Jet effects on pressure loading of all-movable horizontal stabilizer Page: 5 of 28
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to UNT Digital Library by the UNT Libraries Government Documents Department.
Extracted Text
The following text was automatically extracted from the image on this page using optical character recognition software:
4-NPID AL NACA RM E5424
RESULTS AND DISCUSSION
The discussion herein pertains only to the results obtained from
configurations with 3-percent secondary-flow ratio at free-stream Mach
number of 1.5, inasmuch as similar results were obtained at Mach
numbers 0.63 and 1.8. The chordwise pressure coefficients of the
stabilizer at Mach numbers of 0.63 and 1.8 for the range of jet
pressure ratios investigated are presented in table I.
The chordwise pressure distributions of the stabilizers at the
jet-off condition and at the jet pressure ratio Pi/P0 of 9 are V
presented in figure 6. Since the tubing of the static orifices at
chord stations 4.65 and 14.8 of tail station 4.50 leaked, only the
jet-off data points are plotted at tail station 4.50. The distribu-
tions at jet pressure ratios of 1, 4, and 6 exhibit the same trends
as do those at pressure ratio of 9 and were, therefore, not included
in the figures. The data presented in figure 6 indicate that the
influence of the jet on the pressure loading of the stabilizers is not
appreciable. At stabilizer deflection angle of 00 (fig. 6(a)), the
jet effect was felt spanwise to tail station 4.50. Increasing the
deflection angle resulted in a spanwise spreading of the jet effect;
with the stabilizer deflected 50 (fig. 6(b)), the pressures to tail
station 5.50 were influenced; while at 100 deflection angle (fig.
6(c)), the jet affected the distribution of the stabilizer to tail
station 7.09 (suction side only at tail station 7.09). For each of
these configurations, however, the jet effects were confined within
the region bounded by the 65- and 100-percent-chord stations.
Moving the stabilizer to the fore position (fig. 6(d)) reduced
the jet effects. With a deflection angle of 100, the jet effect was
limited spanwise to tail station 4.50 and chordwise between the 70-
and 100-percent-chord stations, on the suction side of the stabilizer
only.
The effect of the stabilizer on the boattail pressure distri-
bution is presented in figure 7. For zero deflection angle, the
boattail pressures on both sides of the stabilizer were nearly equal.
As would be expected, increasing the deflection angle resulted in a
decrease in pressure near the suction side and an increase near the
pressure side of the stabilizer. At pressure ratios of 6 and 9, flow
separation on the boattail was experienced with the configurations
with the body alone and with the stabilizer deflected 00. As the
deflection angle was increased, only the flow passing by the suction
side of the stabilizer was separated.
The effect of the stabilizer on the base annulus pressure
coefficients is presented in figure 8. The annulus pressure
a.~F
Upcoming Pages
Here’s what’s next.
Search Inside
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Valerino, Alfred S. Jet effects on pressure loading of all-movable horizontal stabilizer, report, June 10, 1954; (https://digital.library.unt.edu/ark:/67531/metadc60705/m1/5/: accessed April 30, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.