X-Virus-Scanned: clean according to Sophos on Logan.com From: "Steven W. Boese" Received: from [207.46.100.122] (HELO na01-by2-obe.outbound.protection.outlook.com) by logan.com (CommuniGate Pro SMTP 6.1.7) with ESMTPS id 8184921 for flyrotary@lancaironline.net; Sun, 22 Nov 2015 20:08:27 -0500 Received-SPF: none receiver=logan.com; client-ip=207.46.100.122; envelope-from=SBoese@uwyo.edu Received: from BN3PR0501MB1138.namprd05.prod.outlook.com (10.160.113.148) by BN3PR0501MB1138.namprd05.prod.outlook.com (10.160.113.148) with Microsoft SMTP Server (TLS) id 15.1.331.20; Mon, 23 Nov 2015 01:08:09 +0000 Received: from BN3PR0501MB1138.namprd05.prod.outlook.com ([10.160.113.148]) by BN3PR0501MB1138.namprd05.prod.outlook.com ([10.160.113.148]) with mapi id 15.01.0331.019; Mon, 23 Nov 2015 01:08:09 +0000 To: Rotary motors in aircraft Subject: Re: [FlyRotary] Re: Request for Performance specs on VAF Thread-Topic: [FlyRotary] Re: Request for Performance specs on VAF Thread-Index: AQHRJXuUS5lArNmEAkqNXAbQTF/ooJ6oyDvJ Date: Mon, 23 Nov 2015 01:08:09 +0000 Message-ID: References: In-Reply-To: Accept-Language: en-US Content-Language: en-US X-MS-Has-Attach: X-MS-TNEF-Correlator: authentication-results: spf=none (sender IP is ) smtp.mailfrom=SBoese@uwyo.edu; x-originating-ip: [69.146.103.188] x-microsoft-exchange-diagnostics: 1;BN3PR0501MB1138;5:5+geR84EdTZ3zHH/ZbTw30viLxG6FVXtMb8WNl/QWkHyVyi2vx+l9mazklbmLG6H/seWQJMMSsqJ0d3buW5vltcQkaSooHwq6OYy35Ncz1gzEAWjTSZqBwSN1f4/y3gIVFT8xkK+uklJ2XBHdLVTEQ==;24:GU0IKAB+6NTOsw5eTIteGG12/L4ic54DASVsSl1JWAAL72ktpfO1FBE81Yq2Re9D79QGBgQ5MbbgYC35byeNPtI9owrfOxU10LbCAsIL1Wc= x-microsoft-antispam: UriScan:;BCL:0;PCL:0;RULEID:;SRVR:BN3PR0501MB1138; x-microsoft-antispam-prvs: x-exchange-antispam-report-test: UriScan:; x-exchange-antispam-report-cfa-test: BCL:0;PCL:0;RULEID:(601004)(2401047)(5005006)(520078)(8121501046)(3002001)(10201501046);SRVR:BN3PR0501MB1138;BCL:0;PCL:0;RULEID:;SRVR:BN3PR0501MB1138; x-forefront-prvs: 07697999E6 x-forefront-antispam-report: SFV:NSPM;SFS:(10019020)(279900001)(479174004)(189002)(24454002)(377454003)(199003)(164054003)(102836003)(586003)(74316001)(92566002)(3846002)(86362001)(19617315012)(5004730100002)(19627405001)(6116002)(5007970100001)(11100500001)(89122001)(66066001)(5008740100001)(189998001)(81156007)(16236675004)(88552001)(19625215002)(19625305001)(122556002)(97736004)(50986999)(10400500002)(90282001)(5002640100001)(2950100001)(5003600100002)(101416001)(40100003)(54356999)(33656002)(76176999)(2900100001)(450100001)(77096005)(106356001)(105586002)(75432002)(19580405001)(15975445007)(106116001)(80792005)(19580395003)(107886002)(87936001)(5001960100002)(110136002)(76576001)(99286002);DIR:OUT;SFP:1102;SCL:1;SRVR:BN3PR0501MB1138;H:BN3PR0501MB1138.namprd05.prod.outlook.com;FPR:;SPF:None;PTR:InfoNoRecords;MX:1;A:1;LANG:en; received-spf: None (protection.outlook.com: uwyo.edu does not designate permitted sender hosts) spamdiagnosticoutput: 1:23 spamdiagnosticmetadata: NSPM Content-Type: multipart/alternative; boundary="_000_BN3PR0501MB1138CC4B569E3868CCF26871B9070BN3PR0501MB1138_" MIME-Version: 1.0 X-OriginatorOrg: uwyo.edu X-MS-Exchange-CrossTenant-originalarrivaltime: 23 Nov 2015 01:08:09.0942 (UTC) X-MS-Exchange-CrossTenant-fromentityheader: Hosted X-MS-Exchange-CrossTenant-id: