Today's Message Index:
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1. 09:44 AM - Re: Behavioural Characterstics (Andrew Kuzyk)
2. 05:32 PM - % HP (Linn Walters)
3. 06:05 PM - Re: Behavioural Characterstics (FLYaDIVE)
4. 06:14 PM - Re: % HP (923te)
5. 08:36 PM - Re: % HP (Linn Walters)
6. 11:43 PM - Re: % HP (James Courtney)
7. 11:56 PM - Re: % HP (Linn Walters)
Message 1
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| Subject: | Re: Behavioural Characterstics |
I don't know if it has anything to do with increased horsepower. I was
thinking that may be I wasn't applying sufficient pressure on the
rudder, but then I applied some pressure and the same thing occurred.
Maybe the trimtab?
Andrew Kuzyk BID, ACIDO, RGD // Partner
Entro Communications
122 Parliament St.
Toronto, Canada M5A 2Y8
T: 416-368-6988 x 222
M: 416-706-4490
F: 416-368-5616
www.entro.com
On Sep 27, 2011, at 1:43 AM, Gary Vogt wrote:
> That's a hard one to comment on. If I had flown it I'd have a better
idea. Any other unusual characteristics?
>
> From: Andrew Kuzyk <andrew@entro.com>
> To: teamgrumman-list@matronics.com
> Sent: Monday, September 26, 2011 12:14 PM
> Subject: TeamGrumman-List: Behavioural Characterstics
>
> I flew my Traveler, yesterday in calm clear skies and noticed the
plane had a gentle fishtailing motion when in level cruise, if I
accelerated it would go away. Anyone have any insights?
> Andrew
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Message 2
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Any ideas on a formula for % horsepower that works for different size
engines? So far Google has let me down.
Linn
Message 3
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| Subject: | Re: Behavioural Characterstics |
Was the BALL centered?
On Tue, Sep 27, 2011 at 12:39 PM, Andrew Kuzyk <andrew@entro.com> wrote:
> I don't know if it has anything to do with increased horsepower. I was
> thinking that may be I wasn't applying sufficient pressure on the rudder,
> but then I applied some pressure and the same thing occurred. Maybe the
> trimtab?
>
> <http://www.entro.com/>
>
> **Andrew Kuzyk BID, ACIDO, RGD // Partner**
>
> * Entro Communications*
> 122 Parliament St.
> Toronto, Canada M5A 2Y8
>
> T: *416-368-6988 x 222*
> M: 416-706-4490
> F: 416-368-5616
>
> www.entro.com
>
> <http://www.entro.com/>****
>
> ** **
>
> On Sep 27, 2011, at 1:43 AM, Gary Vogt wrote:
>
> That's a hard one to comment on. If I had flown it I'd have a better ide
a.
> Any other unusual characteristics?
>
> ------------------------------
> *From:* Andrew Kuzyk <andrew@entro.com>
> *To:* teamgrumman-list@matronics.com
> *Sent:* Monday, September 26, 2011 12:14 PM
> *Subject:* TeamGrumman-List: Behavioural Characterstics
>
> I flew my Traveler, yesterday in calm clear skies and noticed the plane h
ad
> a gentle fishtailing motion when in level cruise, if I accelerated it wou
ld
> go away. Anyone have any insights?
> Andrew
>
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Message 4
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Here ya go
hp = torque * RPM / 5252
otherwise check your POH cause it's different in each plane or
see attachments for O-360
----- Original Message -----
From: Linn Walters
To: grumman2
Sent: Tuesday, September 27, 2011 7:29 PM
Subject: TeamGrumman-List: % HP
<pitts_pilot@bellsouth.net>
Any ideas on a formula for % horsepower that works for different size
engines? So far Google has let me down.
Linn
Message 5
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Thanks for the replies.
I should have been a little more specific. I'm looking for a formula
that computes % HP from parameters that are measurable .... fuel flow,
OAT, RPM, MP etc. so I can display the value on my EFIS. Since the EFIS
measures many parameters a formula could compute % HP realtime. Hard to
fly and look at the graphs ...... :-P There is a formula from Van's
(below from another email) but it doesn't seem to be accurate for
different size engines (not sure which engine really fits), and I don't
have the math skills to tweak it. I was hoping someone might have the
magic bullet.
