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[220.235.117.31]) by smtp.gmail.com with ESMTPSA id k35sm25414267pgi.21.2021.06.30.23.02.15 for (version=TLS1_2 cipher=ECDHE-ECDSA-AES128-GCM-SHA256 bits=128/128); Wed, 30 Jun 2021 23:02:16 -0700 (PDT) Content-Type: multipart/alternative; boundary="Apple-Mail=_380CC885-987C-4A5B-ACC6-453E2F0EFCEB" Mime-Version: 1.0 (Mac OS X Mail 14.0 \(3654.100.0.2.22\)) Subject: Re: [FlyRotary] Cooling Inlets Date: Thu, 1 Jul 2021 14:02:12 +0800 References: To: Rotary motors in aircraft In-Reply-To: Message-Id: <5A096FB2-BC0C-4AEF-8766-86B10AECED68@gmail.com> X-Mailer: Apple Mail (2.3654.100.0.2.22) --Apple-Mail=_380CC885-987C-4A5B-ACC6-453E2F0EFCEB Content-Transfer-Encoding: quoted-printable Content-Type: text/plain; charset=utf-8 Hi Le Roux Those diagrams relate to Streamline Diffusers, rather than the entrance = lip shape that Finn is chasing. Steve > On 1 Jul 2021, at 1:52 pm, Le Roux Breytenbach = breytenbachleroux@gmail.com wrote: >=20 > Finn: Has come onto these pictures. >=20 > Maybe can help in figuring out the coordinates or help solving the X = and Y=20 >=20 >=20 > =C2=A0IMG_9641.HEIC = > =C2=A0IMG_9640.HEIC = > Le Roux >=20 > On Thu, Jul 1, 2021 at 5:18 AM Finn Lassen finn.lassen@verizon.net = > wrote: > Thanks. I guess I kept missing it because I don't understand what I'm = looking at. > Can anyone help me understand the following and show me the optimum = inside/outside radius ratio (which I assume is one of the A-10 to A-40 = contours): > > > Finn >=20 > On 6/30/2021 9:45 PM, Charlie England ceengland7@gmail.com = wrote: >> Seems likely; I don't recall seeing a CR3485 referenced anywhere, = either. >>=20 >> On 6/30/2021 4:42 PM, Finn Lassen finn.lassen@verizon.net = wrote: >>> I tried in vain to find NASA_CR3485 (well, I found a NASA = contractors report on animal studies). >>>=20 >>> I wonder of he meant 3405? >>> >>>=20 >>> Anyone found a better match? >>>=20 >>> Finn >>>=20 >>> On 4/28/2011 9:07 AM, Tracy wrote: >>>> Finally got around to finishing my cooling inlets. (pictures = attached)=C3=AF=C2=BF=C2=BD Up until now they were simply round pipes = sticking out of the cowl.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD The pipes = are still there but they have properly shaped bellmouths on = them.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD The shape and contours were = derived from a NASA contractor report (NASA_CR3485) that you can find = via Google.=C3=AF=C2=BF=C2=BD Lots of math & formulas in it but I just = copied the best performing inlet picture of the contour.=C3=AF=C2=BF=C2=BD= =C3=AF=C2=BF=C2=BD Apparently there is an optimum radius for the inner = and outer lip of the inlet.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD There = was no change to the inlet diameters of 5.25" on water cooler and 4.75" = on oil cooler. >>>>=20 >>>> The simple pipes performed adequately in level flight at moderate = cruise settings even on hot days but oil temps would quickly hit redline = at high power level flight and in climb.=C3=AF=C2=BF=C2=BD=20 >>>>=20 >>>> The significant change with the new inlet shape is that they appear = to capture off-axis air flow=C3=AF=C2=BF=C2=BD (like in climb and = swirling flow=C3=AF=C2=BF=C2=BD induced by prop at high power)=C3=AF=C2=BF= =C2=BD MUCH better than the simple pipes. =C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2= =BD First flight test was on a 94 deg. F day and I could not get the oil = temp above 200 degrees in a max power climb. =C3=AF=C2=BF=C2=BD=C3=AF=C2=BF= =C2=BD They may have gone higher if the air temperature remained = constant but at 3500 fpm the rapidly decreasing OAT kept the temps well = under redline (210 deg F). >>>>=20 >>>> I have an air pressure instrument reading the pressure in front of = the oil cooler and was amazed at the pressure recovered from the prop = wash.=C3=AF=C2=BF=C2=BD At 130 MPH the pressure would almost double when = the throttle was advanced to WOT. =C3=AF=C2=BF=C2=BD That did not happen = nearly as much with the simple pipes.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD=20= >>>>=20 >>>> These inlets ROCK! >>>>=20 >>>> Tracy Crook >>>>=20 >>>=20 >>>=20 >>> = = Virus-free. www.avast.com = = >=20 --Apple-Mail=_380CC885-987C-4A5B-ACC6-453E2F0EFCEB Content-Transfer-Encoding: quoted-printable Content-Type: text/html; charset=utf-8 Hi = Le Roux

