This page captures the design intent and the design analysis performed on the Super2. This aircraft is still under construction so has not been flight test, therefore all of the data supplied here is theoretical.

Design Analysis Table of Contents

• Genesis of the all Composite KR
• Design Goals
• Modifications to KR2S
• Why Composite?
• Overall Aircraft Sizing

What were my goals in building a homebuilt plane? How did they lead me to an all composite version of the KR? They were many and some were mutually exclusive.  I wanted the following out of an airplane:

• Economy – closer to 5 gph than 10
• Inexpensive to build, closer to $15,000 than $150,000
• Safe Airplane
• 2 seater with side by side seating
• low wing
• Quick, in excess of the SLA limit
• forgiving handling qualities
• fun to fly
• not to difficult to land
• Usable load to include two adults and a little luggage
• A plane I could build myself
• Good taxing qualities
• Simple
• Reliable
• Take advantage of the latest technologies and methods
• Able to go cross country, but fun to fly locally.
• A plans built plane – I want to build as much of it as I can, even the engine.

After reviewing the offerings I settled on the Rand-Robinson KR2S.  It is simple, inexpensive to build and operate and the specifications touted by Rand-Robinson indicated it would meet my requirements.  The second reason I settled on the design was the KR community; there are many active builders and even more active examples flying with well-documented characteristics and capabilities.

I ordered the plans and committed myself to the KR2S.  Upon receiving them and continuing my research I realized that the design was quite dated and in fact could not meet all its specifications, at least a single example could not meet them all at the same time. Plus, I am a tall guy and I really would not comfortably fit in the cockpit with a passenger and a bit of baggage.  No worries, many people have wrestled with these same issues and have dealt with them.  I would follow in their footsteps and modify the KR2S design.  I settled on the following modifications:

1. Use the KR-2S as the starting point
2. Powerplant - 2700cc Corvair
3. Use a front starter on engine
4. Tri-gear
5. new KR airfoils for wing, vertical and horizontal stabilizors.
6. new Angle of attack for main wing
7. new horizontal stab incidence
8. Increase area of horizontal stab, but not elevator.
9. Slightly larger rudder, extends in front of hinge line above vertical stabilizer. (counter weight here).
10. Balanced control surfaces - both aerodynamic and static
11. move firewall forward
12. move tail back
13. widening the fuselage at top even with shoulders
14. move widest fuselage point to coincide with shoulders
15. Canopy raised 2”
16. Small windows in the turtle deck
17. Dual Center sticks
18. Dual rudder pedals mounted to floor
19. Pilot only brakes on the rudder pedals
20. Standard Rudder control cables routed down center instead of sides
21. wing tanks – small header tank
22. Slightly longer wings, washout at tips, small winglets
23. Slotted Flaps
24. Redesign the fuselage top longeron placement to result in a flat top boat, coplanar with the aircraft's horizontal datum plane.
25. 30 gallon fuel - 3 gal header, 13.5 each outboard wing.
26. cable to bellcrank aileron control
27. Bent spar - constant dihedral wing from fuse side to wing tips.

Given these modifications I laid out the new fuselage as shown below:

Some performance characteristics of the KR2S that have been addressed by lengthening the fuselage and increasing the size of the horizontal stabilizer include pitch sensitivity, small allowable CG range

Horizontal Tail Sizing

A measure of the tail effectiveness is the horizontal tail volume coefficient: A well-behaved aircraft typically has a value which falls in the range: 0.30 ... 0.60. If the value is too small, the aircraft’s pitch behavior will be very sensitive to the CG location. It will also show poor tendency to resist gusts or other upsets, and generally “wander” in pitch attitude, making precise pitch control difficult. Notice that the KR2S is at the low side where as the KR2-VX is in the middle of the range. It is an interesting exercise to calculate the value for comparable aircraft. The KR2S has the smallest Horizontal Tail Volume Coefficient of all of the kit planes I looked at in its class.

