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Wing Aspect Ratio (Newbie to Aerodynamics)

  1. Feb 6, 2014 #1
    1. The problem statement, all variables and given/known data
    A tailless aircraft of 9072kg mass has a delta wing with aspect ratio 1 and area 37m2. Show that the aerodynamic mean chord of a delta wing,
    [itex]\frac{\int_0^{b/2} c^2 dy}{\int_0^{b/2} c\ dy}[/itex]
    is two-thirds of its root chord and that for this wing it is 5.73m.

    2. Relevant equations
    [itex]AR= \frac{b}{\bar{c}}[/itex]
    [itex]\frac{\int_0^{b/2} c^2 dy}{\int_0^{b/2} c\ dy}[/itex]

    3. The attempt at a solution
    Problem 1.
    [itex]AR= \frac{b}{\bar{c}}=1[/itex]
    [itex]b= \bar{c}[/itex]
    I don't get it. If the wingspan equals to the mean chord then it won't be delta wing anymore, wouldn't it?
    220px-Wing_tailless_delta.svg.png
    As you can see the root chord is smaller than the tip chord hence [itex]\bar{c}[/itex] must be smaller than b/2. Where do I get myself wrong?


    Problem 2

    [itex]\frac{\int_0^{b/2} c^2 dy}{\int_0^{b/2} c\ dy}[/itex]
    How do I find the equation for c to solve this integral? Is there any of other way? I know the bottom integral is the area of one wing but I don't know the other one.
     
  2. jcsd
  3. Feb 7, 2014 #2

    CWatters

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    I can't help with the rest of the problem but if I don't see a problem with the wingspan being equal to the mean chord. The plan form won't be an equilateral triangle but it would still be a triangle and classed as a delta.
     
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