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)')

%%  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')

%% 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);

%% CODE
% lift formula is below
lift=(1/2)*p*a*cl*(v^2);
%% DISPLAY OUTPUT
fprintf('the lift force is %g N\n',lift);