Return-Path: Received: from [65.54.168.115] (HELO hotmail.com) by logan.com (CommuniGate Pro SMTP 4.2b1) with ESMTP id 3134127 for flyrotary@lancaironline.net; Mon, 29 Mar 2004 13:36:42 -0500 Received: from mail pickup service by hotmail.com with Microsoft SMTPSVC; Mon, 29 Mar 2004 10:36:41 -0800 Received: from 64.159.105.217 by bay3-dav11.bay3.hotmail.com with DAV; Mon, 29 Mar 2004 18:36:41 +0000 X-Originating-IP: [64.159.105.217] X-Originating-Email: [lors01@msn.com] X-Sender: lors01@msn.com From: "Tracy Crook" To: "Rotary motors in aircraft" Subject: Re: [FlyRotary] Re: Renesis & RD-1Cdrivetesting Date: Mon, 29 Mar 2004 13:36:41 -0500 MIME-Version: 1.0 X-Mailer: MSN Explorer 7.02.0011.2700 Content-Type: multipart/alternative; boundary="----=_NextPart_001_0005_01C41592.DE455230" Message-ID: X-OriginalArrivalTime: 29 Mar 2004 18:36:41.0480 (UTC) FILETIME=[C74A8080:01C415BC] ------=_NextPart_001_0005_01C41592.DE455230 Content-Type: text/plain; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable The 15 degree came from common airfoil stall angles so yes, it applies an= ywhere. =20 Tracy =20 Hi Tracy, I assume that the 15 degree limit is anywhere along the blade = rather than anyone radius. Is that correct? Best Guesses are accepted := -) TJ Tracy Crook wrote: That conclusion was based on measurements of the blade angle, prop rpm & = airspeed and calculating angle to airflow along with the assumption that = stall would occur when angle exceeded 15 deg. Then this SWAG was boiled = in a pot with observations of how adversely the cooling was affected by t= he IVO (stalled air blocking inlets). ------=_NextPart_001_0005_01C41592.DE455230 Content-Type: text/html; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable
The 15 degree came from co= mmon airfoil stall angles so yes, it applies anywhere. 
&= nbsp;
Tracy 
 
 
Hi Tracy,  I assume= that the 15 degree limit is anywhere along the blade rather than anyone = radius.  Is that correct?  Best Guesses are accepted :-)=
TJ
Tracy Crook wrote:
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That conclusion was based on me= asurements of the blade angle, prop rpm & airspeed and calculating an= gle to airflow along with the assumption that stall would occur when angl= e exceeded 15 deg.  Then this SWAG was boiled in a pot with observat= ions of how adversely the cooling was affected by the IVO (stalled a= ir blocking inlets).
 
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