X-Virus-Scanned: clean according to Sophos on Logan.com Return-Path: Received: from wx-out-0506.google.com ([66.249.82.228] verified) by logan.com (CommuniGate Pro SMTP 5.2c1) with ESMTP id 2503245 for flyrotary@lancaironline.net; Sat, 24 Nov 2007 13:08:05 -0500 Received-SPF: pass receiver=logan.com; client-ip=66.249.82.228; envelope-from=cozy4pilot@gmail.com Received: by wx-out-0506.google.com with SMTP id i27so170440wxd for ; Sat, 24 Nov 2007 10:07:27 -0800 (PST) DKIM-Signature: v=1; a=rsa-sha256; c=relaxed/relaxed; d=gmail.com; s=gamma; h=domainkey-signature:received:received:reply-to:from:to:in-reply-to:subject:date:message-id:mime-version:content-type:x-priority:x-msmail-priority:x-mailer:x-mimeole:importance; bh=VJSv0HpuLKr3HykIOZnaCAlHN/NArhJZgMoxhuLhPrk=; b=fq4YXvqkRaGu+gTbbI6ToZ/wZwwNkCJZQwvG82KWMZKeK0aommFXujgRFMD0X+O75M9R4C5W1yD63TVjqpY85r/t4/YZJxo8eEsnUuCYH+d9JVcH9ZaT9+Pm7oo23iBpRen+DN5SqWMhGSzbKdULsMnWtnpDJHG2sui63GmbGzM= DomainKey-Signature: a=rsa-sha1; c=nofws; d=gmail.com; s=gamma; h=received:reply-to:from:to:in-reply-to:subject:date:message-id:mime-version:content-type:x-priority:x-msmail-priority:x-mailer:x-mimeole:importance; b=xnAaGzihmz2ClokuELm+B6iqr53JffZq4WlqDwSrDWdVNgooF1FidCh51j3ZmzsuJvQn5g7lVJ6DkBFit1Lq0CMFRkM4p7ryHGnCaOSBVN0FDAoeafi3rF6iEiWpOId0xmOrke7HCfGLHQxXLwF5A14BFrsrsV/pAs6iQgCl/zo= Received: by 10.70.48.4 with SMTP id v4mr1236582wxv.1195927647797; Sat, 24 Nov 2007 10:07:27 -0800 (PST) Return-Path: Received: from HomePC ( [71.2.20.232]) by mx.google.com with ESMTPS id i34sm8141380wxd.2007.11.24.10.07.24 (version=SSLv3 cipher=OTHER); Sat, 24 Nov 2007 10:07:25 -0800 (PST) Reply-To: From: "Steve Brooks" To: "Rotary motors in aircraft" In-Reply-To: Subject: RE: [FlyRotary] Re: Naca Report on Radiator Thickness Date: Sat, 24 Nov 2007 13:05:13 -0500 Message-ID: MIME-Version: 1.0 Content-Type: multipart/alternative; boundary="----=_NextPart_000_0012_01C82E9A.A6CDB700" X-Priority: 3 (Normal) X-MSMail-Priority: Normal X-Mailer: Microsoft Outlook IMO, Build 9.0.6604 (9.0.2911.0) X-MimeOLE: Produced By Microsoft MimeOLE V6.0.6000.16545 Importance: Normal This is a multi-part message in MIME format. ------=_NextPart_000_0012_01C82E9A.A6CDB700 Content-Type: text/plain; charset="iso-8859-1" Content-Transfer-Encoding: 7bit Tracy, Maybe not relevant for an RV, but pretty relevant if you are cooling a pusher. Steve Brooks -----Original Message----- From: Rotary motors in aircraft [mailto:flyrotary@lancaironline.net]On Behalf Of Tracy Crook Sent: Saturday, November 24, 2007 11:53 AM To: Rotary motors in aircraft Subject: [FlyRotary] Re: Naca Report on Radiator Thickness This NACA paper discussion is interesting but has almost nothing to do with our installations using standard automotive rads rather than the flat plate rads in the paper. Radiator frontal area is almost irrelavant in our installations because they are totally enclosed within a streamlined body. Too bad, because if frontal area was a significant factor, it would end the argument about thick vs thin :-) The thin rad would look terrible in this respect. Keep everything in perspective! Note that the NACA paper indicates that the rads we use (tube & fin type) have no application in aircraft. If that were true it would mean all our discussions and work on installations so far have been a total waste of time! Tracy (should be working on RV-8) On Nov 21, 2007 9:20 PM, Ron Springer wrote: 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 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 > > > -- > Homepage: http://www.flyrotary.com/ > Archive and UnSub: > http://mail.lancaironline.net:81/lists/flyrotary/List.html > -- Homepage: http://www.flyrotary.com/ Archive and UnSub: http://mail.lancaironline.net:81/lists/flyrotary/List.html ------=_NextPart_000_0012_01C82E9A.A6CDB700 Content-Type: text/html; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable
Tracy,
 Maybe not relevant for an RV, but pretty relevant if you = are=20 cooling a pusher.
 
