A development test program of 3 hot air flat plate solar collectors is described in detail. The pressure drop versus flow rate performance characteristics for these collectors, mounted in series, was determined under 14 different test conditions each of which was characterized by a unique combination of inlet air temperature and air flow rate. Characteristics of inlet, exit and transfer ducts of these collectors were also determined during this testing. The test results indicate that significant pressure drop occurs at air flow rates greater than 150 standard cubic feet per minute and this drop is not heavily dependent upon inlet air temperature; and inlet, exit and transfer duct characteristics differ sufficiently to suggest that system performance may be enhanced through careful design of each type of duct individually

Losey, R.

English

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Produced by the NASA Center for Aerospace Information (CASI) 
https://ntrs.nasa.gov/search.jsp?R=19780009528 2020-03-22T06:24:32+00:00Z
DOE/RASA CONTRACTOR REPORT
'	 DOE- ; NASA C° - 150495
t%` SFC HOT A I R COLLECTORS - PHASE I
TEST REPORT
4
Prepared by
le Laboratories
Solar Energy Systems. Division
Huntsvii1e. Alabima 3580.3
Under suh-contract to
IBNT Corporation. Federal System. Division, lluntsville. .11abama 35505
Contract NASA -32036
\atiomil .NeronautiCS and Space .administration
George C. 'M-I rshali Space Flight Center, :llahatna : •i`^1?
for the Department of Fner;p-
1
495)	 m 	 t_.i i,1LI COLLfC'A ,.	 N78-11411
PHASE 1:	 'TEST hrFOFt:
	 yl,^ Iabs., Inc.)
15 p Ht: A02 /1'li A01	 CS)CL 1 VA
I Tic 1 '1 S
1/4 14	 05361
U. S. Department of Energy
f
U
Solar Energy
I
h
.--..r
1unT_C"
:^.i!s report was prepared to document work sponsored by the
United States ;,overnment. Neither the United States nor its
ag-snts the United States Department o" Znergy, the United
States .at=onal Aercnautics and Spacu kdministration, nor any
:ederal employees, nor any of their contractors, sub^ont:actors
or their employees, make any warranty, express or t=plied, or
assume any legal liabilit7 or responsibility for t:e accuracy,
completeness, or usefulness of any information, apparatus,
product or process disclosed, or represent that its use would
not inrringe -^rivataly owned rights.
&.
a
t
7W f
T	 ICAL REPORT ST ANDARD i
I , Rf P(IRT NU.	 2, GOVERNk* NT ACClSSIUN NO	 J . RECIPIENT-S CATALOG N0.
U01? NASA C12 15049.5
♦, TITi f AND SUOTITL[
NISVC 1107 Allt CC)LLFCTORS - Phase 1
Tout lteporl
7. AUTN(Mi1)
It. I,osey
9 . P[RFORU iNG ORGAMIZATION NAM[ AND ADDRESS
Wyle Luborntorles
Scientific Services aril S y stems Group, Solar Energy Sys Div
IGmtsville, Alabama 35505
17 SPON!IORING AO[NCY NAME AND ADDRESS
Nnticmal Aeronnutics and Space Administration
11'rtmhln^^ton, 1`. + C. 20540
18, SUPI •LEMENTARY NOTES
']'film work was acco , nplished snider the technical supervision of Charles N. Thomas,
Mitt-shill Space Flight Center, Alabama.
15, ASSTRACT
Three hot air flat plate solar collectors momifactured 11 N , Marshall Space Flight Center
(no serial numbers) were subjected to a M^velopmeat Test Program as described in detail in
this report. The pressure drop versus floe- rate+ pci-for • manec c• hat:ictcristics for these
collectors, inounted in serle q . was determined under fourteen different test conditions each of
which was characterized by a unlque conihhuttion of inlet air temperature and air flow rate.
Chit racteristies of inlet, exit and transfer ducts of these collectors were also determined during I
	
this tasting. 'rhe test results indicate that (1) significant pressure drop occurs at ail- tlow 	 t
	
