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Statements I've seen about the elliptical wing:

  • This is not the planform which is elliptical, this is the lift distribution.
  • Only on an elliptical wing, the drag is regularly distributed. In other cases drag is generally higher near the wingtips.

I don't understand well these two statements. The only thing I have understood is that on the elliptical wing, at any distance from the root, for a constant angle of attack from root to tip:

  • Lift/drag ratio is constant
  • Lift and drag decrease from root to tip.

enter image description here
Source

My questions:

  • What is elliptical in the elliptical wing?
  • What is regular about lift or drag?
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It is both the planform and the circulation distribution. Note that circulation is not lift coefficient but bound vortex intensity. You can interpret it as local lift coefficient times local chord.

On the untwisted elliptical wing the local lift coefficient is constant over span, and changes in angle of attack over the linear range will change the lift coefficient equally everywhere. This, when combined with the elliptical chord distribution over span, means that the circulation distribution will stay elliptical over the linear angle of attack range. This is the special characteristic of an elliptical wing: While any wing can have an elliptical circulation distribution at one angle of attack (given the right twist distribution), the elliptical wing will keep that elliptical circulation distribution over the whole operating range.

With an elliptic circulation distribution comes also a constant induced angle of attack and downwash angle over span. I guess this is expressed by some authors with the term "regular".

However, only the aerodynamicists will see that as an advantage. Both weight and stall characteristics of elliptical wings are less than optimum; the low induced drag coefficient is bought with higher structural mass and, consequently, lift. A more triangular circulation distribution will yield the lowest wing weight and overall drag for a given non-lifting mass (that is, all mass that is not involved in lift generation, especially the payload). Note that for such a triangular distribution drag will be highest near the center.

When people talk about elliptical lift distribution, they mean lift per span. I prefer to use the more correct term circulation, since lift is a force as in pressure times area and can only be produced by a whole wing or at least wing section, not one spanwise station.

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(Edited after comments by mods. Thanks for guiding me through the process!)

The only thing that is elliptical is the planform shape of an elliptical wing.

Many people unfortunately confuse an elliptical pressure distribution with the pressure distribution over an elliptical wing. They are not equivalent.

On an untwisted elliptical wing the local lift coefficient is not constant over span, as some here and in many other places on the internet maintain.

Arguments from lifting line theory are not appropriate for discussing the behaviour of the flow near wing tips. It is unreasonable to expect lifting line theory to be valid near the wing tips because is not a consistent large aspect ratio asymptotic expansion. See: Van Dyke, "Perturbation methods in fluid mechanics", 1964.

The span loading includes a logarithmic term, hence it is not elliptical. Furthermore, it cannot induce a constant downwash, and so at the trailing edge the vortex wake does not start as a flat sheet.

The process whereby the vortex sheet rolls up is far more vigorous than if it started out as a flat sheet because the relatively weak effect of viscosity would be the main mechanism driving that rolling-up process. There is a strong upwash in the flow-field near to and around the wing tips which initiates the rolling-up process far more vigorously.

See, for example, among many other papers:

Peter F. Jordan, "Exact Solutions for Lifting Surfaces", AIAA Journal, Vol. 11, No. 8, 1973., pp. 1123-1129.

Peter F. Jordan, "On Lifting Wings with Parabolic Tips", ZAMM 54, pp. 463-477, 1974.

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    $\begingroup$ Hello Lysistrata, welcome to Aviation.stackexchange.com. I think your answer has great potential, but currently it is only a comment to Peter Kämpf's answer. Can you edit your post and answer the original question, thereby addressing where you think Peter's answer falls short? Otherwise it may be flagged as "comment to other post" and subsequently deleted. $\endgroup$ – DeltaLima Oct 11 '17 at 12:12
  • $\begingroup$ My comment is a criticism of Peter's answer, specifically regarding constant spanwise lift coefficient. (I have no problem with the other parts of his thoughtful answer.) I gave reasons for why I believe that part of his answer is incorrect, and I have cited appropriate references. I'm not sure that I can do much more than that. $\endgroup$ – Lysistrata Oct 11 '17 at 12:43
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    $\begingroup$ Welcome too, I have to agree with DeltaLima. It's not that your comment is bad, it's great, but the site rules don't allow this format. Please answer the original question in your post as well, to prevent your post from being deleted. It's just to make sure your post fits the community rules, because the community on stack-exchange is strict. $\endgroup$ – Noah Krasser Oct 11 '17 at 12:52
  • $\begingroup$ @Lysistrata I understand you want to criticise Peter's answer, and I think that is fine. However, this is not a forum, it is a question & answer site. Each posted answer should in fact answer the question. Comments can be made under an answer to ask for clarification or to criticise. Since your comment is too big to be left in the comment field, the site's format causes a problem here. I am pretty sure that the community will (and I agree with that approach) vote to delete answers that are in fact comments, just to prevent this site to develop into a discussion forum. $\endgroup$ – DeltaLima Oct 11 '17 at 12:59
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    $\begingroup$ For a moment I thought you deleted your answer and all the good references were gone. Thank you for editing your answer and putting it back in! By the way, we (@NoahKrasser and me) are not mods, we're just ordinary users like you. It's the combined effort of the community that makes this site great. $\endgroup$ – DeltaLima Oct 11 '17 at 14:21
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The beautiful shape of the Spitfire planform also made it difficult and expensive to produce. The target was an elliptical lift distribution, at the time of design regarded as resulting in the highest lift/drag ratio.

enter image description here

This lift distribution is obtained by shaping the wing geometry, in the case of the Spitfire by making the chord an elliptical function of wing span. The other way of achieving this is to use a combination of wing taper and wing twist: the chord reduces linearly with span, plus the wing is twisted with the wing tip having a lower angle of attack than the wing root.

enter image description here

This shape creates elliptical lift distribution as well, but at only one AoA of the aircraft. The elliptical wing has an elliptical planform and elliptical lift distribution throughout all aircraft AoA.

The eliptical planform wing has a constant AoA, and drag changes as a function of wing chord only. The twisted wing has a wing root with a higher AoA, and a wing tip with lower AoA than aircraft AoA: the fat bit of the wing has the higher drag, since wing drag is a function of chord and AoA. So total wing drag of the tapered wing is higher than that of the elliptical wing.

The tapered twisted wing rules though, because:

  • It is cheaper and faster to produce.
  • The wing tip stalls last, and that is where the ailerons are.
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    $\begingroup$ Actually, the reason for the elliptic shape was to house the guns in the thinnest possible wing. Mitchell was cited by Shemstone as follows: "I remember once discussing the wing shape with him and he commented: “! don’t give a b..... whether it’s elliptical or not, so long as it covers the guns!” $\endgroup$ – Peter Kämpf Jul 4 '17 at 21:19

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