Return-Path: Received: from webmail.atlantic.net ([209.208.115.15] verified) by logan.com (CommuniGate Pro SMTP 4.2b8) with SMTP id 322818 for flyrotary@lancaironline.net; Thu, 15 Jul 2004 16:36:00 -0400 Received-SPF: error receiver=logan.com; client-ip=209.208.115.15; envelope-from=banana@atlantic.net Received: (qmail 9741 invoked by uid 48); 15 Jul 2004 20:16:20 -0000 Received: from out.moffitt.usf.edu (out.moffitt.usf.edu [131.247.182.200]) by webmail.atlantic.net (IMP) with HTTP for ; Thu, 15 Jul 2004 16:16:20 -0400 Message-ID: <1089922580.40f6e6148c3e9@webmail.atlantic.net> Date: Thu, 15 Jul 2004 16:16:20 -0400 From: banana@atlantic.net To: Rotary motors in aircraft Subject: Re: [FlyRotary] Re: New Scoop References: In-Reply-To: MIME-Version: 1.0 Content-Type: text/plain; charset=ISO-8859-1 Content-Transfer-Encoding: 8bit User-Agent: Internet Messaging Program (IMP) 3.2.2 X-Originating-IP: 131.247.182.200 Al, I don't know exactly how to phrase this question but I'll take a stab at it. When you decided to place the heat exchangers in the wings how did you estimate the effect(if any) due to impact on the designed airfoil(s)? I think this is a great place for them in the canard designs. I am thinking about the spaces in the rear of the strakes for mine. Dean Head Cozy MK4 BKV FL Quoting Al Gietzen : > Subject: [FlyRotary] Re: New Scoop > > > > Al, > Do you have any photos of your oil cooler install showing the > airflow path? > > Joe Berki > Limo EZ > > > > My oil cooler is in the wing root. The intake is on the bottom just behind > the spar, and the exit is out the top further back. It matches a coolant > rad in the other wing. > > The first pic show the oil cooler. The second is the inlet "scoop" - not > really a scoop, just an airfoil lip that extends down into the air flow > about 1/2". The third pic shows the rough ducting (early version of exit > fairing) for the coolant rad; the oil cooler is similar, and the fourth pic > shows the exit fairing. The flow through this cooler (and the wing root rad) > is enhanced by the normal pressure difference between the bottom and top of > the wing. At this position of the wing the difference should be higher at > higher angle of attack. > > > > Al > > ------------------------------------------------------------------------- This message was sent through Atlantic.Net Webmail. Sick of pop-up ads and climbing prices? Visit www.atlantic.net to get pure Internet for $19.95/mo.