Return-Path: Received: from [65.33.160.104] (account marv@lancaironline.net) by logan.com (CommuniGate Pro WebUser 4.2b5) with HTTP id 165017 for lml@lancaironline.net; Wed, 16 Jun 2004 11:58:21 -0400 From: "Marvin Kaye" Subject: Re: [LML] 320 stall characteristics To: lml X-Mailer: CommuniGate Pro WebUser Interface v.4.2b5 Date: Wed, 16 Jun 2004 11:58:21 -0400 Message-ID: In-Reply-To: <028801c453b8$664ce5e0$0402a8c0@axs> References: <028801c453b8$664ce5e0$0402a8c0@axs> MIME-Version: 1.0 Content-Type: text/plain; charset="ISO-8859-1"; format="flowed" Content-Transfer-Encoding: 8bit Posted for "terrence o'neill" : I did some stall testing with another stabilizer-elevator plane prototype many years ago and found that the stab ilizer stalls a few degrees AOA after the wing stalls... and that slowed the recovery (to a lower wing AOA) a lot. I added slats to the stabilizer and it greatly increased the pitch authority, to return the wing's AOA to an unstalled AOA. Has Lancair looked at stabilizer stall at higher wing-AOA? Might be a good idea to avoid high-AOA stalls if this hasn't ben investigated, imho, and install an AOA isntrument or indicator. T. (just bought a L235/320)