Return-Path: Received: from mail.arc.nasa.gov ([143.232.48.201]) by ns1.olsusa.com (Post.Office MTA v3.5.3 release 223 ID# 0-64832U3500L350S0V35) with ESMTP id com for ; Tue, 2 May 2000 18:51:49 -0400 Received: from [128.102.191.43] (reinath.arc.nasa.gov [128.102.191.43]) by mail.arc.nasa.gov (8.8.7/8.8.7) with ESMTP id PAA14727 for ; Tue, 2 May 2000 15:57:36 -0700 (PDT) Message-Id: Date: Tue, 2 May 2000 15:57:34 -0700 To: lancair.list@olsusa.com From: "Mike S. Reinath" Subject: Re: LNC2 control surfaces X-Mailing-List: lancair.list@olsusa.com Mime-Version: 1.0 <<<<<<<<<<<<<<<<--->>>>>>>>>>>>>>>> << Lancair Builders' Mail List >> <<<<<<<<<<<<<<<<--->>>>>>>>>>>>>>>> >> >>> ... I think we're all agreed that the LE should not be below and that flush with is OK. But are there any benefits to having the control surface leading edges HIGHER, say upwards of .125" above the trailing edges. Is better laminar flow all the way back to the trailing edges of the control surfaces achieved by doing this or is this unnecessary.... <<< You will never get laminar flow all the way back to the TE. Laminar flow airfoils are designed with a plateau in the pressure distribution to maintain laminar flow further in the streamwise direction than a non-laminar flow airfoil. The pressure must eventually return to the freestream (or almost to freestream) starting somewhere near the back 1/3 of the airfoil. This is where the pressure distribution plateau ends and also where laminar flow ends. You have to look at the NLF-0215-F airfoil data to see where it actually ends, but you can be sure that the laminar flow will not survive to the start of the flap or aileron. Mike Reinath 360 MkII N3602M >>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>> LML website: http://www.olsusa.com/Users/Mkaye/maillist.html Builders' Bookstore: http://www.buildersbooks.com/lancair Please send your photos and drawings to marvkaye@olsusa.com. >>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>>