X-Virus-Scanned: clean according to Sophos on Logan.com Return-Path: Sender: To: lml@lancaironline.net Date: Sun, 18 Jul 2010 08:35:49 -0400 Message-ID: X-Original-Return-Path: Received: from imr-mb02.mx.aol.com ([64.12.207.163] verified) by logan.com (CommuniGate Pro SMTP 5.3.8) with ESMTP id 4397011 for lml@lancaironline.net; Sun, 18 Jul 2010 00:52:52 -0400 Received-SPF: pass receiver=logan.com; client-ip=64.12.207.163; envelope-from=Sky2high@aol.com Received: from imo-ma04.mx.aol.com (imo-ma04.mx.aol.com [64.12.78.139]) by imr-mb02.mx.aol.com (8.14.1/8.14.1) with ESMTP id o6I4q5MR018005 for ; Sun, 18 Jul 2010 00:52:05 -0400 Received: from Sky2high@aol.com by imo-ma04.mx.aol.com (mail_out_v42.9.) id q.e34.dd683d1 (34907) for ; Sun, 18 Jul 2010 00:52:03 -0400 (EDT) Received: from magic-d17.mail.aol.com (magic-d17.mail.aol.com [172.19.155.133]) by cia-da02.mx.aol.com (v129.4) with ESMTP id MAILCIADA024-885b4c428873359; Sun, 18 Jul 2010 00:52:03 -0400 From: Sky2high@aol.com X-Original-Message-ID: <8e609.2871380c.3973e273@aol.com> X-Original-Date: Sun, 18 Jul 2010 00:52:03 EDT Subject: Re: [LML] Re: Any LNC2 tail, CG range X-Original-To: lml@lancaironline.net MIME-Version: 1.0 Content-Type: multipart/mixed; boundary="part1_8e609.2871380c.3973e273_boundary" X-Mailer: AOL 9.5 sub 155 X-AOL-ORIG-IP: 67.175.87.113 X-AOL-IP: 172.19.155.133 X-Spam-Flag:NO X-AOL-SENDER: Sky2high@aol.com --part1_8e609.2871380c.3973e273_boundary Content-Type: multipart/related; boundary="part1_8e609.2871380c.3973e273_rel_boundary" --part1_8e609.2871380c.3973e273_rel_boundary Content-Type: multipart/alternative; boundary="8e609.2871380c_alt_bound" --8e609.2871380c_alt_bound Content-Type: text/plain; charset="UTF-8" Content-Transfer-Encoding: quoted-printable Content-Language: en Chris, =20 You got me a little confused but I quickly recovered. All references I= =20 have seen used MAC (Mean Aerodynamic Chord) as the reference for CG. Ind= eed,=20 the diagram you included does exactly that. H bar C is displayed as the= =20 distance from the forward edge of the MAC, further supporting the use of= =20 specifying the CG range as a percent of MAC (MAC%). =20 Sticking strictly to the CG questions I posed and some comments from =20 LMLers concerning the CG, I present the following list: =20 1. The Lancair 235/320/360 POH gives 2 definitions for the CG range:=20 II. Limitations page 10 -- 15% to 29% MAC VI. Weight & Balance page 3 -- 15% to 20% MAC=20 =20 2. The MAC for flaps -7 and flaps 0 are the same because the TE of the= =20 chord doesn't change much (less than .1 inch).=20 =20 3. Measurements on my 320: a. The leading edge of the root chord is at FS15.75 b. The root chord is 48.5" c. The distance from the root chord to the out board leading edge wingtip= =20 is 114.25" d. The taper distance is 3.5" (from tip to line perpendicular to root=20 chord at the leading edge of the root chord). e. The tip chord is 28" where this chord is parallel to the root chord. f. The TE root chord to the tip chord in e is 115.4" but to the actual= TE=20 tip is another 6.25". The wing only up to the tip chord that is parallel= =20 to the root chord was used in prelim calcs. g. Using the calculator at:=20 _http://www.nasascale.org/howtos/cg-calculator.htm_ (http://www.nasascale.= org/howtos/cg-calculator.htm) for 15% results=20 in a MAC of 39.17", 52" from the root and the CG at 7.47" aft at the root= =20 chord. 7.47+ FS15.75 =3D FS23.22 h. For 20% the CG is at 9.43". 9.43 + FS15.75 =3D FS25.18 i. For 29% the CG is at 12.95". 