Aero 242             INDIVIDUAL TERM PROJECT 2             S99
3/25/99

Objective

The object of the term problem is to create a versatile program which can be used for airplane/mission analysis and design. For example when run it can answer the following problems:

a. Analysis:

Given the configuration and the mission, what are the minimum runway lengths?

b. Synthesis:

Given the complete mission and airframe configuration what engine size is required?

The objective will be achieved in steps, or Parts, during the remainder of the semester and will address only the mission type sketched as a mission profile above concentrating on a commercial jet transport.
Most of the elements of the problem will be developed as homework problems.

PART 2A. 
Write a  "Main"  program to determine the fuel burned during the 
mission as follows: 
        Program Main
        %include common.inc
        call input
        call takeoff(W0,W1)
        call climb(W1,W2)
        call cruise(W2,W3)
        call loiter(W3,W4)
        call descend(W4,W5)
        call land(W5,W6)
        wfuel=W6-W0
        wpay=W0-Wfuel-Wempty
        call output
        stop
        end

       
For Fortran programs all global variables will be declared by common 
statements within the include file. 
Global variables will have first letters  as upper case 
Local variables will have first letters  as lower case 
All  variables called by Subroutine input are global
Except for Subroutines cruise and loiter we will, for now, use 
"historical" values for fuel burned by a jet aircraft.

        W1/W0=.98
        W2/W1=1.0065-.0325Mcr   Mcr is the cruise Mach number
        W5/W4=.99
        W6/W5=.99

The following will be used for the wempty function:

        Wempty/W0=1.02*W0^-0.07

Your input subroutine will look something like this:

Subroutine input
        %include common.inc
        open(unit=11,file='problem.dat',status='readonly')
        open(unit=12,file='configuration.dat',status='readonly')
        open(unit=13, file='mission.dat', status='readonly')
        read(11,*) Wempty
        .
        .
        close(11)
        close(12)
        close(13)
        return
        end

To start use the following files. Do not use the third column.

        problem.dat
        (contains information needed, 
            such as system of units
                    aircraft type, jet or prop
                    etc)
                INPUT DATA FILES                
        configuration
        60000           W0              a/c Gross Takeoff Weight (lb:N)
        5000            Wpay            Payload Weight (lb:N)
        15000           Wfuel           Fuel Weight (lb:N)
        200             S               Wing Area (ft2:m2)
        7.              AR              Aspect Ratio
        .81             E               a/c Span Efficiency Factor
        .022            Cdo             Parasite Drag Coefficient
        2               Neng            Number of Engines
        20000           Tmax            Maximum Sea Level Thrust/engine (lb:N)
        18000           Tasl            Design Sea Level Thrust/engine (lb:N)
        .35             TSFC/SFC        Sp. Fuel Consumption (hr-1,lb/hp/hr: hr-1:N/kw/hr)
        .85             ETAp            Propeller Efficiency

        mission
        5000            Horigin         Originating Airport Altitude, (ft:km)
        9000            Sorigin         Originating Runway Length (ft:km)
        0.2             MUorigin        Originating Airport Rolling Friction
        34000           Hcr             Cruise Altitude (ft:km)
        0.6             Mcr             Cruise Mach number
        2500            Rcr             Cruise range (nm:km)
        4000            Hloit           Loiter Altitude (ft:km)
        250             Vloit           Loiter speed (K:km/h)
        50              Endur           Loiter time (min:min)
        0               Hdest           Destination Airport Altitude (ft:km)
        9000            Sdest           Destination Runway Length (ft:km)     
        0.4             MUdest          Destination Airport Rolling Friction

                OUTPUT DATA FILES                
        Output
        60000           W0s             a/c Gross T/O Weight (lb:N)
        40000           Wempty          a/c Empty Weight (lb:N)
        5000            Wpay            Payload Weight (lb:N)
        15000           Wfuel           Fuel Weight (lb:N)
        200             S               Wing Area (ft2:m2)
        7.              AR              Aspect Ratio
        34000           Hcr             Cruise Altitude (ft:km)
        0.6             Mcr             Cruise Mach number
        2500            Rcr             Cruise range (nm:km)
        4000            Hloit           Loiter Altitude (ft:km)
        250             Vloit           Loiter speed (K:km/h)
        0               Hdest           Destination Airport Altitude (ft:km)

Use "mission" located at /home/aeem/lockers/wilson/bin/mission to adjust Wto until Wpay = 5000 lb.

Submit (only):

Documented FORTRAN source code

Final Input files

Final Output files, formatted

"Snapshot" of final "Mission" display

Term Problem PART A Due: Friday Apr 9