Optimization of Airplane Formation Flight

2006

(1) Simulation


silmulation


(2) Input

 

% Air density

rho=0.0186;                                        

% Free stream speed  

V_inf=959.8747;       

% Angle of attack

angle=1.0;      

% Number of the main wing section: this is required for a complex wing shape.  

wingsection=2;      

% Main wing geometry

span=[63 126]; Lambda=[45 45]; AR=[4.5]; taperatio=[0.8 0.5];

% Vortex lattice number chordwise: nth matrix component is nth airplane value. 

numvortexlatticechordwise=[2 2 2 2 2 2 2 2 2];                 

% Vortex lattice number spanwise: nth matrix component is nth airplane value.

numvortexlatticespanwise=[32 32 32 32 32 32 32 32 32]; 

% Formation size

numberofairplane=2;

 

(3) Output

 

% Change of induced drag: the output is a k-by-l matrix. Its row indicates vertical separation, and column indicates lateral separation.

AverageInduceDragChange(k,l) = -5.1048    -5.1307  -4.9529

                                                        -6.1324    -6.1287  -5.8503

                                                         3.4289    -7.3967  -6.976

% Change of total drag

AverageDragChange(k,l) = -0.89095     -0.89548      -0.86444

                                             -1.0703       -1.0697        -1.0211

                                               0.59845    -1.291          -1.2175

% Change of flight range

AverageRangeChange(k,l)  = 0.90656     0.91125     0.8791

                                                1.0931       1.0924       1.0417

                                               -0.591         1.3244       1.2472
 


(4) Program Functional Block

functional block
(5) Source Code (Written in MatLab M file - Code screenshot saved in PDF file)

Program source code