Linn
Van's formula:
h=(H-((R-r)*(5.58-0.125*(M-m))/100 + 7.35*(M-m)) +
2.0*pa/1000)*sqrt((519-3.58*pa/1000)/(460+ta))
h% = h/H*100
where
Constants:
H= maximum sea level horsepower at maximum manifold pressure (from
manufacturer's data)
R= maximum sea level RPM at maximum manifold pressure (from
manufacturer's data)
M= maximum sea level manifold pressure at rated RPM (from manufacturer's
data)
For a Lycoming/Superior 320 (my case):
H= 160
R= 2700
M= 28.6
Variables (inputs)
r= actual RPM
m= actual manifold pressure
pa= actual pressure altitude (altimeter set to 29.92 inHg)
ta = actual air inlet temperature at pressure altitude (OAT has
practically the same value)
Outputs
h = calculated horsepower
h%= calculated percent horsepower
On 9/27/2011 9:16 PM, 923te wrote:
> Here ya go
> hp = torque * RPM / 5252
> otherwise check your POH cause it's different in each plane or
> see attachments for O-360
>
> ----- Original Message -----
> *From:* Linn Walters <mailto:pitts_pilot@bellsouth.net>
> *To:* grumman2 <mailto:teamgrumman-list@matronics.com>
> *Sent:* Tuesday, September 27, 2011 7:29 PM
> *Subject:* TeamGrumman-List: % HP
>
> <pitts_pilot@bellsouth.net <mailto:pitts_pilot@bellsouth.net>>
>
> Any ideas on a formula for % horsepower that works for different size
> engines? So far Google has let me p; Features Chat,
> http://www.mnbsp; via the Web
> href="http://forums.matronics.com">http://forums.matronics.com
> <http://www.matronics.com/Navigator?TeamGrumman-List>
> _p; generous bsp;
> href="http://www.matronics.com/contribution">http://www.matronics.com/c================
>
>
Message 6
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Lean of peak %HP is determined by fuel flow. ROP all the other atmospheric
parameters apply. A good rule of thumb for the big Continentals
(IO-520/550) operated LOP is 14.9 HP per gallon per hour of fuel flow.
Probably not helpful to a carbureted Lycoming. Drop a line to the GAMI guys
and see if they have a suggestion. There's got to be some reasonable
equation for approximating out there. Your equation doesn't seem terrible
as when I plug it into Mathematica it returns some not unreasonable looking
values. Maybe a bit high.
Jamey
From: owner-teamgrumman-list-server@matronics.com
[mailto:owner-teamgrumman-list-server@matronics.com] On Behalf Of Linn
Walters
Sent: Tuesday, September 27, 2011 8:33 PM
Subject: Re: TeamGrumman-List: % HP
Thanks for the replies.
I should have been a little more specific. I'm looking for a formula that
computes % HP from parameters that are measurable .... fuel flow, OAT, RPM,
MP etc. so I can display the value on my EFIS. Since the EFIS measures many
parameters a formula could compute % HP realtime. Hard to fly and look at
the graphs ...... :-P There is a formula from Van's (below from another
email) but it doesn't seem to be accurate for different size engines (not
sure which engine really fits), and I don't have the math skills to tweak
it. I was hoping someone might have the magic bullet.
Linn
Van's formula:
h=(H-((R-r)*(5.58-0.125*(M-m))/100 + 7.35*(M-m)) +
2.0*pa/1000)*sqrt((519-3.58*pa/1000)/(460+ta))
h% = h/H*100
where
Constants:
H= maximum sea level horsepower at maximum manifold pressure (from
manufacturer's data)
R= maximum sea level RPM at maximum manifold pressure (from manufacturer's
data)
M= maximum sea level manifold pressure at rated RPM (from manufacturer's
data)
For a Lycoming/Superior 320 (my case):
H= 160
R= 2700
M= 28.6
Variables (inputs)
r= actual RPM
m= actual manifold pressure
pa= actual pressure altitude (altimeter set to 29.92 inHg)
ta = actual air inlet temperature at pressure altitude (OAT has practically
the same value)
Outputs
h = calculated horsepower
h%= calculated percent horsepower
On 9/27/2011 9:16 PM, 923te wrote:
Here ya go
hp = torque * RPM / 5252
otherwise check your POH cause it's different in each plane or
see attachments for O-360
----- Original Message -----
From: Linn Walters <mailto:pitts_pilot@bellsouth.net>
Sent: Tuesday, September 27, 2011 7:29 PM
Subject: TeamGrumman-List: % HP
<pitts_pilot@bellsouth.net>
Any ideas on a formula for % horsepower that works for different size
engines? So far Google has let me p; Features Chat,
http://www.mnbsp; <http://www.matronics.com/Navigator?TeamGrumman-List>
via the Web href="http://forums.matronics.com">http://forums.matronics.com
_p; generous bsp; href
<http://www.matronics.com/contribution>
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Message 7
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Thanks Jamey. Math is one of my weak areas. I wish I knew what the
constants are and where they came from. Your suggestion about GAMI is a
good one.