Those = diagrams relate to Streamline Diffusers, rather than the entrance lip = shape that Finn is chasing.

Steve



On 1 Jul 2021, at 1:52 pm, Le Roux = Breytenbach breytenbachleroux@gmail.com <flyrotary@lancaironline.net> wrote:

Finn: Has come onto these pictures.

Maybe can help in figuring out the = coordinates or help solving the X and Y 


 IMG_9641.HEIC

 IMG_9640.HEIC

Le= Roux

On Thu, Jul 1, 2021 at 5:18 AM Finn = Lassen finn.lassen@verizon.net <flyrotary@lancaironline.net> wrote:
=20 =20 =20
Thanks. I guess I kept missing it because I don't understand what I'm looking at.
Can anyone help me understand the following and show me the optimum inside/outside radius ratio (which I assume is one of the A-10 to A-40 contours):
<nadfchpfafimnegl.png>
<kbdejbnihmgdehea.png>
Finn

On 6/30/2021 9:45 PM, Charlie England ceengland7@gmail.com wrote:
=20
Seems likely; I don't recall seeing a CR3485 referenced anywhere, either.

On 6/30/2021 4:42 PM, Finn Lassen finn.lassen@verizon.net wrote:
=20
I tried in vain to find NASA_CR3485 (well, I found a NASA contractors report on animal studies).

I wonder of he meant 3405?
<bnmfmdnlndmefidc.png>

Anyone found a better match?

Finn

On 4/28/2011 9:07 AM, Tracy wrote:
=20 Finally got around to finishing my cooling inlets. (pictures attached)=C3=AF=C2=BF=C2=BD Up until now they were = simply round pipes sticking out of the cowl.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2= =BD The pipes are still there but they have properly shaped bellmouths on them.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD The shape and = contours were derived from a NASA contractor report (NASA_CR3485) that you can find via Google.=C3=AF=C2=BF=C2=BD Lots of math & = formulas in it but I just copied the best performing inlet picture of the contour.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD Apparently = there is an optimum radius for the inner and outer lip of the inlet.=C3=AF=C2=BF=C2=BD=C3= =AF=C2=BF=C2=BD There was no change to the inlet diameters of 5.25" on water cooler and 4.75" on oil cooler.

The simple pipes performed adequately in level flight at moderate cruise settings even on hot days but oil temps would quickly hit redline at high power level flight and in climb.=C3=AF=C2=BF=C2=BD

The significant change with the new inlet shape is that they appear to capture off-axis air flow=C3=AF=C2=BF=C2=BD= (like in climb and swirling flow=C3=AF=C2=BF=C2=BD induced by = prop at high power)=C3=AF=C2=BF=C2=BD MUCH better than the simple = pipes. =C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD First flight test was on a 94 deg. F day and I could not get the oil temp above 200 degrees in a max power climb. =C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD They may have gone = higher if the air temperature remained constant but at 3500 fpm the rapidly decreasing OAT kept the temps well under redline (210 deg F).

I have an air pressure instrument reading the pressure in front of the oil cooler and was amazed at the pressure recovered from the prop wash.=C3=AF=C2=BF=C2=BD = At 130 MPH the pressure would almost double when the throttle was advanced to WOT. =C3=AF=C2=BF=C2=BD That did not happen = nearly as much with the simple pipes.=C3=AF=C2=BF=C2=BD=C3=AF=C2=BF=C2=BD=

These inlets ROCK!

Tracy Crook



3D"" Virus-free. www.avast.com



= --Apple-Mail=_380CC885-987C-4A5B-ACC6-453E2F0EFCEB--