# Explained intuitively, why does aspect ratio affect induced drag?

Over the last few hours, I've been trying to intuitively understand induced drag, and how aspect ratio affects it. I already know the equations, but while they explain the relationship, they do not really explain anything, I want to understand what is happening physically. I've read on many answers in this community, specially by Peter Kämpf, but I've been unable to attain an intuitive understanding.

I will explain my line of thinking, hopefully I can be corrected on any misconceptions, or wrong assumptions.

First of all, my way of thinking about lift is simply airflow being redirected. If airflow is redirected by a surface, a force in the opposite direction is applied on said surface. This means that for lift to be generated, downwash must exist, therefore induced drag is an inseparable side-effect of generating lift. Let's imagine 2 theoretical wings, both of which have the same area, but differ in aspect ratio. If induced drag depends on the downwash angle, why would a longer wingspan reduce the angle? If the downwash angle is reduced, then the amount of air being redirected (total mass) must increase to keep lift equal, how can that happen when the wing area is equal?

All of the sources I am able to find blame induced drag solely on wingtip vortexes, since they cause downwash, but the entire wing is creating downwash, so what gives?

If tip vortexes are what cause induced drag, how does a longer wingspan reduce the induced drag coefficient? As an example: If the span of rectangular a wing is increased without changing the chord length, the aspect ratio will increase, which according to the math, will lower the induced drag coefficient. How does a longer wingspan affect the vortexes such as to reduce the downwash?

• "Intuitively", airplanes wouldn't fly at all. So it's difficult to understand what variety of "intuitively" would be a satisfactory answer here. Feb 5, 2021 at 23:48
• @PeterDuniho, well, that depends on your experience and powers of observation I guess, but I disagree with that statement. If you have ever observed and felt a fan blowing air, ever stuck your hand out of a car window to play with the AOA of your palm, it isn't that big a leap in imagination to link the idea of a propeller and a wing, and to thereby grasp the fundamental forces that allow a heavier than air craft to fly. Aug 21, 2022 at 15:31
• I have a hypothesis which is that our intuition about flow comes from observations of water. In that case, if you observe water rushing down a river and meeting rocks and other obstacles, you will come the wrong conclusion. If you don't like that, let’s just go with the fact that if you intuitively assume air is inviscid, what the great Euler did, then you also get no lift. So, we might be able to observe the effects of the wind from a storm, but that does not give us an appreciation for Navier-Stokes. Hence, @PeterDuniho is making a reasonable statement. Aug 21, 2022 at 18:42

Let's imagine 2 theoretical wings, both of which have the same area, but differ in aspect ratio.

Then the wing with the higher aspect ratio also has more span. This is what counts.

If induced drag depends on the downwash angle, why would a longer wingspan reduce the angle?

Because the wider wing will affect more air. Think of the air affected by the wing as what flows through a tube, the diameter of which equals wing span. Like in the picture below. Of course, for clarity, the amount of bending the stream tube undergoes due to the wing is greatly exaggerated here. In reality it is a few degrees at most.

how can that happen when the wing area is equal?

Wing chord does not count here as long as the amount of stream tube bending can be done by the skinnier wing. More chord will not affect the result. Only when too much is being asked of a limited chord will the wing stall. At lower lift coefficients, more chord will only increase friction drag.

In reality the influence of the wing fades the more you move away from it. This picture of a stream tube is a simplification which you will also find in propeller theory, and it gives the correct result, because what you neglect in the far field you compensate by assuming a constant influence over the near field.

All of the sources I am able to find blame induced drag solely on wingtip vortexes

You do well to disregard those sources. They have the causality backwards.

• This was a great answer, as always, and it fundamentally improved my understanding of lift as well as gave me a very simple (and intuitive!) way to explain to others why wingspan matters so much for efficiency. However I honestly struggle to understand the graphic. I know what it wants to show, but I just can't get my eyes to see what they're supposed to there. I know I should be seeing a tube deflected downward, but I see two circles, one tangent to a wingtip and the other floating in space. Just an FYI on an otherwise impeccable post. May 25 at 10:41
• @KennSebesta Thank you, that is the kind of feedback which is most helpful for me. I will try to improve the graphic. May 25 at 17:33
• @KennSebesta Is this any better? Like last time, I used Sketchup and increased the contrast, but I'm afraid it is not fundamentally different. May 25 at 20:30
• Yes, I think so! The shading helps tons. May 25 at 20:33

I use exaggerated example,with two wings with same area producing same lift.