12.95 + FS15.75 =3D FS28.7 =20 4. Since this calculator only considers tapered wings with parallel chords= ,=20 perhaps you have a more sophisticated calculator. If you need other =20 measurements, let me know. The measurements I took were from points plumb= =20 bobbed to the floor with chalk lines used and a proper rectangle construc= ted. =20 5. Assuming that the swept out wing tip changes the forward CG limit a bit= =20 back to the 24.5 (1.28 inches), that will still not explain the narrow CG= =20 from the calculator or logic. The calculations show a range of only 2" an= d=20 that makes sense to me because the published span is only 5% and 2"/.05= =20 equals 40" for the MAC - close enough to 39.17 inches. Using this sort= of=20 logic and the POH where a 15% MAC results in a CG at 24.5 then 24.5-FS15.= 75 =3D=20 8.75/.15 =3D 58" for a MAC longer than the longest wing chord and the spa= n of=20 5.8" - Huh? 5.8/.05=3D116 which would be a really BIG MAC (no pun intend= ed). =20 HELP! =20 Scott Krueger IO320 =20 In other words, I am still suspicious of Lancair's published CG reference= .=20 =20 =20 In a message dated 7/16/2010 4:57:43 A.M. Central Daylight Time, =20 chris_zavatson@yahoo.com writes: Bill, We definitely have too many MACs out there: mean aerodynamic centers vs.= =20 chords. Both start out as integrals which can degenerate to averages for= =20 simple geometry, like Hershey bar wings. The combination of washout and= =20 sweep make the calculation of the mean aerodynamic center a bit more=20 challenging. CG is a mass property and only moves if you burn fuel, move something in= =20 the plane or get up to use the rest room (not in a Lancair of course). = All=20 forces, including moments, about the CG must vanish for steady=20 unaccelerated flight. The neutral point is a parameter important to stab= ility and best=20 be safely behind the CG otherwise you'll have one of those Wright Flyer= =20 experiences. =20 Chris Zavatson N91CZ 360std _www.N91CZ.com_ (http://www.n91cz.com/)=20 =20 =20 ____________________________________ From: Bill Bradburry To: lml@lancaironline.net Sent: Thu, July 15, 2010 4:08:18 PM Subject: [LML] Re: Small tail, MK II tail, CG range Unless we are talking about MAC and cheese, or the Mickey D kind of MAC,= =20 the aircraft MAC is the Mean Aerodynamic Chord. This MAC is the width of= =20 the wing when measured through the center of the wing in the forward-aft= =20 direction. On a plane like a Piper, this is just the width of the wing.= With=20 a more complicated wing design like the Lancair it is the average of this= =20 measurement. That is where the word =E2=80=9CMean=E2=80=9D comes from. = This measurement=20 has nothing to do with the =E2=80=9Cneutral point=E2=80=9D. It really jus= t describes how=20 effectively wide the wing is. The CG (Center of Gravity) is the point=20 around which the airplane balances (or would balance) if it is sitting on= its=20 wheels. (Maybe that is a =E2=80=9Cneutral point=E2=80=9D?) This CG is= calculated when the=20 plane is motionless on the ground and on scales. It is not the CG that= =20 the plane is operating with when it is in flight because the horizontal= =20 stabilizer is usually designed to place a down force on the plane, which= will=20 have the effect of moving the CG backward in cruise. That is why the CG= is=20 specified to be in the front 25% of the wing width (MAC) in the specs.=20 When we determine thru the Weight and Balance calculations, the CG, we=20 have no idea what the CG of the plane will be in flight because as the an= gle=20 of attack moves the Center of Lift forward and aft, and the horizontal=20 stabilizer adds and removes loads, we have no way of calculating or knowi= ng how=20 these forces are moving. Hopefully the aircraft designer did all this wh= en=20 he specified the CG range that we should keep the plane in when it is on= =20 the ground and on its wheels. I suggest we stay inside these =20 recommendations.=20 Bill B=20 --8e609.2871380c_alt_bound Content-Type: text/html; charset="UTF-8" Content-Transfer-Encoding: quoted-printable Content-Language: en <= FONT id=3Drole_document color=3D#000000 size=3D2 face=3DArial>
Chris,
 
