is very nearly 2 τ A = 0 . 60 c t = 0 . 60 c which allows estimation of the wing volume and hence the wing weight. The weight of the remainder of the airplane can be assumed to be fixed for now....
View Full Document

## This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.

### Page1 / 2

spr_sysprob4 - Lab 4 – Design Problem Formulation Unified...

This preview shows document pages 1 - 2. Sign up to view the full document.

View Full Document
Ask a homework question - tutors are online