rsites greater than 150 Stan(tird Cubic Feet Ver minute (SCFM) and this drop is not heavily 	 I
clepondent upon inlet air tcniperature, and (2) inlet. exit and transfer duct characteristics
differ mufficicntlY to suggest that system performance ni:i
,
\• be enhanced through careful design
of each type of duct individually.
17
	 Is. DISTRIBUTION STATEMENT
ITnelasstfied-Unlimited
William A. Brooksbank, Jr.
Nlandger
19. SECURITY CLASSI F , (of this repat)	 kO . SECURITY CLASSIF, (of this pe4e) 	 21 NO. OF, Fmur5 22 PRICF
IInclas+sifled	 I'nc • lassified	 t-t	 NTIS
' WI-1- - Form 3293 ( NB Y ICAO)	 For sale,
 by Nat'l Tech Information Svc, :*rinbfield, Va. 22151
S REPORT OAT!
_ November 197 7
e; Pf RI OR MIN(: OW. A0,11ATtON C(OE
a PINFORMING ORGANIZATION R[PhRI s
_ WYLF TR-531-1, Rev A
10. WORK UNIT NO.
11. CONTRACT OR GRANT NO.
NASN-32036
13 TYPE OF REPORT & PERIOD COVLRED
Contractor Report
1 .1 SPONSORIN(. AGENCY CODF
'i Ab LE J:' CON T,
1.0 PURPOSE
2.0 REFERENCES
3.0 MANUFACTURER
4.0 SUMMARY
5.0 TEST CONDITIONS AND TEST EQUIPMENT
5.1 Test Article Description
5.2 Ambient Conditions
5.3 Instrumentation and Equipment
6.0 REQUIREMENTS, PROCEDURES AND RESULTS
6.7. Test Title
6.1.1 Requirements
6.1.2 Procedures
6.1.3 Results
TABLE I.	 DATA GENERATED PRESSURE PROFILES
100, 2V SCFM AT 80°F
TABLE II. DATA GENERATED PRESSURE PROFILES
200 SCFM AT 100°F, 200°F
TABLE III. HOT AIR COLLECTOR dP DATA
FIGURE I. STATIC PRESSURE MEASUREMENT IDENTIFICATION
r
1^.
1.
t
1
2
2
2
2
2
2
2
3
5
6
7
8
11
i
k
QIIIGINAL PAGV, IS
OF PU014 QUALITY
1.1 . U
	
111JPIIOSF:
The purJ) ,.)se of this i eport i:; to present the test
procedures used and the results obtained during the
performance of Phase I of a. development test program.
Phase I of the test program was conducted to determine
the pressure drop across three prototype Hot Air
Collectors as a function of air velocity and operating
temperature in accoraance with references shown in
Section 2.0.
	
2.0	 REFERENCES
	
2.1
	
MSFC Memorandum EP (76-23), dated June 1, 1976.
MSFC AVO 76-103 from FT--44, dated June 3, 1976,
Subject: Testing of MSFC Hot Air Collectors.
	
2.2	 Test Procedure, MTCP-DC-SHAG-400, "MSFC Hot Air
Collector - Phase I Test Procedure".
	
3.0
	
MANUFACTURER
National Aeronautics 6 Space Administration
George C. Marshall Space Flight Center
Huntsville, Alabama 35812
	
4.0	 SUMMARY
Three hot air flat plate solar collector:; manufactured
by Marshall Space Flight Center (no serial numbers)
were subjected to a Development Test Program as
described in detail in this report. The pressure drop
versus flow rate performance characteristics for these
collectors, mounted in series, were determined under
fourte.. , n (14) different test conditions each of which
was characterized by a unique combination of inlet air
temperature and air flow rate. Characteristics of
inlet, exit and transfer ducts of these collectors
were also determined during this testing. The test
results indicate that: 1) significant pressure drop
occurs at air flow rates greater than 150 Standard
Cubic Feet Per Minute (SCFM) and this drop is not
heavily dependent upon inlet air temperature, and
2) inlet, exit and transfer duct characteristics
differ sufficiently to suggest that system performance
may be enhanced through careful design of each type
duct individually.
5. u ri-:..T CON TJTTr.OWc	 PNO TE'Sr [?QU!V9'rNT
5.1 Teut Article Description
The test article consisted of three MSFC Clot Air
Collectors manifolded in series. 	 Each collector
had a	 surface area of	 17.5	 ft 2	(1.62 m2)	 with air
transfer ducts of 	 0.65	 ft 2	(0.06 m 2 ).	 Each
collector was	 3	 ft	 (0.96	 m)	 wide,	 6	 ft	 (1.8 m)	 long,
0.6 ft
	
(0.18 m)	 deep and weighs approximately 35 lb
(15.9 kg).	 The collector surface was a 0.012	 inch
2024-T3 aluminum plate coated dark on the top surface.
The collector was covered with a single,
	