f9cdd7ad-825d-4601-8e9c-a325e02d52da X-MS-Exchange-Transport-CrossTenantHeadersStamped: BN3PR0501MB1138 --_000_BN3PR0501MB1138CC4B569E3868CCF26871B9070BN3PR0501MB1138_ Content-Type: text/plain; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable Kelly, I tried cores from two sources: 60-66 Ford/Mercury from Fast Forward, Rialto,CA, part # PCE109.1055, 3 row = , 15 fins/in. Dewitts Radiator 1139012M from Summit Racing, part # DWR-1139012M, 2 row, 1= 5 fins/in. Big difference in price, little difference in performance. Long term relia= bility difference: unknown. The cores were the desired width and cut to size with a band saw after remo= ving the original tanks. New tanks were then tig welded to the header plat= e. Steve ________________________________ From: Rotary motors in aircraft on behalf of = Kelly Troyer Sent: Sunday, November 22, 2015 4:14 PM To: Rotary motors in aircraft Subject: [FlyRotary] Re: Request for Performance specs on VAF Steve, Curious as to your source for the 7x16.5x2.25 radiator cores.........I a= m in need of about 9.5x16.5x2.25 cores..........Also how many fins per inch of your cores ?............ Thanks, Kelly Troyer On Sun, Nov 22, 2015 at 4:17 PM, Steven W. Boese > wrote: Charlie, The following data can be forwarded to the VAF thread as you see fit: The data are averages for stabilized cruise portions of cross country fligh= ts with a single 7x16.5x2.25" radiator core in a belly mounted scoop. The = Altrak altitude hold was engaged and the data was recorded by the Dynon EFI= S and EMS at 3 second intervals. The stock cooling air inlets were blocked= with flat foam plugs with about 2 sq in openings in each to supply some ai= r flow through the cowl. RV-6A, wheel and gear leg fairings installed. Mazda 13B engine, normally aspirated. RWS RD1A PSRU, 2.18:1 reduction ratio. Warp Drive HP propeller, 3 blade 68" dia, 16.5 degree pitch at tip. Belly mounted scoop for cooling, containing coolant radiator and oil to coo= lant heat exchanger, variable air outlet. Auxiliary coolant radiator in cowl, thermostat controlled coolant flow, var= iable air inlet. Stabilized cruise averages: date 8/15/2015 8/15/2015 8/16/2015 duration (min) 20 40 = 70 ALT (ft) 9530 11530 10593 DA (ft) 12446 14294 13078 OAT (deg F) 69 59 = 59 MAP (in Hg) 20.8 19.2 19.0 RPM 5747 5712 55= 91 CAS (knots) 116 112 1= 12 TAS (knots) 145 143 1= 41 FF (gal/hr) 8.75 8.15 7= .76 wt (lb) 1745 1715 1= 710 Coolant T in from cowl rad (deg F) 177 164 125 Coolant T in from scoop rad (deg F) 184 181 179 Coolant T out (deg F) 190 187 185 Oil T out (deg F) 226 222 216 Oil T in (deg F) 205 202 1= 98 As possible point of interest, a more recent test flight with a V shaped ra= diator with two 7x16.5x2.25" cores in the scoop was made. In the cruise co= ndition with a 114 degree F air temperature rise through the scoop radiator= , the aircraft TAS was 143 knots and the scoop outlet air velocity was meas= ured to be 157 knots TAS. Steve Boese RV6A, 1986 13B NA, RD1A, EC2 -- Homepage: http://www.flyrotary.com/ Archive and UnSub: http://mail.lancaironline.net:81/lists/flyrotary/List.= html --_000_BN3PR0501MB1138CC4B569E3868CCF26871B9070BN3PR0501MB1138_ Content-Type: text/html; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable

Kelly,


I tried cores from two sources: 

60-66 Ford/Mercury from Fast Forward, Rialto,CA, part # PCE109.1055= , 3 row , 15 fins/in.


Dewitts Radiator 1139012M from Summit Racing, part # DWR-1139012M, 2 row, 1= 5 fins/in.


Big difference in price, little difference in performance.  Long te= rm reliability difference: unknown.


The cores were the desired width and cut to size with a band saw after r= emoving the original tanks.  New tanks were then tig welded to th= e header plate.


Steve



From: Rotary motors in ai= rcraft <flyrotary@lancaironline.net> on behalf of Kelly Troyer <fl= yrotary@lancaironline.net>
Sent: Sunday, November 22, 2015 4:14 PM
To: Rotary motors in aircraft
Subject: [FlyRotary] Re: Request for Performance specs on VAF
 
Steve,
   Curious as to your source for the 7x16.5x2.25 radiator co= res.........I am in need of about 9.5x16.5x2.25 cores..........Also how man= y fins per inch
of your cores ?............

Thanks,

Kelly Troyer 

On Sun, Nov 22, 2015 at 4:17 PM, Steven W. Boese= <flyrot= ary@lancaironline.net> wrote:
Charlie,

The following data can be forwarded to the VAF thread as you see fit:

The data are averages for stabilized cruise portions of cross country fligh= ts with a single 7x16.5x2.25" radiator core in a belly mounted scoop.&= nbsp; The Altrak altitude hold was engaged and the data was recorded by the= Dynon EFIS and EMS at 3 second intervals.  The stock cooling air inlets were blocked with flat foam plugs with about = 2 sq in openings in each to supply some air flow through the cowl.

RV-6A, wheel and gear leg fairings installed.
Mazda 13B engine, normally aspirated.
RWS RD1A PSRU, 2.18:1 reduction ratio.
Warp Drive HP propeller, 3 blade 68" dia, 16.5 degree pitch at tip. Belly mounted scoop for cooling, containing coolant radiator and oil to coo= lant heat exchanger, variable air outlet.
Auxiliary coolant radiator in cowl, thermostat controlled coolant flow, var= iable air inlet.

Stabilized cruise averages:
date                    &= nbsp;    8/15/2015      8/15/2015    &nb= sp; 8/16/2015
duration (min)               20&nbs= p;                     40=                     70 ALT (ft)                  &nbs= p;     9530               = ;11530             10593
DA (ft)                   = ;    12446               = 14294             13078
OAT (deg F)                  &= nbsp;  69                 = ;    59                &n= bsp;   59
MAP (in Hg)                  2= 0.8                 19.2 =                19.0
RPM                    &n= bsp;          5747        &nbs= p;       5712             = ;  5591
CAS (knots)                  &= nbsp;  116                &nbs= p; 112                  112 TAS (knots)                  &= nbsp;  145                &nbs= p; 143                  141 FF (gal/hr)                  &= nbsp;   8.75                &n= bsp;8.15                7.76
wt (lb)                   = ;         1745           =     1715               1= 710

Coolant T in from
cowl rad (deg F)              177  =                 164    &n= bsp;            125

Coolant T in from
scoop rad (deg F)            184   =               181      &= nbsp;          179

Coolant T out (deg F)      190        &n= bsp;         187          &nbs= p;     185
Oil T out (deg F)               226=                   222  &n= bsp;             216
Oil T in (deg F)                &nb= sp; 205                  202&n= bsp;               198

As possible point of interest, a more recent test flight with a V shaped ra= diator with two 7x16.5x2.25" cores in the scoop was made.  In the= cruise condition with a 114 degree F air temperature rise through the scoo= p radiator, the aircraft TAS was 143 knots and the scoop outlet air velocity was measured to be 157 knots TAS.

Steve Boese
RV6A, 1986 13B NA, RD1A, EC2
--
Homepage:  http://www.flyrotary.com/
Archive and UnSub:   http://mail= .lancaironline.net:81/lists/flyrotary/List.html





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