Both wing has same area 30m2,lets say high aspect wing has span of 30m and chord line 1m and low aspect wing has span 5m and chord line 6m.

As you can see low aspect has huge area of pressure loss,to compensate pressure loss wing must fly at greater AoA to get same lift,which increase induced drag. This is my interpretation. See if it helps. Induced drag can be thought of as the energy consumed in making lift, in other words, the energy consumed in inducing a package of air to move down as a result of the wing's passage. It's the energy consumed in accelerating a mass; wing, propeller, helicopter rotor, it's all the same.

Vortices are just a manifestation of energy "leakage" in the process of inducing a package of air to move down. Some of the air, instead of being induced to move down, escapes around the wing tip, and it extends well beyond the core right at the tip were the strong vortice is; there's a large flow field circulating around. It's like a snow plow where snow near the ends of the plow is able to escape around the ends and avoids being pushed forward.

A higher aspect ratio wing is moving a longer and skinnier package of air compared to a low aspect ratio one of the same area that is moving the same total mass of air. This means that the escape route around the tip is a smaller proportion of the total mass affected, so the overall losses, the amount of leakage, is a smaller part of the overall package of air being induced to move down.

If both the high aspect wing and low aspect wing have the same area, meaning they are both attempting to redirect more or less the same total mass of air, the high aspect one with the lower losses from tip leakage*, relative to the total package of air affected,* is able to get more work from the same package of air. If it's getting more work out of the same package of air, it can operate at a slightly lower angle of attack for the same net lift force generated, and needs less total energy to generate that lift force, and therefore has less induced drag.

• I am pretty sure the tip leakage is a red herring. The wing with larger span is affecting a lot more air. Feb 5, 2021 at 23:51
• But the chord is narrower. The air package is longer, but shallower. In any case, then why to end plates work (if large enough) if not to inhibit the circulation? Feb 6, 2021 at 1:07
• The end plates force air higher above and lower below the wing to be affected and contribute to the lift creation. So you are kind of correct, they prevent circulation as in the air below being pushed to the sides rather than down and the air from the sides instead from above filling in, but note that the scale is again comparable to the wing span and the “large enough” means much higher than the wing span here. Feb 6, 2021 at 10:26

Your understanding of induced drag is correct. It is caused by turning the air flow and the force that does it must be tilted, otherwise conservation of energy would be violated.

The stream ‘tube’ affected by the wing is obviously as wide as the wing, and always considered to be roughly as high as wide. That is, wings with higher span affect air to greater height above and below them and therefore much more of it. This matches the fact that, for given lift, induced drag is inversely proportional to the square of span.

An intuitive, approximate, explanation is that the air below the middle can't escape directly to the sides and must go further down the wider the high-pressure region is, and similarly above the wing the air from sides is already used up for filling above the wing tips, so air from higher up is needed to fill in in the middle.

Or in other words, the affected region is approximately circular, because the pressure is being equalized in all directions.

The lower aspect ratio wing has to fly at higher angle of attack to compensate. I think, but am not completely sure, that it can do that because the longer chord allows turning the air more gradually—with the same lift and the same area, the pressure drop is the same (pressure being force per area), but it acts longer on the stream—so it can be turned by higher total angle before the flow separates. But it is to an extent only—both $${C_L}_{max}$$ and $${C_L}_\alpha$$ depend on the chord length and the lower aspect ratio wing will produce less lift.

Do not focus on aspect ratio. Also, do not focus on drag coefficients. Instead, work in terms of dimensional drag and lift. Airplanes don't fly on coefficients, they fly on forces...