0.125 inch,
standard plate glass.
5.2 Ambient Conditions
Unless otherwise specified herein, 	 all test: were
performed at an atmospheric pressure of 29.38 +0.50
inches of mercury absolute,	 a temperature of 23° +2°C
and a relative humidity of approximately 50 percent.
5.3 Instrumentation and Equipment
Instrumentation consisted of two copper-constantan
thermocouples monitored by a Mity-Mite T.C. meter
and a water-filled inclined manometer with a resolu-
tior. of	 0.01 inches of water.
The air supply system used for the test was a 3500 psi
missile air supply system available at Building 4619.
This supply was regulated and heated through the use
of a three-stage regulator stand equipped with an
18 kW proportional controlled heater stage.
6.0 REQUIREMENTS, PROCEDURES AND RESULTS
6.1 Test Title:	 MSFC HOT AIR COLLECTOR TEST - PHASE I
6.1.1 Requirements
Determine pressure drop over the collectors under
the followin g
 conditions:
Air Flow Rate	 (SCFM)	 Temperature
	 (`F)
30	 800	 and	 1100
URI('7L1 AL PAGE 1.
Q.UALI'I'Y
10 0
	800	 and	 110°
OF pWR 120	 80°	 and	 1101
` 200	 800	 and	 '1100
2
,^	 1 ^ 1
E.
^.1.(	 l` ► U,.av4ILI,4,:,
6. 1.2.1	 I l IIIL'., lee of Opera tion
The test articles were arranycd as indicated in
Figure 1.	 Air fi^)m I, ►e ► vgL.l..t.):.,he: ► ter system
was allowed to expand and pass through a six foot
by eight-inch diameter chamber to facilitate
equalization prior to passing into the collectors.
From this expansion chamber the air was routed
through the entrance duct to the first collector.
This intake manifold was instrumented for static
air measurements. The air passed through all three
collectors in series before exiting to ambient
pressure through an exhaust duct identical to the
entrance duct.
Air flow was mensured in Actual Cubic Feet Per
Minute (ACFM) after gassing throudti the heater :ind
converted to Standard Cubic Feet Per Minute (SCFM)
for test purposes. The temperature sensing for the
controller was located at the flowmeter section and
concurrently monitored at the first collector inlet
port for test parameter determination.
6.1.2.2
	 Initial Test Procedure Modifications
Duriny the proceE:s of system performance veri i i cati on,
it was determined that the initial pressure sensing
port locations wt-re inadequate. Due to their
orientation they were producing erroneous results.
They were relocated as shown in Figure I upon approval
of Mr. F. zurBurg. It was also decided to drop the
proposed data format and use a new format which does
not include indivi.du, ► 1 differential measurement for
each .;ollector, since it was agreed that those measure-
ment: woulO not obtain further pertinent data.
6.1.2.3
	 Test Procedure
1.	 Set up propt-r test parameters -- This required
setting a temperature/air flow configuration;
allowing foi sy::tem stabilization; determining
true SCFM/inlet temperature parameters; adjusting
to new ACFM,temperature configuration if required
by test parameters; and computing new true SCFM/
inlet temperature conditions. This process was
repeated until correct test parameters were
obtained.
3
6.1.2.4
Revision A
2. Manometer was tested for zero offset -- This was
don_! oy exposing both differential sensing lines
to ambient pressure.
3. Flowmeter frequency, temperature, pressure,
inlet and outlet air temperature, and manometer
zero offset were recorded on data sheet.	 (A,
4. The static prt!ssurc at Test Port 1, see Figure 1,
referenced to amt,ient pressure was measured and
recorded -- This was done by attaching one sense
line to Port No. 1 and exposing the second line
to ambient pressure. Caution was required to
determine correct sign of the pressure value
(+ or - reference to ambient).
S.	 The static pressure at TP:',c Port 2, see Figure 1,
reter.ence to Test Port (1) was measured and
r ord .+
Caution was required to determine correct sign of
the pressure valise (+ or - Reference to ambient) .
61	 The static pressure at Test Ports 3 through 14
referenced to Test Port (1) were measured and
recorded in the same manner as in Step S above.
7. Inlet and outlet air temperature were noted --
If either temperature changed by more than one
degree Fahrenheit, that temperature was recorded
as the original temperature plus one-half the
change in temperature.
8. The flow-meter frequency was manitor^d and the
,.verage deviation from the initial recorded
frequency was recorded.
Data Analysis
Before complete data evaluation was possible, it was
necessary to accurately determine the true test par-
ameters. This was done by correcting the indicated
flow for temperature and pressure deviations from
standard conditions using the following equation:
owl
t. '.
. n
SCFM = ACFM x K x PAj'i'K
ORIGINAL PAGE, I'-'j
OF YuOR QUALITY
4
who i r -	 ." M	 stond.t r i cl- 1 , 1 ­ ,# ., . % r m 1 mite
ACF'M	 Actual cubic feet per minute_
(Interpreted from the frequency
v-, rsus ACFM curve of the flowmeter)
K	 = 19.948 (conversion factor obtained from EC23)
PA 	s Meter pressure in Asia
TK	z Meter temperature in °K (degrees Kelvin)
Correction was also made on the fluctl ►atzons of the
flowmeter to determine their detrimental effect on
the accuracy of the test parameters.
Once the data was corrected for non-standard conditions,
pressure profile trends were generated for each type of
transfer duct as well as a centerline profile.
6.1.3	 Results
The results of the tests are depicted in Tables I, 11
and III, and form the basis for the following
conclusions:
1. The pressure drop becomes significant above
150 SCFM.
2. Pressure gradients across the transfer ducts are
significant and could be altered through better
design.
3. Pressure gradients across the transfer ducts
.;re not strongly temperature dependent.
4. Pressure gradients across the transfer ducts are
velocity dependent.
S.	 The pressure drop across the collector is heavily
velocity dependent and slightly temperature
dependent.
6. For conditions up to 200 SCFM at 200°F, pressure
drops of greater than 0.17 inches of water
should not be ei.countered for an individual
collector.
7. More reliable data should be obtainable through
the use of a lower pressure air supply, and
better designed inlet air ducts.
5
i
W9i
i
E 1
1
r T11 :;'	 e:'1'.1:I` """: ':URE i'ROr'ILES
100, 200 SCFM AT 80°F
0.00-^;-	 ---♦''- ` 100 S('F':.l
200 SCFM
2	 1	 3
	 INLET PROFILE
W I ^-,
0.0
-0.0	 100 SCFM
-0.1
	
