Wind tunnel tests dealing with the effects of a Douglas YO-31C airplane of various bearings behind the radiator. GALCIT (Guggenheim Aeronautics Laboratory, California Institute of Technology) Report 117
no:iort }117 Pae;e 3.
t aken as the correct t:::i.re <lrag i'or the nm'1 ritmin·; . The new taro dras
was about 7 ~& s:.1aller t han t ho old one .
The notation and met hods of reducine t he data were all
identical with those described in the eo.rlier Reports a.n.d will not be
further discussed here.
The accuracy , a:s indicated by t he scatter of t l10 plotted
experimental points, is considered to be very satisfactory , bein3 of
the same order as was obtained in nep. 114.
III. ~erinental Reaul·ta and Discussiono
1) Tests over complete ran~e of a~~les cf o Fir,. 2.
In order to be sure tho. t t he vo.ri ous fair in.gs had !lO important
effects at attitudes other than that for high speed, a f'cw check points
were ta:cen with most o:f' the confie;urations over a considerable ranse of
angles. The :results,. :plotted in J'i.r.;. 2, indicate that the var iations
caused no appreciable effects exce-pt for those connected ·uith CDp.
2) Effects on parani te· drag in the high Sl)eed region.
All of the experimental points are plotted ·toc;eth er nith
faired curves in Fir,. 3. The values of C are Given in Table l
along \71 th dias ram.s illustrating the various modifications. It appears
that the optimum configuration is that corresponding to lOf. Assuming
the high speed attitude to occur at CL : o.15 then the parasite drns for
101" ts about 3% lo\7er ·than that for 10. This ~ould correspond to un
· increase in V. . of about l~; or approximately 2 miles per hour. max
Hence the conclusion to be drai'm from the present tests is
that by a proper -fairing behind the racliator, the hi.~h speed of the Y0-310
could be increased by ::i.bout 2 m.p.h. 'rhe proper fa.ir:inr_; would in addition
increase the depth of the fuselage at the coclcpits very materially. The
question of adequate cooling wns, of course, not considered in this in-vestigation,
but t he slot, ·tr..i•ou:;h which the air leaves t he radiator
GALC/T-REP 117 PA6£ .5
GAL CIT REPORT 117
TO STATIC RINGS
IN ENTRANCE AND
TO SELSYN GENERATOR
SIX COMPONENT SETUP FOR TEN FOOT WIND TUNNEL TESTS
AT GUGGENHEIM AERONATICS LABORATORY
CALIFORNIA INSTITUTE OF TECHNOLOGY
OWG. WT 2.6
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