Steve=20 Brooks
 
-----Original Message-----
From: Rotary motors in = aircraft=20 [mailto:flyrotary@lancaironline.net]On Behalf Of Tracy=20 Crook
Sent: Saturday, November 24, 2007 11:53 = AM
To:=20 Rotary motors in aircraft
Subject: [FlyRotary] Re: Naca = Report on=20 Radiator Thickness

This NACA paper discussion is interesting but has almost nothing = to do=20 with our installations using standard automotive rads rather than the = flat=20 plate rads in the paper.   Radiator frontal area is almost=20 irrelavant in our installations because they are totally enclosed = within a=20 streamlined body.  Too bad, because if frontal area was a = significant=20 factor, it would end the argument about thick vs thin :-)  The = thin rad=20 would look terrible in this respect.
 
Keep everything in perspective!
 
Note that the NACA paper indicates that the rads we use (tube = & fin=20 type) have no application in aircraft.  If that were true it = would mean=20 all our discussions and work on installations so far have been a total = waste=20 of time! 
 
Tracy (should be working on RV-8)

On Nov 21, 2007 9:20 PM, Ron Springer <ron2369@sbcglobal.net> = wrote:
Well,=20 engineering judgement tells me that your drag
increase is still = too low.=20 Now I'll just have to prove
it by looking at that report, or=20 elsewhere.
Sounds like a good project for the long = holiday
weekend, or=20 I could just work on my Cozy ... it will
be a tough call!

Ron

--- Ed Anderson <eanderson@carolina.rr.com&g= t;=20 wrote:

>
>  Ok, Ron, I went back and = looked at=20 the drag aspects
> again.  It looks like
> the = calculation=20 was accurate, however, I think this
> will put it into = a
>=20 better perspective than before.
>
> The frontal drag at = 120 mph=20 for the 1 square foot
> radiator (using just the
> = frontal area=20 - no drag coefficient) was
>
> 37.63 lbf/ft^2,  the = "internal skin" drag of the 4"
> thick radiator was = 6.7
>=20 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=20 up
> with the 58% increase in
> skin = drag.
>
>=20  However, adding  the frontal and skin drag = factors
> for=20 the "total" drag, I
> get 37.62 lbf/ft^2 + 4.28 lbf/ft^2 =3D = 40.98=20 lbf/ft^2
> total drag for the 1"
> rad. For the 4" rad=20  37.62 + 6.7 =3D 44.32 lbf/ft^2,
> so based on that = it
>=20 appears that the total drag was increased by
> 41.90/44.32 = =3D 5.5%=20 more total
> drag for the 4" radiator than for the 1"=20 radiator.
> It might be a tad bit
> less than that due = to the 5%=20 decrease in mass flow
> on the frontal area of
> the = thicker=20 rad.
>
> At least that is the way it appears to=20 me.
>
> Ed
>
>
> --
> Homepage: =  http://www.flyrotary.com/
> Archive and=20 UnSub:
>
http://mail.lancaironline.net:81/lists/flyrotary/List.htm= l
>


--
Homepage:=20  http://www.flyrotary.com/
Archive and UnSub: =   http://mail.lancaironline.net:81/lists/flyrotary/List.htm= l

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