Linn
On 9/28/2011 2:40 AM, James Courtney wrote:
>
> Lean of peak %HP is determined by fuel flow. ROP all the other
> atmospheric parameters apply. A good rule of thumb for the big
> Continentals (IO-520/550) operated LOP is 14.9 HP per gallon per hour
> of fuel flow. Probably not helpful to a carbureted Lycoming. Drop a
> line to the GAMI guys and see if they have a suggestion. There's got
> to be some reasonable equation for approximating out there. Your
> equation doesn't seem terrible as when I plug it into Mathematica it
> returns some not unreasonable looking values. Maybe a bit high.
>
> Jamey
>
> *From:*owner-teamgrumman-list-server@matronics.com
> [mailto:owner-teamgrumman-list-server@matronics.com] *On Behalf Of
> *Linn Walters
> *Sent:* Tuesday, September 27, 2011 8:33 PM
> *To:* teamgrumman-list@matronics.com
> *Subject:* Re: TeamGrumman-List: % HP
>
> Thanks for the replies.
>
> I should have been a little more specific. I'm looking for a formula
> that computes % HP from parameters that are measurable .... fuel
> flow, OAT, RPM, MP etc. so I can display the value on my EFIS. Since
> the EFIS measures many parameters a formula could compute % HP
> realtime. Hard to fly and look at the graphs ...... :-P There is a
> formula from Van's (below from another email) but it doesn't seem to
> be accurate for different size engines (not sure which engine really
> fits), and I don't have the math skills to tweak it. I was hoping
> someone might have the magic bullet.
> Linn
>
> Van's formula:
> h=(H-((R-r)*(5.58-0.125*(M-m))/100 + 7.35*(M-m)) +
> 2.0*pa/1000)*sqrt((519-3.58*pa/1000)/(460+ta))
>
> h% = h/H*100
>
> where
>
> Constants:
>
> H= maximum sea level horsepower at maximum manifold pressure (from
> manufacturer's data)
> R= maximum sea level RPM at maximum manifold pressure (from
> manufacturer's data)
> M= maximum sea level manifold pressure at rated RPM (from
> manufacturer's data)
>
> For a Lycoming/Superior 320 (my case):
>
> H= 160
> R= 2700
> M= 28.6
>
> Variables (inputs)
>
> r= actual RPM
> m= actual manifold pressure
> pa= actual pressure altitude (altimeter set to 29.92 inHg)
> ta = actual air inlet temperature at pressure altitude (OAT has
> practically the same value)
>
> Outputs
>
> h = calculated horsepower
> h%= calculated percent horsepower
>
>
> On 9/27/2011 9:16 PM, 923te wrote:
>
> Here ya go
>
> hp = torque * RPM / 5252
>
> otherwise check your POH cause it's different in each plane or
>
> see attachments for O-360
>
> ----- Original Message -----
>
> *From:*Linn Walters <mailto:pitts_pilot@bellsouth.net>
>
> *To:*grumman2 <mailto:teamgrumman-list@matronics.com>
>
> *Sent:*Tuesday, September 27, 2011 7:29 PM
>
> *Subject:*TeamGrumman-List: % HP
>
> <pitts_pilot@bellsouth.net <mailto:pitts_pilot@bellsouth.net>>
>
> Any ideas on a formula for % horsepower that works for different size
> engines? So far Google has let me p; Features Chat,
> http://www.mnbsp; via the Web
> href="http://forums.matronics.com">http://forums.matronics.com
> <http://www.matronics.com/Navigator?TeamGrumman-List>
> _p; generous bsp;
> href="http://www.matronics.com/contribution"
> <http://www.matronics.com/contribution>>http://www.matronics.com/c================
>
> * *http://www.matronics.com/Navigator?TeamGrumman-List
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