--200 SCFM
-0.20
S	 4	 6
0 5•r
100 SCFM
•0. 3 0--
-0 . ? .
	
?F---.^-
-0.4	 --	 200 SCFM
9	 8	 10
TRANSFER PROFILE
EXIT PROFILE
	
0 0
	
100 SCFM -7
	
-0•^	 200 SCFM
-U.J
-0. 4(
13 - 14	 1.	 4	 7	 8	 11	 12	 PRESSURE. PROFIL E
ORIGINAL PArF IS
OF POOR (QUALITY
6
1	 t'
100°F
9	 8	 10
	
EXIT PQOFILE
0.00
-0. 10
-0.20
-0. 30
-0.s0
-0.50
IUO SIYM A 	 ,c. . , [Jj'k'
	0.02	 200 °F
0.01
	0.00	 100°:
-0.01
2	 1	 3 INLET PROFILL
-0.10	 ___ 200 ° F
--0. 15
-0.20	 200°F
5	 4	 6
	 TR.11N6FER PROF I TJ:
-0. 30
-
-0.35	 100°F
-0.40
-0.45 -^- X'--- i^11/'
	 2 0 0° F
100"F
	
—T--= i-----r— T—+	 F-----^---
13	 14	 1	 4	 7	 8	 ll	 12
4^N'rFRLINL.
P RL,S,S U RE PROFILE
7
iS
C.
T T4
TABLE
	
r T I. HOT AI k CuIAXCTO R AP F,ATA
DATE 7/23 I	 7/23 7/23 7/23 7/23T7/23
TEST 0 1 2 s 4 5 tTEMP or 81 72 60 54 80 80SCFM 45(44.3) 115(95.7) 140(144.8) 227(226) 30
150
100
4751,'I1EQ
	
