modified Feb 2, 2006 by Charles W. Barbour II
Modifications: - corrected wing span, chord lengths, AR
Origin of the front side of the nose
Taper ratio of out board section
Root and Tip chords
Wing Area
Wingspan
twist, typically 0 - 3 degrees, none needed unless wing is sweeped or tapered severly, or airfoils are varied with span
sweep of the wing quarter chord
fraction of span for inner section
fraction of span for outter section
Aileron, fraction of chord,
Aileron, fraction of span,
aileron effectiveness factor (from Fig. 2.21 Flight Stability and Control)
X coordinate of the mac of the wing in relative to the front of the plane
Y coordinate of the mac of the wing in relative to the front of the plane
Lift Coef. function
Thickness to chord
Drag Coef. function
maximum lift coef
Moment coef function
minimum lift coef
Wing surface area
C.r solved for
root chord
tip chord
mean chord
X location of the mac relative to the chord
Check pg 442 Torenbeek
Y location of the mac
root thickness for structures
tip thickness
average thickness
approx.wetted area
cg location of aileron servos
Interpolation Method for Area of Airfoil Given Chord
Reference: Autocad Values from Airfoil ah94145
Varying Taper Ratio
Wing rib area for half span
Wing rib area for full span
Surface Area of Rib Contact with Skin
Wing surface area for half span
Wing surface area for full span
Horizontal Tail Taper Ratio
Horizontal Tail Twist
assumed dynamic pressure at the tail / dynamic pressure, qh/q
incidence angle of the horizontal tail
Elevator, fraction of chord,
Elevator, fraction of span,
quarter chord of wing
position of the quarter chord of the tail
span
root chord
tip chord
mean chord
X location of the mac
Y location of the mac
root thickness, for structures
tip thickness
average thickness
wetted area
cg location of elevator servos
Horizontal Tail surface area for half span
Horizontal Tail surface area for full span
Horizontal Tail rib area for full span
Length between quarter chord of wing
This value (C.v) is the y input on Fig. 9-24 in Torenbeek.
0.038 or greater for a single engine propeller A/C with little normal
force on the vertical tail.
Look at the "Checking the Vertical Tail Size" section.
the analysis shows that a C.vt of 0.04 is required.
tail vol coeff
Taper Ratio vertical tail
assumed dynamic pressure at the tail / dynamic pressure, qh/q
Rudder, fraction of chord,
Rudder, fraction of span,
span
root chord
tip chord
mean chord
position of the quarter chord of the tail
Length
root thickness, for structures
tip thickness
average thickness
wetted area
rudder chord
Vertical Tail surface area for half span
Vertical Tail surface area for full span
Vertical Tail rib area for full span
Length of the payload
Width of the payload
Height of the payload
cg position of the payload relative to center of payload
X cg coordinate of the payload relative to front of plane
Y cg coordinate of the payload relative to front of plane
Z CG COORDINATE OF PAYLOAD IS IN GEOMETRY FILE DUE TO REFERENCE OF VARIABLES LATER DEFINED
Distance from mac of the wing to the cg of the payload
center position of the payload
position of end of the payload
Position of front of payload
Length of the Gear Strut
Thickness of the landing gear
Width of Gear at Fuselage Connection
tire height
tire width
Height of Fuselage off ground
position of the landing gear cg
length of engine from back plate to drive washer
NEED TO BE CORRECTED
Aileron Servos
Tail Servo
maximum X distance between the engine cg and the tank cg
X position of the engine relative to clump mass cg
X position of the receiver relative to clump mass cg
X distance between the cg of the tank and cg of the battery
minimum X distance between the engine cg and the tank cg
minimum X distance between the battery cg and the receiver cg
Source: Geometry. See Fig. 11.11, p.289 - Raymer
Length of forward compartment. Minimum is determined by the fuel tank (4.5 inches long).
Height of the front of the nose compartment
Height of the rear of the nose compartment
CG of the nose with respect to front of nose
Bulkhead Area at front of nose(accounts for 1in flange around bulkhead)
Bulkhead location at front of nose
Bulkhead Diameter at 50% of nose
Bulkhead Area at 50% of nose
Bulkhead location at 50% of nose
Width of the fuselage
Length of Fuselage
CG of Fuselage
Fuselage side angle
k.n factor (Nelson 74)
Bulkhead Area at front of fuselage
Bulkhead location at front of fuselage
Bulkhead Area at 63% of fuselage
Bulkhead location at 63% of fuselage
Bulkhead Area at rear of fuselage
Bulkhead location at rear of fuselage
position of the propeller
propeller length
Length of tail section of fuselage
Forward Diameter of Tail (where fuselage ends)
Rear Diameter of Tail (where fuselage ends)
CG of tail with respect to front of nose of plane
Wetted area of the fuselage tail
Bulkhead Diameter at 50% of tail
Bulkhead Area at 50% of fuselage
Bulkhead location at 50% of tail
Bulkhead Diameter at 75% of tail
Bulkhead Area at 75% of tail
Bulkhead location at 75% of tail
Bulkhead Diameter at 100% of tail
Bulkhead Area at 100% of tail
Bulkhead location at 100% of tail
Wetted area of the forward fuselage (from Calculation)
Wetted area of the mid fuselage
Wetted area of the full fuselage side
Wetted area of the entire fuselage
Length of the entire fuselage
CG of Stringers with respect to the front of the nose
Z cg coordinate of the payload relative to front of plane
DOES NOT TAKE INTO ACCOUNT SWEEP
Root chord of horizontal tail
Tip chord of horizontal tail
Taper Ratio of horizontal tail
Location of mac of horizontal tail
Location of hinge for horizontal tail
Location of front edge of root chord of horizontal tail
Location of rear edge of root chord of horizontal tail
Location of front edge of tip chord of horizontal tail
Location of rear edge of tip chord of horizontal tail
Location of front edge of root chord of horizontal tail
Location of rear edge of root chord of horizontal tail
Location of front edge of tip chord of horizontal tail
Location of rear edge of tip chord of horizontal tail
Z coordinate of CG of the wing
Root chord of vertical tail
Tip chord of vertical tail
Taper Ratio of vertical tail
Location of mac of vertical tail
Location of hinge for vertical tail
Location of front edge of root chord of vertical tail
Location of rear edge of root chord of vertical tail
Location of front edge of tip chord of vertical tail
Location of rear edge of tip chord of vertical tail
Location of front edge of root chord of vertical tail
Location of rear edge of root chord of vertical tail
Location of front edge of tip chord of vertical tail
Location of rear edge of tip chord of vertical tail
rotation angle
Design aircraft weight
Design flight altitude
Ref area is wing area, normal practice.