Contents
clc
clear all
IDENTIFICATION
Name: Autar Kaw (Put your name here) Section : 001 (Put Section here) Semester: Fall 2011 Due Date & Time: August 29, 2011 (Put due data and time here)
disp('Name: Autar Kaw (Put your name here)') disp('Section : 001 (Put Section here)') disp('Semester: Fall 2011') disp('Due Date & Time: August 29, 2011 (Put due data and time here)')
Name: Autar Kaw (Put your name here) Section : 001 (Put Section here) Semester: Fall 2011 Due Date & Time: August 29, 2011 (Put due data and time here)
BACKGROUND and DESCRIPTION
Title: Lift force of an Airfoil is calculated from density of the airfoil material, cross-section area, velocity of flow and the coefficient of lift. lift=(1/2)*p*a*cl*(v^2); where, p = Density, kg/(m^3) a = Area of cross section, m^2 v = Velocity of airflow, m/s
disp('This program finds the lift of an airfoil')
This program finds the lift of an airfoil
INPUTS AND DISPLAY INPUTS
% p=density (kg/m^3) p =1.247; % a=area (m^2) a =2.4510; % cl=lift coef (unitless) cl =0.8100; % v=velocity (m/sec) v =35; fprintf('Density is %g Kg/m^3\n',p); fprintf('Area is %g m^2\n',a); fprintf('Velocity is %g m^2\n',v);
Density is 1.247 Kg/m^3 Area is 2.451 m^2 Velocity is 35 m^2
CODE
lift formula is below
lift=(1/2)*p*a*cl*(v^2);
DISPLAY OUTPUT
fprintf('the lift force is %g N\n',lift);
the lift force is 1516.35 N