Ilz 225 475 I	 700 900
TEMP °I, 76 64 58 57 70 72VRrS.S psis AMB AMB AMA 17.7 AMB AMB
INLET O F 91 72 60 54 SO 79
ou ,rLET o V 87 76 62 58 80 80
zr,Ro "if 2 0 0.00 0. o0 0.00 0.u0 0.ou o.o0
01	 ;(FF,,II 0 0.025 0.10 23to AMD 2 0. 0.45 0.00 0.10
REFERENCE TO #1 POSITION
"11220 I	 -	 0.01 0.00 0.00 0.00 0.00 0.000.00 0.00 0.00 0.00 0.00 0.004 -	 0.01 0.05 0.08 0.15 0.00 0.055 -	 0.01 0.05 0.06 O.io 0.00 0.046 -	 0.01 0.05 0.10 0.20 0.00 0.057 -	 0.01 0.07 0.15 0.28 0.00 0.088 -	 0.02 0.08 0.20 0.43 0.00 0.089 -	 0.02 0.08 0.20 0.40 0.00 0.0810 -	 0.02 0.10 0.23 0.45 0.00 0.0811 -	 0.02 0.10 0.23 0.47 0.00 0.0912 -	 0.03 0.09 0.23 0.47 0.00 0.0013 -	 0.00 0.20 0.00 0.00 0.00	 X0.0014 -	 0.01 0.30 0.00 0.00 0.00 0.00
Niunbers in parentheses ( ) indicate true test values
as determined by T, I ,
 flow correction which weredifferent from desired test parameters.
DATA RESOLUTION IS 10.01 inches of 1I201
f)F, WR QUALITY1k	 P
8
TA I ll GE I 1 I .	 ( I 'I s ►h" A NIP , 10
U, T  7/23 7/A i/17 7/27
TEST
	 A 7 8 9 10
Tr Mr	 OF 80 80 100 100
:;Ci'M	 (») 120(118+6) 200(.- 28+5) 100 (103.7) 115(111.3+7)
FREQ	 llz 580	 +30 950	 +5 550 580	 +40
TEMP	 OF 74 78 100 100
I'RESS Nsia 14.7 17.7 1.4.7 14.7
INLET	 O F 80 80 96 97
OUTLET O F 80 80 98 94
ZERO	 "H 2 0 0.00 0.00
_	
0.00 0.00
## 1	 ItEF ,, H	 O
to FMB	 2 0.11 0. 40 0.10 0.13 
REFERENCE TO #1 POSITION
"11 ? O	 2 0.00 0.00 0.00 0.00
3 0.00 -0.01 -0.01 -0.01
4 -0.05 -0.13 -0.05 -0.05
5 -0.04 -0.09 -0.04 -0.05
6 -0.06 -0.16 -0.05 -0.06
7 -0.08 -0.27 -0.08 -0.08
8 -0.10 -0.37 -0.10 -0.10
9 -•0.10 -0.35 -0.10 -0.10
10 -0.10 -0.40 -0.10 -0.10
11 -0.10 -0.40 -0.10 -0.10
12 -0.10 -0.40 -0.10 -0.10
1.3 -0.00 -0.00 -0.10 -0.00
14 -0.00 -0.00 -0.00 -0.01
9
" A PI F I I1 .	 ((7, )AC.
DATE: 7/27 7/27
	 7/27 7/27
TEST
	 N 11 12	 13 14
'TEMP	 OF 100 200	 200 200
SCFM 200(211+10) 100(100.9+7)	 115(115.9+7) 200(228.7+4)
FREQ	 Hz 970+50 680+50 775+50 1150 + 20
TrMP	 OF 106 2 255 230
PRESS pdia 16.7 14.7 14.7 18.7
INLET	 O F 100 205 209 195
OUTLET OF 98 164 169 174
ZERO
	 "H20 0.00 0.00 0.00 0.00
# 1	 IZL; r „ H
	
0
2 0.36to AMID 0.12 0.1(1 0.52
REFERENCE TO N1 POSITION
1 '.
?oil 2 O	 2 0.00 0.00 0.00 0.02
3 -0.01 (1.00 0.00 -0.01
4 -0.10 -0.05 -0.05 -0.14
5 -0.10 -0.05 -0.05 -0.10
F -0.15 -0.06 -0.06 -0.19
7 -0.23 -0.08 -0.09 -0.30
8 -0.33 -0.10 -0.12 -0.46
9
I	
-0.11 -u.10 -0.12 -0.45
10 -0.-s5 -0.10 -0.13 -0.50
11
12
-0.36
-0.36
-0.10
-0.10
-0.13
-0.13
-0.53
-0.51
13 0.01 -0.01 0.00 0.05
_14 -, 0_00 0.00 0.00 0.00
ORIGINAL PAGE IS
OF POUR QUAIITY
10
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N 0 T I C E
When government drawings, npec•ific•ations
or other data are u:ied for any purl)ost,
other than in connection with a cl(-!finitttly
relate-.d government_ pr()c;urement op-ration,
tho United States government thereby incurs
nc) responsibility nor any obligation
what' yoevert and the fact that the novern-
mnnt may have formulated, furnished. or in
--Any way supplied the said clr.awinys, .',fter_ifi-
cau i ons or other data is not to be regarded
by implication or otherwise s in any manner
the holder or any other person or
corpot-at ion or conveying any rights or
permission to manufacture, use, or sell any
patont vd invention that may in any way be
relat, I t:hereto.
ti A's n tir.PC.
12


MSFC hot air collectors. Phase 1: Test report

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