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# Hi. I am an aerospace engineering student at uni. I have been given an assignment that needs to be done by this Sunday. I have to design a sailplane that can be made from "household items" and can...

Hi. I am an aerospace engineering student at uni. I have been given an assignment that needs to be done by this Sunday. I have to design a sailplane that can be made from "household items" and can carry a payload of "50g". I've been told that the method to be used for this is "Raymer's method" and that all equations should be stored in an excel sheet so that if one value changes, there is no need to redo all the equations, and the professor would like to see this excel sheet. I would also like a written up version of all the equations so that I can fully understand and explain to my professor what is being done in the excel sheet. It would be preferred to use a fixed-sweep wing rather than a variable-sweep. Is this something you could help with please?
Answered 9 days AfterMar 08, 2022

## Solution

Lalit answered on Mar 11 2022
Initial Sizing
Important Variables:
Kus = 1    Fixed sweep
A = 0.86    Unpowered Sailplane
C = -0.05
0.110231        l
Wo Equation:    W-0.86*W^0.95 = W_payload        Variable    Value:        Equation    Constrain:
W    0.8340585381595877        0.11023090791097667    0.110231
Wo (Takeoff Weight)    0.83406    lb    Without Payload
*****************************************************
Fuselage Length:    Length = a*Wo^c        For an unpowered sailplane:
a =     0.86
c=    0.48
Wo =     0.83406    l
Fuselage length =     0.7882666489421296    ft
***********************************************
Other Parameters
Airfoil:     NACA 4418
Range:    5.0    m
ft2
Aspect Ratio    7.0
Wetted Area Ratio    4.0
************************************************
0.34307667999999997    ft    ~4.2 inch
Span    0.6861533599999999    ft
Wetted Area:    Aspect Ratio/ Wetted Area Ratio
1.75
Initial Sizing
Wing
Model Weight (ounces)
13.34496
Sweepback            Sweepback        Sweepback
0.0
Curtis Suter: Measure from Root Leading Edge.
0.0
Curtis Suter: Measure from Root of this panel.        0.0
Curtis Suter: Measure from Root of this panel.        Sweepback
0.0
Curtis: Measured from Root of this Panel.
Root Chord        1st Panel Chord            2nd Panel Chord        3rd Panel Tip Chord
1.2        1.2            1.2        1.2        Tip Chord
0.0
1st Panel Span            2nd Panel Span        3rd Panel Span        4th Panel Span
1.4            1.4        1.4        0.0
Note: All panel spans are measured perpendicular to the aircraft centerline
Distance from Wing Trailing Edge to Stab Leading Edge
4.0
Span    Chord    Span    Chord    Span    Chord    Span    Chord
0.0    0.0    1.4    1.2    2.8    1.2    4.199999999999999    1.2
Distance from Wing Trailing Edge to Fin Leading Edge                0.0    1.2    2.8    1.2    4.199999999999999    1.2    4.199999999999999    1.2
4.3                1.4    1.2    2.8    0.0    4.199999999999999    0.0    4.199999999999999    1.2
1.4    0.0    1.4    0.0    2.8    0.0    4.199999999999999    0.0
0.0    0.0
Red Dashed Line
AC    0.0    0.90        0.00    2.10
0.90    0.90
MAC distance    2.10    1.20    MAC Length
MAC distance    2.10    0.00    MAC Length
Total Wing Results
Total Span        8.40    in.
Total Area        10.08    in2
Mean Chord (area/span)        1.20    in.
Mean Aerodynamic Chord (length)        1.20    in.
Wing Aspect Ratio        7.00        Note: Red Triangle is Aerodynamic Center (AC) of the Wing
Taper Ratio        1.00         Blue line is MAC location
Location of 0% point        0.00
Curtis Suter: Measured aft from Leading edge at wing root.    in.     Where Blue MAC line and Red dashed line intersect is the Aerodynamic Center of the Wing
Location of 25% point        0.30
Curtis Suter: Measured aft from Leading edge at wing root.
in.
MAC distance from root        2.10    in.
Reynolds Numbe
Effective Wing Results
Curtis: These results are how the wing is actually seen in flight if your wing has Dihedral.
Note: The Dihedral Tab must be completed.                Airspeed    15.0    mph
Total Span        8.13    in.        Result    14040
Curtis: Standard Day:
- 59 degrees Farenheit
- Sea Level Altitude
- Barometric Pressure 29.92 in hg
Total Area        9.76    in2
Mean Chord (area/span)        1.20    in.        Speed, G and Cl Calc
Aspect Ratio        6.77    in.        Min (Stall) Airspeed     10.6    mph
Cl    41.46
Curtis: Affected by Weight, Total Wing Area and Speed above.
Assumed Standard Density at Sea Level

Curtis Suter: Measured aft from Leading edge at wing root.
Curtis Suter: Measure from Root Leading Edge.

Curtis Suter: Measured aft from Leading edge at wing root.

Curtis: These results are how the wing is actually seen in flight if your wing has Dihedral.
Note: The Dihedral Tab must be completed.
Curtis Suter: Measure from Root of this panel.    Max Airspeed    42.4    mph
G-load at Max Airspeed    15.7    G
Specify Cl
Cl    0.95
Required Calculations, please ignore.                    Min (Stall) Airspeed    70.8    mph
Panel 1 Results                    Max Airspeed    283.1    mph
Area (dS1)        1.68    in2        G-load at Max Airspeed    16.0    G
25% MAC (x1) from R.L.E.        0.30    in.
MAC for this panel        1.20    in.
Sweep distance at MAC        0.00    in.
Sweep Angle (leading edge)        0.0    degrees
MAC distance from root        0.70    in.
Effective Span        1.40    in.
Effective Area        1.68    in2
Panel 2 Results
Area (dS2)        1.68    in2
25% MAC (x2) from R.L.E.        0.30    in.
MAC for this panel        1.20    in.
Sweep distance at MAC        0.00    in.
Sweep Angle (leading edge)        0.0    degrees
MAC distance from root        2.10    in.
Effective Span        1.38    in.
Effective Area        1.65    in2
Panel 3 Results
Area (dS3)        1.68    in2
25% MAC (x3) from R.L.E.        0.30    in.
MAC for this panel        1.20    in.
Sweep distance at MAC        0.00    in.
Sweep Angle (leading edge)        0.0    degrees
MAC distance from root        3.50    in.
Effective Span        1.29    in.
Effective Area        1.54    in2
Panel 4 Results
Area (dS4)        0    in2
25% MAC (x3) from R.L.E.        0    in.
MAC for this panel        0.80    in.
Sweep distance at MAC        0.00    in.
Sweep Angle (leading edge)        0.0    degrees
MAC distance from root        4.20    in.
Effective Span        0.00    in.
Effective Area        0    in2
Does your wing look like this?
0    0    1.4    1.4    0    0    1.2    1.2    0    0    1.4    2.8    2.8    1.4    1.2    1.2    0    0    2.8    4.1999999999999993    4.1999999999999993    2.8    1.2    1.2    0    0    0    4.1999999999999993    4.1999999999999993    4.1999999999999993    4.1999999999999993    1.2    1.2    1.2    0    NP    0    0.9    MAC    2.1    2.1    1.2    0    0    2.1    0.9    0.9    Inches
Inches
Wing
Horizontal...
SOLUTION.PDF