Investigations on the Downwash Behind a Tapered Wing With Fuselage and Propeller Page: 16 of 52
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N.A..A. Technical Memorandum No. 876
rectangular wing has already been pointed out. The lateral
axis -h = -02 at- a.= 6.8o, lies, as seen from figure 8,
exactly at height of the maximum downwaah values. Thus
this lateral axis curve is comparable with a theoretical
curve for nonrolled-up vortex sheet, because the lateral
axis lies in the vortex sheet. The mathematical expression
for it reads
w TJ 1 ( - Jq ..C
+ + --d
( qa (( + cq) a (
This expression also was evaluated grapliicallt.
Figure 5 shows - apart from the parallel displacement -
the good agreement, thus proving anew that the lateral vor-
tes.motion during the rolling-up process playe-no essential
bt) Low-Wing Model with Ideal Fuselage
First we discuss the downwash on the "low wing with
ideal fuselage," because the ideal fuselage influences the
flow bf the "wing alone" very little only, whence this ar-
rangement with propeller ruining may, within a restricted
angle of attack range, equally be termed "wing with propel-
ler runn7.ng," expecially if reflecting that the propeller
axis lies above the wing.
Sa = D1 q.. Figure 23 shows the results of eight lat-
eral-axes at diestence et = 1.0 for a = 3.150. This an-
gle a = 3.150 is distinguished by the fact that the pro-
peller axis.and the-undisturbed flow direction are exactly
coincident, that is, subject to a certain yaw only as a re-
sult of the upflow before the wing; The-coefficient of ad-
vance is A-= 0.2. It also' is
S c = - -- 0.34-
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Muttray, H. Investigations on the Downwash Behind a Tapered Wing With Fuselage and Propeller, report, September 1938; (https://digital.library.unt.edu/ark:/67531/metadc63295/m1/16/: accessed April 23, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.