X-Virus-Scanned: clean according to Sophos on Logan.com From: "James R. Osborn" Received: from mail-pa0-f42.google.com ([209.85.220.42] verified) by logan.com (CommuniGate Pro SMTP 6.1.2) with ESMTPS id 7703255 for flyrotary@lancaironline.net; Wed, 20 May 2015 17:42:54 -0400 Received-SPF: pass receiver=logan.com; client-ip=209.85.220.42; envelope-from=rxcited@gmail.com Received: by pacwv17 with SMTP id wv17so81128423pac.2 for ; Wed, 20 May 2015 14:42:18 -0700 (PDT) DKIM-Signature: v=1; a=rsa-sha256; c=relaxed/relaxed; d=gmail.com; s=20120113; h=from:content-type:message-id:mime-version:subject:date:references :to:in-reply-to; bh=tC82LsyStvkBdc/No15QLKDrkuVuDgv1nBw0OliK1IA=; b=Bmo5wrPhEpCm/dqJxDoN+gb0vhMtu6xycEqo6HKHMCitFbmagjYcq4fNvN8+dV9EZy J5o2ikS3OOMSOHbYL+p9DntDutxtQxnbFpnja43npWm8twJIKsE8g0oNgAjewinPVxOL CdW2r4xRd4SWqzo4EpzLMDntpMeviSftjlwwJiRhgD+zCmu60JOlblcO5pxeE7oPrECM huKZNMxClCll1jxSWsVqVlPd40G+UPDUoKGpjPSI7RYi1F0+XLUJKta1DseC7B2TLvDm hhOU2f9/3hP06qHR4lOvJBIAvlOBZtcFeG7H7mWrlenUFqWkaCkqCa10qHhL3xc3mFUV 52kw== X-Received: by 10.70.11.130 with SMTP id q2mr545965pdb.115.1432158138174; Wed, 20 May 2015 14:42:18 -0700 (PDT) Return-Path: Received: from ?IPv6:2001:400:613:18::5c2? ([2001:400:613:18::5c2]) by mx.google.com with ESMTPSA id b4sm14968135pbu.71.2015.05.20.14.42.16 for (version=TLSv1 cipher=ECDHE-RSA-RC4-SHA bits=128/128); Wed, 20 May 2015 14:42:17 -0700 (PDT) Content-Type: multipart/alternative; boundary="Apple-Mail=_4D1783F5-98AB-4A56-9B2F-949352B2400E" Message-Id: <39CF7984-38C4-4608-9D14-4FA391B1FAA4@gmail.com> Mime-Version: 1.0 (Mac OS X Mail 8.2 \(2098\)) Subject: Re: [FlyRotary] Return to Flight - 2 Date: Wed, 20 May 2015 14:42:15 -0700 References: To: Rotary motors in aircraft In-Reply-To: X-Mailer: Apple Mail (2.2098) --Apple-Mail=_4D1783F5-98AB-4A56-9B2F-949352B2400E Content-Transfer-Encoding: quoted-printable Content-Type: text/plain; charset=windows-1252 Steve, 37 inHg is about 18+ psi absolute, so nominally around 3 psi boost above = sea level pressure? Just curious. Nice you can get that at 8000 feet. = Do you keep it that low for reliability and longevity? I have heard the = Renesis cannot take as much boost as the rotors have less squish space = for boost, so maybe that is why? Or is that as far as your turbo is = able to go? Cool to see the scientific approach on these babies. Some day when I = get my rotary project underway, I plan to do the engine test stand = approach. Seems like the way to make sure everything works properly = before risking life and limb! =97 James > On May 20, 2015, at 9:29 AM, Steven W. Boese = wrote: >=20 > Bill, >=20 > At 6000 RPM, HP was 174 and MAP was 37" Hg. >=20 > The radiator for the test stand is larger than what would be needed in = an aircraft. It is capable of maintaining a 200 degree coolant out of = the engine at the above power setting with 0.8" H20 pressure difference = across the core. It is from a BMW(320i?) with a core 23"wide, 17" long, = 1.25" thick, and a fine fin spacing of about 20 per inch. It was given = to me because the plastic tanks were leaking. I cleaned it up and = welded aluminum tanks onto it. It is mounted at an oblique angle in the = duct. A photo of the heat exchanger inlet ducts is attached. >=20 > The oil cooler is a reasonable size and is capable of maintaining 200 = degree oil out of the cooler at the above power setting with 2.4" H20 = pressure difference across the core.=20 >=20 > It should also be noted that this is at a density altitude of about = 8000 ft which decreases the cooling capacity relative to sea level. >=20 > Steve > From: Rotary motors in aircraft > on behalf of Bill Bradburry = > > Sent: Wednesday, May 20, 2015 8:16 AM > To: Rotary motors in aircraft > Subject: [FlyRotary] Re: Return to Flight - 2 > =20 > Steve, > =20 > That is a great chart! Amazing what you can learn with a little data. > =20 > At the end of the test, it looks like you revved the engine up to = 5000, then 5500, then 6000 for a couple of minutes and the temp seemed = to stabilize at about 205 for both water and oil. Is this where your = test engine runs with only prop air to cool it? What kind of HP do you = think the turbo Renesis is doing at 6000? That seems like a really good = cooling system to cool what is probably over 200 HP with just the prop = blast. Do you think it would do that if cowled? > =20 > Bill >=20 > -- > Homepage: http://www.flyrotary.com/ > Archive and UnSub: = http://mail.lancaironline.net:81/lists/flyrotary/List.html = --Apple-Mail=_4D1783F5-98AB-4A56-9B2F-949352B2400E Content-Transfer-Encoding: quoted-printable Content-Type: text/html; charset=windows-1252
Steve,

