Alright,
so we have our velocity of 40mph, or 18 m/s. Pretty nifty, huh?
and we have our lift, too. All that's left is to find out the
wing area!
According to the lift equation:
Everything else is constants! So let's figure those out:
the first is the coefficient of lift.
Generally, the coefficient of lift can be attributed to
the angle of attack.
With a 15 degree angle of attack, which is pretty standard, the CL is 1.65.
Next is air density, which for the sake of argument is in a temperature of -5 degrees Celsius, at standard pressure.
On a warm winter day, p, the density, is 1.3163
With a 15 degree angle of attack, which is pretty standard, the CL is 1.65.
Next is air density, which for the sake of argument is in a temperature of -5 degrees Celsius, at standard pressure.
On a warm winter day, p, the density, is 1.3163
And bang!
We're all set. all that's left is to plug in our
values.
I'm going to use 200 lbs, or 887 N as as my lifting force, because who wants to gain altitude slowly? So we have:
I'm going to use 200 lbs, or 887 N as as my lifting force, because who wants to gain altitude slowly? So we have:
L = 887 N
CL = 1.65
p = 1.3163 kg/m^3
v = 18 m/s
Plugging all these values into the equation, and solving for A, we get
A = 2.55 m^2!
so two and a half square meters. Or about 26.9 square feet.
To put this in perspective, the Cessna 162, the most popular recreational plane on the market has a wing area of about 120 square feet.
So not bad. Not bad at all.
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CL = 1.65
p = 1.3163 kg/m^3
v = 18 m/s
Plugging all these values into the equation, and solving for A, we get
A = 2.55 m^2!
so two and a half square meters. Or about 26.9 square feet.
To put this in perspective, the Cessna 162, the most popular recreational plane on the market has a wing area of about 120 square feet.
So not bad. Not bad at all.
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