X-Virus-Scanned: clean according to Sophos on Logan.com X-SpamCatcher-Score: 10 [X] Return-Path: Sender: To: lml@lancaironline.net Date: Fri, 11 May 2007 20:16:06 -0400 Message-ID: X-Original-Return-Path: Received: from web53704.mail.re2.yahoo.com ([206.190.37.25] verified) by logan.com (CommuniGate Pro SMTP 5.1.8) with SMTP id 2038834 for lml@lancaironline.net; Fri, 11 May 2007 20:02:43 -0400 Received-SPF: none receiver=logan.com; client-ip=206.190.37.25; envelope-from=kyrilian_av@yahoo.com Received: (qmail 35761 invoked by uid 60001); 12 May 2007 00:02:06 -0000 DomainKey-Signature: a=rsa-sha1; q=dns; c=nofws; s=s1024; d=yahoo.com; h=X-YMail-OSG:Received:Date:From:Subject:To:In-Reply-To:MIME-Version:Content-Type:Content-Transfer-Encoding:Message-ID; b=uscweLg33yxnkf5SH4LvojNs/TF3JeWl/d2xKBYS778L4TAQ86ess14O80JkAGR0A/1lqZbXz/yAX1wh9pvNtKNdV3SjYEryCggrvJ5f1QYUECrmb73/8RFLBaE4UgHrvVWnU1UNdDOKHZgNjBTzKQ6AhKTRBGr3BPqwmu8lOAM=; X-YMail-OSG: oBF1GD8VM1kkWN37QKFn6lZAGi0hfnC7v_zie20vv6NFDsEpwKl4qmtgcG6FJ4l6k_3pSHkTmzDoLhFY9urfUnxxmFcoWW3QaVQge9IbAw4zpmAcpKSKxjaR5nIV8A-- Received: from [66.32.95.169] by web53704.mail.re2.yahoo.com via HTTP; Fri, 11 May 2007 17:02:06 PDT X-Original-Date: Fri, 11 May 2007 17:02:06 -0700 (PDT) From: Kyrilian Dyer Subject: Re: [LML] Re: IO-550 fuel injection, Possible Fuel Vent Clogging Problem X-Original-To: Lancair Mailing List In-Reply-To: MIME-Version: 1.0 Content-Type: multipart/alternative; boundary="0-543923938-1178928126=:32116" Content-Transfer-Encoding: 8bit X-Original-Message-ID: <188553.32116.qm@web53704.mail.re2.yahoo.com> --0-543923938-1178928126=:32116 Content-Type: text/plain; charset=iso-8859-1 Content-Transfer-Encoding: 8bit This table looks like simple dynamic pressure. The third report referenced in Chris Z's post (NACA RM A50E02) provides pressure recovery ratios for various mass flow ratios (discussion on p 5, plots on pages 14-20). While it appears nothing was tested to ratios around zero (1/4 dia wing tank vent lines at 15gph and 200 kts are in the 0.005 range--essentially zero), extrapolating a bunch makes me think we should expect mass flow ratios of 0.5 to 0.8. This is based on -2 to +2deg angle of attack at 0.3 Mach. So divide in half the pressures in the table below for a (maybe) conservative estimate. - Kyrilian Sky2high@aol.com wrote: Mike, Pressure in Units IAS mph Knots "H2O "Hg PSI 40 34.8 0.79 0.06 0.028 50 43.4 1.23 0.09 0.044 60 52.1 1.77 0.13 0.064 70 60.8 2.41 0.18 0.087 80 69.5 3.15 0.23 0.114 90 78.2 4.00 0.29 0.144 100 86.9 4.94 0.36 0.178 110 95.6 5.98 0.44 0.216 120 104.3 7.12 0.52 0.257 130 113.0 8.37 0.62 0.302 140 121.7 9.72 0.71 0.351 150 130.3 11.17 0.82 0.403 160 139.0 12.72 0.94 0.460 170 147.7 14.39 1.06 0.520 180 156.4 16.15 1.19 0.583 190 165.1 18.03 1.33 0.651 200 173.8 20.01 1.47 0.722 210 182.5 22.10 1.62 0.798 220 191.2 24.29 1.79 0.877 230 199.9 26.60 1.96 0.961 240 208.6 29.03 2.13 1.048 250 217.2 31.56 2.32 1.140 260 225.9 34.21 2.52 1.236 270 234.6 36.98 2.72 1.335 280 243.3 39.86 2.93 1.440 290 252.0 42.87 3.15 1.548 300 260.7 45.99 3.38 1.661 --------------------------------- Yahoo! oneSearch: Finally, mobile search that gives answers, not web links. --0-543923938-1178928126=:32116 Content-Type: text/html; charset=iso-8859-1 Content-Transfer-Encoding: 8bit
This table looks like simple dynamic pressure.
 
The third report referenced in Chris Z's post (NACA RM A50E02) provides pressure recovery ratios for various mass flow ratios (discussion on p 5, plots on pages 14-20).  While it appears nothing was tested to ratios around zero (1/4 dia wing tank vent lines at 15gph and 200 kts are in the 0.005 range--essentially zero), extrapolating a bunch makes me think we should expect mass flow ratios of 0.5 to 0.8.  This is based on -2 to +2deg angle of attack at 0.3 Mach.  So divide in half the pressures in the table below for a (maybe) conservative estimate.
 
- Kyrilian


Sky2high@aol.com wrote:
Mike, 
 
 
Pressure in Units
IAS mph
Knots
 "H2O
"Hg
PSI
 
 
 
 
 
40
34.8
0.79
0.06
0.028
50
43.4
1.23
0.09
0.044
60
52.1
1.77
0.13
0.064
70
60.8
2.41
0.18
0.087
80
69.5
3.15
0.23
0.114
90
78.2
4.00
0.29
0.144
100
86.9
4.94
0.36
0.178
110
95.6
5.98
0.44
0.216
120
104.3
7.12
0.52
0.257
130
113.0
8.37
0.62
0.302
140
121.7
9.72
0.71
0.351
150
130.3
11.17
0.82
0.403
160
139.0
12.72
0.94
0.460
170
147.7
14.39
1.06
0.520
180
156.4
16.15
1.19
0.583
190
165.1
18.03
1.33
0.651
200
173.8
20.01
1.47
0.722
210
182.5
22.10
1.62
0.798
220
191.2
24.29
1.79
0.877
230
199.9
26.60
1.96
0.961
240
208.6
29.03
2.13
1.048
250
217.2
31.56
2.32
1.140
260
225.9
34.21
2.52
1.236
270
234.6
36.98
2.72
1.335
280
243.3
39.86
2.93
1.440
290
252.0
42.87
3.15
1.548
300
260.7
45.99
3.38
1.661
 

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