Mailing List flyrotary@lancaironline.net Message #40458
From: Ed Anderson <eanderson@carolina.rr.com>
Subject: Re: [FlyRotary] Re: Naca Report on Radiator Thickness
Date: Wed, 21 Nov 2007 23:08:56 -0500
To: Rotary motors in aircraft <flyrotary@lancaironline.net>
Work on the Cozy, Ron.  Because then something useful will get done for certain {:>)

Ed
----- Original Message ----- From: "Ron Springer" <ron2369@sbcglobal.net>
To: "Rotary motors in aircraft" <flyrotary@lancaironline.net>
Sent: Wednesday, November 21, 2007 9:20 PM
Subject: [FlyRotary] Re: Naca Report on Radiator Thickness


Well, engineering judgement tells me that your drag
increase is still too low. Now I'll just have to prove
it by looking at that report, or elsewhere.
Sounds like a good project for the long holiday
weekend, or I could just work on my Cozy ... it will
be a tough call!

Ron

--- Ed Anderson <eanderson@carolina.rr.com> wrote:


 Ok, Ron, I went back and looked at the drag aspects
again.  It looks like
the calculation was accurate, however, I think this
will put it into a
better perspective than before.

The frontal drag at 120 mph for the 1 square foot
radiator (using just the
frontal area - no drag coefficient) was

37.63 lbf/ft^2,  the "internal skin" drag of the 4"
thick radiator was 6.7
lbf/ft^2.  The skin drag for the 1" thick rad was
4.28 lbf/ft^2.  So
comparing the 6.7 with the 4.28 was where I came up
with the 58% increase in
skin drag.

 However, adding  the frontal and skin drag factors
for the "total" drag, I
get 37.62 lbf/ft^2 + 4.28 lbf/ft^2 = 40.98 lbf/ft^2
total drag for the 1"
rad. For the 4" rad  37.62 + 6.7 = 44.32 lbf/ft^2,
so based on that it
appears that the total drag was increased by
41.90/44.32 = 5.5% more total
drag for the 4" radiator than for the 1" radiator.
It might be a tad bit
less than that due to the 5% decrease in mass flow
on the frontal area of
the thicker rad.

At least that is the way it appears to me.

Ed


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