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Aerospace How much pop from a Kitewing?

  1. May 11, 2009 #1
    There's a product on the market called a Kitewing. It's a hand held sail for ice, water or land. It can be swung horizontally to lift. I'm curious to know how much mimium wind speed would be needed to get some pop?

    There are some utube videos out where some get 5 ft of air from level ground. Suprizing for such a small wing.

    The sail is symmetric like a wing, having a 5.5 square meters, with an aspect ration of about 2.2, and a roughly eliptical profile. Wing span and washout aren't given.
     
    Last edited: May 11, 2009
  2. jcsd
  3. May 12, 2009 #2
    So I guess there aren't any AEs around who have any interest in fluid flows without a cabin wraped around them and 500+ horses in the front...
     
  4. May 12, 2009 #3
    Your question doesnt leand itself to a simple answer. Aerodynamics is highly experimental. There isnt a magic formula you can use to arrive at the answer you want.
     
  5. May 14, 2009 #4
    I've run out of time. I'll have to generate some numbers tomorrow afternoon.
     
  6. May 15, 2009 #5
    I'm looking for a, not too, rough idea of how well it could perform. So far I have,

    Mg = ½CLρV²S

    ρO = 1.225 kg/m³, density of air at sea level
    ρ = 1.1 kg/m³
    CL_MAX=1.2
    V = 30 mph = 44 fps = 13.4 m/s
    S = 5.5 m²
    g = 9.8 m/s², acceleration due to gravity.
    M = 67 kg
    Mg = 146 lb ...very marginal.

    For a sail on land, we could assume a "beta" of at least 30 degrees. This means wind speed is 15 mph to obtain a 30 mph relative wind, V at the most favorable tack. The ground speed would be 30*0.866 mph.

    For a wing that is mostly single sided except along the leading edge, I'm assuming a max coefficient of lift of only 1.2.

    I still don't know if I'm using the right coefficient of lift. CL_MAX is the lift coefficient of an infinite aspect ration section.
     
  7. May 15, 2009 #6
    Sorry, that's way wrong. You want 'not too close' build or use a wind tunnel, or find data generated by someone who has. You've pretty much assumed 99.9% of the problem. Your answer is probably as much as 40% off.
     
  8. May 16, 2009 #7

    FredGarvin

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    You're estimating on the Cl and treating like an infinite wing. Of course it's going to be off, but, IMO, for a first guess, those numbers don't seem all that bad. At least you aren't in the area of an order of magnitude off. Especially since you are treating Cl as a constant (which it isn't) and who knows just what the relative velocity a wing actually sees is. As a total SWAG I think you're not too bad. Just understand that to be accurate you need way more information.
     
  9. May 16, 2009 #8
    I don't understand the sources of large amounts of error. Is it just CL? But, this is what I was asking. How is CL max obtained from CL max from section data?
     
    Last edited: May 16, 2009
  10. May 16, 2009 #9

    FredGarvin

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    It's usually not. It is done experimentally...hence Cy's comments.
     
  11. May 16, 2009 #10
    I'll read theory of wing sections.
     
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