Hi. I am an aerospace engineering student at uni. I have been given an assignment that needs to be...

Question

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?

Lalit · Accepted Answer

Initial Sizing
	Important Variables:
	Kus = 1	Fixed sweep 
	A = 0.86	Unpowered Sailplane
	C = -0.05
	W_payload
	0.110231		lb
	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	lb
	Fuselage length = 	0.7882666489421296	ft
	***********************************************
	Other Parameters
	Airfoil: 	NACA 4418
	Range:	5.0	m
	Takeoff wing loading	6.0	lb/ft2
	Aspect Ratio	7.0
	Wetted Area Ratio	4.0
	************************************************
	Wing Length:	Wo/Takeoff wing loading
		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
	  Wing Loading		190.64	oz/ft2
	  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 Number
		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
	  Wing Loading		196.98	oz/ft2			Specify Speed
	  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.

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...

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