X-Virus-Scanned: clean according to Sophos on Logan.com Return-Path: Sender: To: lml@lancaironline.net Date: Thu, 26 Jan 2006 00:28:36 -0500 Message-ID: X-Original-Return-Path: Received: from smtp104.sbc.mail.mud.yahoo.com ([68.142.198.203] verified) by logan.com (CommuniGate Pro SMTP 5.0.7f) with SMTP id 953411 for lml@lancaironline.net; Wed, 25 Jan 2006 12:39:12 -0500 Received-SPF: none receiver=logan.com; client-ip=68.142.198.203; envelope-from=elippse@sbcglobal.net Received: (qmail 49033 invoked from network); 25 Jan 2006 17:31:16 -0000 Received: from unknown (HELO Computerroom) (elippse@sbcglobal.net@66.122.67.190 with login) by smtp104.sbc.mail.mud.yahoo.com with SMTP; 25 Jan 2006 17:31:15 -0000 X-Original-Message-ID: <002801c621d5$2703f800$be437a42@Computerroom> From: "Paul Lipps" X-Original-To: Subject: Flap reflex X-Original-Date: Wed, 25 Jan 2006 09:31:18 -0800 MIME-Version: 1.0 Content-Type: multipart/alternative; boundary="----=_NextPart_000_0025_01C62192.18567960" X-Priority: 3 X-MSMail-Priority: Normal X-Mailer: Microsoft Outlook Express 6.00.2900.2180 X-MIMEOLE: Produced By Microsoft MimeOLE V6.00.2900.2180 This is a multi-part message in MIME format. ------=_NextPart_000_0025_01C62192.18567960 Content-Type: text/plain; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable On the Lancair 235-360 the flaps can be moved up above the wing as well = as below. This effectively changes the camber of the airfoil to move the = point of minimum drag coefficient, the so-called "drag-bucket", to = coincide with the angle-of-attack for the required lift-coefficient = based on TAS and weight. The NLF1 0215F airfoil used on these models had = a lot of camber and so this reflex gave a way to reduce the camber by = moving the flaps up and so reducing the drag. Otherwise the wing would = have had to be flown with the wing at a negative angle-of-attack at a = higher drag coefficient. This effect of camber-changing by means of the = flap can be seen by looking at the bugs on the leading edge of your = wing. When you land and have the flaps down, the wing must fly at an = apparently lower A-O-A. Generally most airports have a field just before = the approach end of the runway. As you come in over this field, the bugs = in the field, which are ardent environmentalists, sacrifice their = existence by flying up into your path hoping to cause you to crash. = Since your wing is flying nose-down relative to your flight path, these = little critters impact your wing slightly above the leading edge at a = point referred to as the stagnation point, which is perpendicular to = your flight path. Sorry! This is probably more info than you really = wanted! ------=_NextPart_000_0025_01C62192.18567960 Content-Type: text/html; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable
On the Lancair 235-360 the flaps can be moved up = above the=20 wing as well as below. This effectively changes the camber of the = airfoil to=20 move the point of minimum drag coefficient, the so-called "drag-bucket", = to=20 coincide with the angle-of-attack for the required lift-coefficient = based on TAS=20 and weight. The NLF1 0215F airfoil = used on=20 these models had a lot of camber and so this reflex gave a way to reduce = the=20 camber by moving the flaps up and so reducing the drag. Otherwise the = wing would=20 have had to be flown with the wing at a negative angle-of-attack at a = higher=20 drag coefficient. This effect of camber-changing by means of the flap = can be=20 seen by looking at the bugs on the leading edge of your wing. When = you land=20 and have the flaps down, the wing must fly at an apparently lower A-O-A. = Generally most airports have a field just before the approach end of the = runway.=20 As you come in over this field, the bugs in the field, which are ardent=20 environmentalists, sacrifice their existence by flying up into your = path=20 hoping to cause you to crash. Since your wing is flying nose-down = relative to=20 your flight path, these little critters impact your wing slightly above = the=20 leading edge at a point referred to as the stagnation point, which is=20 perpendicular to your flight path. Sorry! This is probably more info = than you=20 really wanted!
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