You got me a little confused but I quickly recovered.  All refer= ences=20 I have seen used MAC (Mean Aerodynamic Chord) as the reference for CG.&nbs= p;=20 Indeed, the diagram you included does exactly that.  H bar C is displ= ayed=20 as the distance from the forward edge of the MAC, further supporting the= use of=20 specifying the CG range as a percent of MAC (MAC%).
 
Sticking strictly to the CG questions I posed and some comments= from=20 LMLers concerning the CG, I present the following list:
 
1.  The Lancair 235/320/360 POH gives 2 definitions for the= CG=20 range: 
II. Limitations page 10 -- 15% to 29% MAC
VI. Weight & Balance page 3 -- 15% to 20% MAC 
 
2.  The MAC for flaps -7 and flaps 0 are the same because the TE= of=20 the chord doesn't change much (less than .1 inch).
 
3. Measurements on my 320:
a. The leading edge of the root chord is at FS15.75
b. The root chord is 48.5"
c. The distance from the root chord to the out board leading edg= e=20 wingtip is 114.25"
d. The taper distance is 3.5" (from tip to line perpendicul= ar to=20 root chord at the leading edge of the root chord).
e. The tip chord  is 28" where this chord is parallel to the roo= t=20 chord.
f.  The TE root chord to the tip chord in e is 115.4" but to the= =20 actual TE tip is another 6.25".  The wing only up to the tip chord th= at is=20 parallel to the root chord was used in prelim calcs.
g. Using the calculator at: http://www.nasascale.org/howtos/cg-calculator.= htm =20  for 15% results in a MAC of 39.17", 52" from the root and the= CG at=20 7.47" aft at the root chord.  7.47+ FS15.75 =3D FS23.22
h. For 20% the CG is at 9.43".  9.43 + FS15.75 =3D FS25.18<= /DIV>
i.  For 29% the CG is at 12.95". 12.95 + FS15.75 =3D FS28.7
 
4. Since this calculator only considers tapered wings with parallel= chords,=20 perhaps you have a more sophisticated calculator.  If you need other= =20 measurements, let me know.  The measurements I took were from points= plumb=20 bobbed to the floor with chalk lines used and a proper rectangle=20 constructed.
 
5. Assuming that the swept out wing tip changes the forward CG limit= a bit=20 back to the 24.5 (1.28 inches), that will still not explain the narrow CG= from=20 the calculator or logic. The calculations show a range of only 2" and= that=20 makes sense to me because the published span is only 5% and 2"/.= 05=20 equals 40" for the MAC - close enough to 39.17 inches.  Using th= is=20 sort of logic and the POH where a 15% MAC results in a CG at 24.5 the= n=20 24.5-FS15.75 =3D 8.75/.15 =3D 58" for a MAC longer than the longest wing= chord and=20 the span of 5.8" - Huh?  5.8/.05=3D116 which would be a really B= IG MAC=20 (no pun intended).
 
HELP!
 
Scott Krueger
IO320
 
In other words, I am still suspicious of Lancair's published CG=20 reference. 
 
In a message dated 7/16/2010 4:57:43 A.M. Central Daylight Time,=20 chris_zavatson@yahoo.com writes:


Bill,
We definitely have too many MACs out there: = ; mean=20 aerodynamic centers vs. chords.  Both start out as integrals which= can=20 degenerate to averages for simple geometry, like Hershey bar wings. = ; The=20 combination of washout and sweep make the calculation of the mean aerody= namic=20 center a bit more challenging.
CG is a mass property and only moves if you= burn=20 fuel, move something in the plane or get up to use the rest room (not in= a=20 Lancair of course).  All forces, including moments, about the CG mu= st=20 vanish for steady unaccelerated flight.  The neutral point is a par= ameter=20 important to stability and best be safely behind the CG otherwise= you'll=20 have one of those Wright Flyer experiences.
 
Chris Zavatson
N91CZ
360std


 

From: Bill=20 Bradburry <bbradburry@bellsouth.net>
To: lml@lancaironline.net
Sent: Thu, July 15, 2010 4:08:18=20 PM
Subject: [LML] Re:= Small=20 tail, MK II tail, CG range

Unless we are talking=20 about MAC and cheese, or the Mickey D kind of MAC, the aircraft MAC is= the=20 Mean Aerodynamic Chord.  This MAC is the width of the wing when mea= sured=20 through the center of the wing in the forward-aft direction.  On a= plane=20 like a Piper, this is just the width of the wing.  With a more=20 complicated wing design like the Lancair it is the average of this=20 measurement.  That is where the word =E2=80=9CMean=E2=80=9D comes= from.  This=20 measurement has nothing to do with the =E2=80=9Cneutral point=E2=80=9D.&= nbsp; It really just=20 describes how effectively wide the wing is.  The CG (Center of Grav= ity)=20 is the point around which the airplane balances (or would balance) if it= is=20 sitting on its wheels.  (Maybe that is a =E2=80=9Cneutral point=E2= =80=9D?)  This CG=20 is calculated when the plane is motionless on the ground and on scales.&= nbsp;=20 It is not the CG that the plane is operating with when it is in flight= because=20 the horizontal stabilizer is usually designed to place a down force on= the=20 plane, which will have the effect of moving the CG backward in cruise.&n= bsp;=20 That is why the CG is specified to be in the front 25% of the wing width= (MAC)=20 in the specs.

 

When we deter= mine=20 thru the Weight and Balance calculations, the CG, we have no idea what= the CG=20 of the plane will be in flight because as the angle of attack moves the= Center=20 of Lift forward and aft, and the horizontal stabilizer adds and removes= loads,=20 we have no way of calculating or knowing how these forces are moving.&nb= sp;=20 Hopefully the aircraft designer did all this when he specified the CG ra= nge=20 that we should keep the plane in when it is on the ground and on its=20 wheels.  I suggest we stay inside these=20 recommendations.

 

Bill=20 B

 

 

 




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