hwk10-drag_force (1)

hwk10-drag_force (1) - = 0.344; % constant value for wing...

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
function [drag] = drag_force(length,width,velocity) %Homework 10 Problem 2 % This function calculate the total drag force on a generic wing given the % width, length and wind velocity. % % INPUT ARGUMENTS: length = length of the wing (m) % width = width of the wing (m) % velocity = velocity of air (m/s) % OUTPUT ARGUMENTS: drag = force due to drag on airfoil (N) % % ---- Input Section ---- Cl
Background image of page 1
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: = 0.344; % constant value for wing lift (non-dimensional) rho = 0.124; % density of air (kg/m^3) % ---- Calculation Section ----% Calculate the drag coefficient Cd = (Cl^2)*width/length; % Calculate the drag force drag = 0.5*rho*velocity^2*Cd*(length*width); % ---- Output Section ----% x = drag_force(20,4.5,4.47) % x = 2.9686 N % x = drag_force(30,6,5.36) % x = 7.5882 N...
View Full Document

This note was uploaded on 02/12/2012 for the course ENGR 126 taught by Professor Oakes during the Fall '08 term at Purdue.

Ask a homework question - tutors are online