Starting the Program



In the Matlab prompt, type and execute:

>Tornado
and the Tornado splash screen and main menu appears.

""""""""""""""""""""""""""""""""""""""""""""""""""""""
"  TORNADO  V 135 Export
"  Main Menu                                       
"                                                  
""""""""""""""""""""""""""""""""""""""""""""""""""""""
 
 Input operations.
 
    [1]. Aircraft geometry setup
    [2]. Flight condition setup
    [3]. Change rudder setting
    [4]. Move reference point
 
 Lattice operations.
 
    [5]. Generate lattice.
       
 Computation operations.
 
     [6]. Processor access
 
 Post processing and interactive operations.
 
    [7]. Post processing, Result/Plot functions
    [8]. Keyboard access
 
 Auxiliary operations.
 
    [9]. About / Release Info
    [0]. Exit Tornado
 
    Please enter choice from above:



Navigating through the program is done by selecting the number by the desired function in the list. When entering data, it's either in numerical format, Boolean (0 for no, 1 for yes) or as a string.

 



Computing the characteristics of a simple wing.

Select option number 1 in the main menu, "Geometry Setup", and then select option number 1, "Define new geometry", in the Geometry setup menu. This starts the geometry input loop which loops over the number of wings and the partitions of each wing.

For this first aircraft geometry we'll just employ one wing (The horizontal stabilizer would usually be the second, and the vertical tail the third), so answer "1" to the question Number of Wings:

Then, answer "1" to the question Number of partitions for this wing. After this a series of questions regarding the constitution of this partition follows, answer them as follows:
(What the numbers actually means will be explained later, in case it's not obvious). The first six questions will only be asked for the first wing in your design, as they are global.

Center of gravity x-coordinate:          0
Center of gravity y-coordinate:          0
Center of gravity z-coordinate:      0
Reference point x-coordinate:            0  
Reference point y-coordinate:           0    
Reference point z-coordinate:            0
Is the wing mirrored in the xz-plane [1 0]:               1
Root chord:                                               1  
Base chord airfoil:                                       2400  
Number of panels chord wise:                              5                      
Partition dihedral [deg]:                                 5  
Number of panels semi-span wise:                          5   
Span of partition:                                        2
Taper ratio:                                              0.7
Tip chord airfoil:                                       2400  
Quarter chord line sweep [deg]:                           10  
Outboard twist [deg]:                                    -5
Mesh type:                                              1 
Is partition flapped [1 0]:                               1
Flap chord in fraction of local chord (0..1):             0.15
Number of chord wise panels on flap:                      1
Does control surfaces deflect symmetrically [1 0]:    1


When this loop is done, you'll be back in the main menu. From here select flight condition setup and define new state. (2, and then 1). In the state setup, enter:



Alpha [deg]:                              5
Beta [deg]:                                 0
Roll angular velocity [deg/s]:              0
Pitch angular velocity [deg/s]:             0
Yaw angular velocity [deg/s]:               0


After which you'll be asked for speed and altitude, in a format of your choice.
Enter which type of speed you whish to enter:


 
 International units:
 
 [1]. True airspeed (TAS) at SSL                     [m/s]
 [2]. True airspeed (TAS) at altitude                [m/s, m]
 [3]. Equivalent airspeed (EAS) at altitude       [m, m/s]
 [4]. Calibrated air speed (CAS) at altitude      [m, m/s]
 [5]. Mach number at altitude                        [-, m]
 
 Imperial Units:
 
 [6]. True airspeed (TAS) at altitude               [kts, ft]
 [7]. Equivalent airspeed (EAS) at altitude      [kts, ft]
 [8]. Calibrated air speed (CAS) at altitude     [kts, ft]
 [9]. Mach number at altitude                        [-, ft]
 
Type of speed selection:                             1
True airspeed [m/s]:                                 100
Apply Prandtl-Glauert Correction [0 1]:             0



When this is done, you're again dumped back into the main menu. Select the option generate lattice, option 0 -"freestream following wake".  The lattice is now initialized and ready for solving. First plot the geometry to make sure it looks like you intended. Got to post processing, and there select option 2, geometry plot. This will invoke four plots, one with panels, reference point and mean aerodynamic chord, one with collocation points and panel normals, one with the vortex layout and one with a three view drawing of your paneling. Plotting the geometry is not essential for getting a solution.

When this is done, select the processor access to see the different options regarding the solver. Here, select simple solution computation. You'll be asked for a Job Identifier (JID). This is just a text string to help you identify your results among printouts and files.

Enter Job IDentity tag (JID):                  test


The computer will chew on this for a couple of seconds before invoking the main menu again. When ready, select Post processing, Result/Plot functions and then select Solution plot, simple state in the post processing menu. You'll be shown a list of available result files (saved automagically by the solver function). Type in your JID to plot the results.



Enter JID to plot:                             test


A couple of result plots should appear.

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test