X-Virus-Scanned: clean according to Sophos on Logan.com Return-Path: Sender: To: lml@lancaironline.net Date: Sun, 07 Jun 2009 08:59:33 -0400 Message-ID: X-Original-Return-Path: Received: from web36904.mail.mud.yahoo.com ([209.191.85.72] verified) by logan.com (CommuniGate Pro SMTP 5.2.14) with SMTP id 3673783 for lml@lancaironline.net; Sat, 06 Jun 2009 09:50:20 -0400 Received-SPF: none receiver=logan.com; client-ip=209.191.85.72; envelope-from=chris_zavatson@yahoo.com Received: (qmail 75444 invoked by uid 60001); 6 Jun 2009 13:49:45 -0000 DomainKey-Signature:a=rsa-sha1; q=dns; c=nofws; s=s1024; d=yahoo.com; h=Message-ID:X-YMail-OSG:Received:X-Mailer:References:Date:From:Subject:To:In-Reply-To:MIME-Version:Content-Type; b=sz0vPBNDmqNaMjEyPftOitWbduMAvjYKIs7S2w3A1cnm6rak7KtQv5G8oLaBayJNd2L3573d+ZKakYWTJtgxk6f6pfTqaD3jXTgi6XVFFC3c3RnzcS8fXvEE7f+Y2TdtWUfUok0gYmPaChW0qHQswmJslX/qMpo5cwd+Mka3M1E=; X-Original-Message-ID: <531558.74082.qm@web36904.mail.mud.yahoo.com> X-YMail-OSG: T3NPTvAVM1kvb3Id0FSHXqdYc1MWG4LqmYmg1.HshlbILBSEmhYfdCnqhc2tAx934ltj5WQzO.OM1hPCGl5pT8Xz546S8.2ObQcDLh_t0W.Yeng2s0FLd3CrBRljACcSOhfkRZGLDd_cP6_ZyzVppn93IYILLvktDVxhMlNWqo4CIFruiNvutyzISNSsZfX6WMMAJPqgCQBxJCqCYyXN5R.nfFIvIEwAfrBRKE4kctFpEvgxMsKZc2NEzRBlEsWsvjpJrrRqqdGOCkQ_PpdQZz9UEDEqLPy1hDhPidHl07GRjDExQ21PGNeTf0ZjEtHd2fLscaTywwrHP8lcLausVr.Wc9gmllvELrmHjuB7Qgt9_NDKQL9t Received: from [149.32.224.34] by web36904.mail.mud.yahoo.com via HTTP; Sat, 06 Jun 2009 06:49:45 PDT X-Mailer: YahooMailRC/1277.43 YahooMailWebService/0.7.289.15 References: X-Original-Date: Sat, 6 Jun 2009 06:49:45 -0700 (PDT) From: Chris Zavatson Subject: Re: [LML] Re: L360 winglets X-Original-To: Lancair Mailing List In-Reply-To: MIME-Version: 1.0 Content-Type: multipart/alternative; boundary="0-12630944-1244296185=:74082" --0-12630944-1244296185=:74082 Content-Type: text/plain; charset=iso-8859-1 Content-Transfer-Encoding: quoted-printable =0A=0A=0AA=A0NASA report on winglets tested on a Beechcraft back in 1980.= =A0 It has some nice plots of the before and after drag polars so one can s= ee very clearly when winglets help and when they hurt.=0A=0Ahttp://www.n91c= z.com/Interesting_Technical_Reports/NASA_TM81892.pdf=0A=0AFrom the summary1= .=A0=0Athe increase in maximum lift-to-drag ratio was Adding the winglets i= ncreased the Oswald efficiency factor by 13 percent;11 percent.2. Winglets = left the maximum speed at 3962 m (13 000 f t ) density alti -tude =0Areduce= d. Cruise speed increased virtually unchanged. At lower altitudes, however,= the maximum speed was8 knots (5.6 percent) at 3962 m and=A0 51 percentmaxi= mum continuous power.3. =0Aof wingletsAn improvement in climb performance w= as obtained due to the installationor 6 percent, a t 1524 m (5000 ft)and by= a greater amount at higher altitude.Rate of climb increased approximately = 0.25 m/sec (50 ft/min:,4. Winglets increased the fuel efficiency of the air= plane for CL > 0.266.5. =0Awinglets.Handling qualities were favorably affec= ted by the installation of=0A=0AChris Zavatson=0AN91CZ=0A360std=0Awww.N91CZ= .com=0A=0A=0A --0-12630944-1244296185=:74082 Content-Type: text/html; charset=iso-8859-1 Content-Transfer-Encoding: quoted-printable
 
=0A

A NASA report on winglets tested on = a Beechcraft back in 1980.  It has some nice plots of the before and a= fter drag polars so one can see very clearly when winglets help and when th= ey hurt.
=0A
 
=0A=0A
 
=0A=0A

From the summary

=0A

1. Adding the winglets increased the Oswald= efficiency factor by 1= 3 percent;

=0A

the increase in maximum lift-to-drag rat= io was 11 perce= nt.

=0A

2. Winglets left the max= imum s= peed at 3962 m (13 000 f t ) density alti -=

=0A

tude <= FONT face=3D"Times New Roman">virtually unchanged. At lower altitudes, however, the maximum speed was

=0Areduced. Cruise speed increased 8 knots (5.6 percent) at 3962 m and  5= 1 percent

=0A

maximum con= tinuous power.

=0A3. An im= provement in climb performance was obtained due to the installation=0A

of wingletsor 6 percent, a t 1524 m (5000 = ft)= and by a greater amount at higher altitude= .

=0A

Rate = of climb increased approximately 0.25 m/sec (50 ft/min:,

=0A

4. Winglets in= creased the fuel efficiency of the airplane for CL > 0.266.

=0A<= P align=3Dleft>5. Handling qualities were favorably affected by the = installation of

=0A

winglets.

=0A
 
=0A=
C= hris Zavatson
=0A
N91CZ
=0A
360std
=0A=0A

=0A
 
=0A=0A=0A=0A --0-12630944-1244296185=:74082--