- Flight Club Aerospace

# Wing Design Day 14

Updated: Jun 23

### Calculations and refinements

Ever since the Design Team finished a draft of the fuselage a week or so ago, we’ve shifted our focus to verifying the safety and functionality of our design through a mathematical lens. When we initially sized the wing a few months ago, we just eyeballed the __graphs of the Clark Y airfoil__ and did some quick calculations on a whiteboard. This was enough to get us started in the right direction, but before we start spending a lot of money on parts, it’s important that we take a closer look into all our calculations. To start off, we __calculated our cruise Reynolds number__ based on our initial calculations which called for a 5ft chord with a thickness of 7.014in and a cruise velocity of 50 knots. The Reynolds number describes how turbulent or laminar the flow of air around our airfoil will be. Based on the turbulence of the air, an airfoil can behave quite differently, so it’s critical that we determine the Reynolds number to get accurate results. Below is a graph showing the relationship between angle of attack (Alpha) and the lift coefficient of the airfoil (Cl) with each line representing a different Reynolds number. Though all plots represent configurations of the Clark Y airfoil, it’s clear that the Reynolds number plays a large part in their stall behavior, with some stalling cleanly (highest plot) and some stalling unpredictably (lowest plot).

Source: __Airfoil Tools__

With our Reynolds number determined, we could isolate a specific plot which would more accurately represent our airfoil. Since Airfoil Tools only supplies Xfoil predictions for set Reynolds numbers, we had to round ours to the closest value. By clicking the “details” link next to the plot, we accessed the exact Xfoil data. To know if our wing is properly sized and will generate sufficient lift, we examined angle of attack and lift coefficient data. By plugging in __our weight calculations, mission requirements, and wing reference area__ into the __lift coefficient equation__, we determined the minimum lift coefficient required to achieve a maximum stall speed of 24 knots (as specified in __Part 103__). Unfortunately, we realized the Clak Y airfoil would stall long before producing a sufficient lift coefficient to maintain level flight at 24 knots.This means that our minimum speed would be greater than 24 knots, which would not only be dangerous to fly, but would also compromise the certifiability of our aircraft. In other words, our wing was simply too small.

To increase the wing reference area, we could either extend the wingspan or extend the length of the chord. Extending the wingspan would increase the __aspect ratio__ but would come at the cost of extending our heavy aluminum spars. Alternatively, we could increase the length of the chord which would decrease the aspect ratio and therefore increase __lift induced drag__. Since ultralights are inherently draggy airplanes, we decided to extend the chord to 6ft and save a little weight.

Our second round of calculations can be broken down into two categories: stall and cruise. According to __AC 103-7 section 21__, our stall speed must legally be no greater than 24 knots. We can make our cruise speed whatever we want, but ideally we’d like it to be the velocity at which the airfoil has the lowest __zero lift drag coefficient__.

For our stall calculations, we plugged in our new airfoil thickness, stall velocity, and kinematic viscosity at 59°F (a rough temperature average for San Francisco Bay Area weather). This produced a Reynolds number of approximately 1.81 E^4. We then selected the Clark Y plot with an__ Ncrit value of 9__ and a Reynolds number of 2.00 E^4. We scrolled down the __Xfoil prediction data__ and determined that at an angle of attack between 11 and 11.25 degrees, the airfoil would produce a lift coefficient between 1.3494 and 1.3609.

Source: __Airfoil Tools__

We then resolved the lift coefficient equation with our stall parameters and got a required lift coefficient of 1.356 which falls right within the range taken from the Xfoil predictions! In short, this told us 2 key things:

Our plane would stall at 11-11.25 degrees AOA

A reference area of 192ft^2 is just large enough to support level flight at 24 knots

Knowing our stall lift coefficient, it was time to calculate our required cruise lift coefficient. When we initially wrote our aircraft mission, we decided on a cruise speed of 50 knots (5 knots below the maximum speed of 55 knots). Our plane likely won’t have much range due to its electric powertrain so we wanted to have a high speed to cover a lot of distance in a short time. Admittedly, we could have determined the angle of attack with the lowest drag coefficient and then rearranged the equations accordingly to solve for the cruise, but we decided to just find the lift and drag coefficients at 50 knots to start. By plugging our __cruise parameters__ into the lift coefficient equation, we found that we would need a lift coefficient of 0.3627 to maintain level flight at cruise. We also recalculated our Reynolds number using our cruise parameters and we found that at a Reynolds number of 5.00 E^4 and an Ncrit value of 9, we would need an angle of attack from -0.25° to 0° to achieve the required lift coefficient. Conveniently, the drag coefficient is at its lowest between an AOA of -0.25° to 0°! We were super lucky in guessing a cruise speed which happened to align with the lowest drag coefficient and we would have otherwise had to rearrange the equations and take a slightly different process to determine the optimal cruise velocity. These calculations told us 2 important things:

When the spars of the wing are horizontal, the wing is actually at a 2 degree angle of attack. This is necessary to simplify some dimensions in the design and it means we’ll have to mount it at a negative 2 degree angle at the fuselage so that it has a net AOA of zero degrees.

At cruise, the wing will have an AOA of zero degrees.

Once we finished our calculations, it was time to implement them into our __wing design__. Over the past couple months, we’d been collecting a list of small changes we’d like to implement into the wing so we did a little more than just increasing the reference area. Here’s a change list:

New false rib (first) and old false rib (second) designs

We updated the false rib design (curved orange part) to be simpler and stronger. The previous false rib design was inspired by those used in the popular BeLite ultralights. However, the BeLite ultralights use carbon fiber and aluminum while we use house insulation. The new ribs are simpler in form and should be easier to manufacture using a hot wire.

New drag strut hole (first) and old drag strut hole (second)

We revised the drag strut holes in the wing to be pill-shaped instead of ovals. We realized that it would be very difficult to make a precise elliptical hole, and the pill shape forms a cleaner hole in the rib to allow the passage of the drag struts.

The tops and bottoms of all ribs are now covered by a thin 3/32” strip of aircraft grade birch plywood. While we haven’t yet constructed any ribs or done any testing of our own, ultralight enthusiast __Ian Lea’s rib tests__ suggest that plywood strips can significantly improve the strength of ribs for only a little additional weight. These strips will be epoxied in place during construction.

The wing chord can now be adjusted without breaking any wing geometry.

Now we’ve finalized our wing design, it’s time to look forward to some more nitty gritty physics work. Some key upcoming tasks include: loading our ribs until they break and optimizing the total number of them, spar thickness calculations based on chordwise and spanwise lift distribution, support strut placement calculations, bearing stress and tearout calculations, and much, much more.

*Editors note: the thought processes and design choices presented in this article don't necessarily represent those implemented into the final design and are subject to change. Flight Club Aerospace is a group of amateur students with no formal education in any fields of engineering. We present this information for educational purposes only, with the understanding that it is not to be re-created without adequate professional oversight and mentorship. For our latest designs and updates, please see our most recent blog posts.