Nielsen, Jack Norman

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RUTHOR'S PERSONAL COPY ARR No. L4Illb 
7N-34 
/le.-. 4 / 7  
74 
NATIONAL ADVISORY COMMITEE FOR AERONAUTICS 
/ Y 7 0 3  
0RlGlNALl.Y ISSUED 
September 1944 as 
Advance Restricted Report  L4111b 
HIGH-ALTITUDE COOLING 
III - RADIATORS 
By Jack N. Nielsen 
Langley Memorial  Aeronautical Laboratory 
Langley Field, Va. 
(bBCE-BEE-L4111L) t i 1 G t - A i 3 f l L D E  COGLING.  3: 
i i A C X A I C k 5  A b s t r a c t  Cnfy ( b a t i c c a l  Advisory 
CcBmrttee f o r  AGrcaautics. I a r c l c y  
AEronautical  iai.) 24 F 00134 
H89-7 CG07 
Unc la I 
C147053 
WASHINGTON 
NACA WARTIME REPORTS are reprints of papers originally issued tu provide rapid distribution of 
advance research results to an authorized group requiring them for the w a r  effort. They were pre- 
viously held under a security status but are now unclassified. Some of these reports were not tech- 
nically edited. A l l  have been reproduced without change in order ta expedite general distribution. 
L-773 
1 https://ntrs.nasa.gov/search.jsp?R=19890067694 2020-03-20T00:21:33+00:00Z
NACA ARR loiilLgIllb 
* NATIONAL ADVISORY COMMI!ElTE FOR- AEROWUTICS ., . 
. . ,  
HIM-ALTITUDE COOrSIG. 
I11 - RADIATORS 
By Jack 1. Nielsen 
. <  , ,  
* .  .. * . .  sLTIWARY 
2 ' i ' .  
A detai led anelyele has Wen made t o  take account of the 
high cooling-air velocity occurring in high-altitude radiatore. 
Method6 are developed for determining the heat-tranefer rate, 
the preeeure drop, and the drag; parer. So& ef fec te  of Mach 
number are ahown, Rsdiator performance charts baaed on the anal- 
yeie are presented f o r  a w i d e  range of the deeign variablee. The 
application of the chart8.ig shown bX an example. 
a given total-preeeure loee i e  not great ly 'affected by the high 
airplane veloci t iee  but .that the neceeeary total-preeeure 1086 
and the reeulting drag are both b e a t l y  increaeed a t  high al t i -  
t u d e ~ .  . 
The perforp3ance aharts ehaw that the heat-transfer rate f o r  
' I"l3ODUCTION . 
Extensive l i t e ra ture  i e  available re la t ive  t o  the perfom- 
ance of ethylene-glycol radiators -in the normal range of oper- 
a t ing  conditione. A t  high alt i tudoe, hovever, cer ta in  e f fec te  
that normally receive but l i t t l e  coneideration acquire increaeed 
importance as a reau l t  of the high veloci t iee  of the cooling air 
through the tubes. The purpose of t h i e  paper i e  t o  deecribe and 
evaluate these effecte.  
The theoriee are outlined on which are based the calcula- 
t ione of heat tranafer,  o f , f r i c t i o n  proeeure drop, and of accel- 
erat ion pressure drop at high Mach numbers. 
equation for $he pressure drop and eome approximate eolutione 
f o r  the equation a re  given.' Radiator doeign charts baeed on the 
eimpleet of these approxirpate &utione a re  included. 
A general d i f f e ren t i a l  
Thee0 charts 


High-altitude cooling. 3: Radiators

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