From: "Charlie England ceengland7@gmail.com" <flyrotary@lancaironline.net>
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Date: Tue, 7 Jan 2020 11:33:41 -0600
Message-ID: <CAHxyc51PomBoSvtcSV7bXxh9bGJMkV63FeMq-F7A+wued3ROrA@mail.gmail.com>
Subject: Re: [FlyRotary] Inlet radius ratio
To: Rotary motors in aircraft <flyrotary@lancaironline.net>
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I probably have the paper you're looking for. I'll try to find it for you &
send it to you later today.

Charlie

On Tue, Jan 7, 2020 at 11:03 AM Finn Lassen finn.lassen@verizon.net <
flyrotary@lancaironline.net> wrote:

> Tracy reported a marked increase in cooling when changing the
> inner/outer radius of the duct inlet. The outer radius of the lip should
> apparently be greater than the inner radius of the lip. He got the
> optimum ratio from an NACA paper, but don't remember which.
>
> I think the goal is maximum pressure recovery at low speeds (100 mph)
> and high angle of attack and of course minimum drag at low and high
> speeds (output cowl flap to lessen flow at high speeds making the air
> flow easily around the inlet and cowl at higher speeds).
>
> I've been trying to locate that paper but keep finding papers on turbine
> inlets and supersonic inlets.
>
> Does anyone know what that NACA paper may be? Or even just the optimum
> radius ratio?
>
> Finn
>
>
>
> --
> Homepage:  http://www.flyrotary.com/
> Archive and UnSub:
> http://mail.lancaironline.net:81/lists/flyrotary/List.html
>

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<div dir=3D"ltr"><div class=3D"gmail_default" style=3D"font-size:small">I p=
robably have the paper you&#39;re looking for. I&#39;ll try to find it for =
you &amp; send it to you later today.</div><div class=3D"gmail_default" sty=
le=3D"font-size:small"><br></div><div class=3D"gmail_default" style=3D"font=
-size:small">Charlie</div></div><br><div class=3D"gmail_quote"><div dir=3D"=
ltr" class=3D"gmail_attr">On Tue, Jan 7, 2020 at 11:03 AM Finn Lassen <a hr=
ef=3D"mailto:finn.lassen@verizon.net">finn.lassen@verizon.net</a> &lt;<a hr=
ef=3D"mailto:flyrotary@lancaironline.net">flyrotary@lancaironline.net</a>&g=
t; wrote:<br></div><blockquote class=3D"gmail_quote" style=3D"margin:0px 0p=
x 0px 0.8ex;border-left:1px solid rgb(204,204,204);padding-left:1ex">Tracy =
reported a marked increase in cooling when changing the <br>
inner/outer radius of the duct inlet. The outer radius of the lip should <b=
r>
apparently be greater than the inner radius of the lip. He got the <br>
optimum ratio from an NACA paper, but don&#39;t remember which.<br>
<br>
I think the goal is maximum pressure recovery at low speeds (100 mph) <br>
and high angle of attack and of course minimum drag at low and high <br>
speeds (output cowl flap to lessen flow at high speeds making the air <br>
flow easily around the inlet and cowl at higher speeds).<br>
<br>
I&#39;ve been trying to locate that paper but keep finding papers on turbin=
e <br>
inlets and supersonic inlets.<br>
<br>
Does anyone know what that NACA paper may be? Or even just the optimum <br>
radius ratio?<br>
<br>
Finn<br>
<br>
<br>
<br>
--<br>
Homepage:=C2=A0 <a href=3D"http://www.flyrotary.com/" rel=3D"noreferrer" ta=
rget=3D"_blank">http://www.flyrotary.com/</a><br>
Archive and UnSub:=C2=A0 =C2=A0<a href=3D"http://mail.lancaironline.net:81/=
lists/flyrotary/List.html" rel=3D"noreferrer" target=3D"_blank">http://mail=
.lancaironline.net:81/lists/flyrotary/List.html</a><br>
</blockquote></div>

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