Starting from a simple parabolic polar.

$$C_D=C_{D,0}+\frac{C_L^2}{\pi\,e\,AR}$$

$$D=C_D\,q\,S$$

$$L=C_L\,q\,S$$

$$AR=\frac{b^2}{S}$$

Throwing all this at dimensional drag step by step...

$$D=C_{D,0}\,q\,S + \frac{C_L^2}{\pi\,e\,AR}\,q\,S$$

$$D=C_{D,0}\,q\,S + \frac{\frac{L}{q\,S}^2}{\pi\,e\,AR}\,q\,S$$

$$D=C_{D,0}\,q\,S + \frac{L^2}{\pi\,e\,AR\,q^2\,S^2}\,q\,S$$

$$D=C_{D,0}\,q\,S + \frac{L^2}{\pi\,e\,AR\,q\,S}$$

$$D=C_{D,0}\,q\,S + \frac{L^2}{\pi\,e\,\frac{b^2}{S}\,q\,S}$$

$$D=C_{D,0}\,q\,S + \frac{L^2}{\pi\,e\,b^2\,q}$$

The first term is the dimensional parasite drag. The second term is the dimensional induced drag.

Notice the appearance of the term $$\frac{L}{b}$$. We call this the span loading. Instead of aspect ratio, the span loading is what is important for induced drag. Or, for fixed lift, the span is what is important.

The area (and aspect ratio) becomes important when you want to figure out what speed your best L/D occurs at -- and other things -- so it isn't totally unimportant. However, the thing to recognize from this analysis is that induced drag is reduced by increasing span.

Spreading the act of generating lift over a greater span will reduce induced drag. It isn't about some ratio of wing shape -- it is about spreading the lift across a wider span. Similarly, the shape of the lift distribution is a driver of induced drag -- you already know elliptical is best.

Something similar happens for induced power for rotorcraft. Because of this, all aircraft (that want to be efficient) want as large of a span (diameter) as they can get. Consequently, with very few exceptions, all aircraft are span constrained. Some new aircraft designers believe that they don't have a span constraint -- they just haven't figured out what their span constraint is yet. A great early step in design is to figure out your span constraint if your customer didn't state one.

Starting with the simplest example, a fully symmetrical airfoil, aspect ratio (of a straight wing) can be described as the ratio of area to chord, or area to span, or ...

higher ratio of leading edge to area

Why is this important?

Because the total lift vector here is pointing forwards, creating a thrust component!

Yes, that's right, induced thrust!

lowers the overall induced drag of the wing.

That, and proportionally lower interferences at the wing tip and fuselage make high aspect wings more efficient for gliding.

It's important that Reynolds Number also plays an important role here.

For very slow soaring birds, such as vultures and eagles, the low aspect wing is actually better to catch the energy of updrafts. In much the same way as a circular parachute is better than a long thin one, this type of wing cannot take advantage of very low net drag contribution of upper forward wing lift because it is too slow (Reynolds number too low to generate it) and there is greater pressure "leakage" from the bottom due to the higher perimeter to area ratio of the higher aspect design.

But in size and speed from the albatross to full scale gliders, high aspect ratio is the way to go for best glide distance.

This leads to the conclusion that "top lift" mechanism (Coanda/Bernoulli) generates less induced drag than simple Newtonian action/reaction deflection of air from the bottom of the wing for a given amount of lift.

• Can you please better explain the "induced thrust" phenomenon? Maybe with a practical example. And why Bernoulli generates less induced drag than Newton? Thanks Aug 21, 2022 at 6:40
• @sophit the forward upper surface of the wing has its lift vector tilting ahead. This decomposes into vertical lift and a bit of forward "thrust". Go to Airfoil Tools on the net and see how Reynolds number affects L/D ratios. Aug 21, 2022 at 14:56
• Ok but when does it happen? Do you have a practical example? Aug 21, 2022 at 15:46
• When the Reynolds number is high enough. This is why, 100 years ago, as planes got better engines, wing design changed by filling in the wing bottom (no more undercamber). Aug 21, 2022 at 17:36

Because percentagewise the tips are a much smaller part of the whole lift. So there are less vortices generated at the tips and that means less induced drag.