The horizontal tail volume coefficient also directly affects the allowable CG location. The derivation of the formula is beyond the scope here, but it is straightforward to evaluate for any aircraft configuration. The KR2-VX has an allowable CG range double that of the KR2S.

Vertical Tail Sizing
The primary role of the vertical tail is to provide yaw damping, which is the tendency of yaw oscillations of the aircraft to subside. The vertical tail also provides yaw stability, although this will be almost certainly ensured if the yaw damping is sufficient. One measure of the vertical tail’s effectiveness is the vertical tail volume coefficient: Most well behaved aircraft typically have a value which falls in the range: 0.02 ... 0.05. If this value is too small, the aircraft will tend to oscillate or “wallow” in yaw as the pilot gives rudder or aileron inputs. This oscillation is called Dutch Roll, and makes precise directional control difficult. The KR2S vertical tail size and moment is within the acceptable range, however the vertical tail was increase somewhat on the KR2-VX.

When running a series of analysis on the truss box fuselage it was found that there were some issues including tortional rigidity of the rear fuse.  These were addressed by: 1.) Additional trussing in the rear portion of the fuselage. 2.) Triangular solid members where the sides meet the firewall. 3.) Additional shear web mounted on top of the fuselage half way between seat and the tail.

One assumption I have made is that the turtle deck does not add any structural strength to the fuselage. Depending on the method of attachment, the turtle deck does add some stiffening toward the tail end.


The triangular blocks at the top and bottom where the fuse meets the firewall are intended to help transmit the load of the engine mount to the fuselage. there will be angles bolting behind the firewall tying the engine mount into these triangular blocks.

Currently the design calls for a small shear web across the top of the fuselage just behind the seat. I have added a second one halfway back between this one and the tail. An important point to make here: The seat back is an important structural bulkhead in the fuselage. It should be solidly tied to both fuselage sides. I have seen aircraft where the seat back is hinged forward--this would be fine as long as when the seat is in its back and locked position, it is securely tied to the fuse sides.

At this point I was quite happy with the design and believe it to be as good as any KR flying.  The additional weight was minimal and the strength and tort ional rigidity of the rear fuse were sufficient to handle the increased moment arm and increased size of the horizontal tail. 

A friend of mine, Zeke Smith, talked me into building my wings from the ‘outside in’ using a female wing skin mold, then building all the wing internals on this wing skin. This is a technique that he espouses in his latest book “Advanced Composite Techniques”.  As I was won over to the idea of attempting this, I got to thinking, why not go all composite?  I already had the wooden truss box fuse model in the computer so I ran a comparative analysis of that design against one with a composite construction. The structural analysis shows that the composite fuselage has superior strength to weight. It is actually not that much lighter, but stronger and stiffer given my longer fuselage. The analysis shows that the wooden structure is plenty strong, but has a much more uneven stress distributions. 
This is something that Ken Rand wanted to do at some point, create an all-composite version of his plane.

So using techniques from Zeke’s books, I designed a composite KR fuselage and tail feathers.  The fuselage is easy to build using 1/2" last-a-foam. The panels are fabricated on the floor or work bench so little glassing is required bending over into the fuselage.  The foam panels are only bent in one axis. The fuse sides are laid at the KR 82 degree angle and curved in, and the rear sides of the fuse twist from the 82 degrees to vertical at the tail. The front deck and turtle deck are made the same way as the current KR. One difference is that I am glassing the fuse and turtle deck together as I am using the whole rear fuse "tube" as a structural member. I am rounding the bottom corners of the fuselage as has been done on a few KRs.

The technique I am going to use has you glass the outside of the last-a-foam first, then a large piece of flat MDF or melanine coated with mold release is laid on top while the glass cures. This gives a nice smooth surface that is finished easier. Then the piece is cut to shape as defined by the CAD model and bent into the proper shape. A form is used to hold the fuse in position while the inside is glassed. Bulkheads are added and there you go....a boat.

Once I decided to build an all-composite airplane I stepped back and did a top down design analysis of the aircraft.  Following are the major steps of that analysis.