37 inHg is about 18+ psi absolute, so nominally around = 3 psi boost above sea level pressure?  Just curious.  Nice you = can get that at 8000 feet.  Do you keep it that low for reliability = and longevity?  I have heard the Renesis cannot take as much boost = as the rotors have less squish space for boost, so maybe that is why? =  Or is that as far as your turbo is able to go?

Cool to see the scientific approach on = these babies.  Some day when I get my rotary project underway, I = plan to do the engine test stand approach.  Seems like the way to = make sure everything works properly before risking life and = limb!

=97 = James

On May 20, 2015, at 9:29 AM, = Steven W. Boese <flyrotary@lancaironline.net> wrote:

Bill,

At 6000 RPM, HP was 174 and MAP was 37" Hg.

The radiator for the test stand is larger than what would = be needed in an aircraft.  It is capable of maintaining a = 200 degree coolant out of the engine at the above power setting = with 0.8" H20 pressure difference across the core.  It is from a = BMW(320i?) with a core 23"wide, 17" long, 1.25" thick, and a fine = fin spacing of about 20 per inch.  It was given to me because the = plastic tanks were leaking.  I cleaned it up and welded aluminum = tanks onto it.  It is mounted at an oblique angle in the = duct.  A photo of the heat exchanger inlet ducts is = attached.

The oil cooler is a reasonable size and = is capable of maintaining 200 degree oil out of the cooler at the above = power setting with 2.4" H20 pressure difference across the = core. 

It should also be noted that this is at = a density altitude of about 8000 ft which decreases the cooling capacity = relative to sea level.

Steve
From: Rotary motors in aircraft = <flyrotary@lancaironline.net> on behalf of Bill = Bradburry <flyrotary@lancaironline.net>
Sent: Wednesday, May 20, 2015 = 8:16 AM
To: Rotary motors in = aircraft
Subject: [FlyRotary] Re: Return to = Flight - 2
 
Steve,

 

That is a great = chart!  Amazing what you can learn with a little = data.

 

At the end of the = test, it looks like you revved the engine up to 5000, then 5500, then = 6000 for a couple of minutes and the temp seemed to stabilize at about = 205 for both water and oil.  Is this where your test engine runs = with only prop air to cool it?  What kind of HP do you think the = turbo Renesis is doing at 6000?  That seems like a really good = cooling system to cool what is probably over 200 HP with just the prop = blast.  Do you think it would do that if = cowled?

 

Bill

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