The swirl recovery vane (SRV) oriented in the slipstream of the propeller can in principle recover the swirl effect and thus would improve the propulsion performance in terms of thrust production and propulsive efficiency. The present study employs the design of experiments (DoEs) method to optimize the geometry of the specific SRV for Fokker 29 propeller for the sake of further enhancing the thrust generation and swirling recovery. First, orthogonal experiment was employed to identify the most significant factors, which directly influence the thrust production. Second, steepest ascent method was used to search the optimum range of target factors through climbing and factorial experiments. The resulting optimal solution was evaluated by the center composite experiment. Results show that the thrust generated by the SRV has been increased significantly (11.78%) after optimization at the design point, and a 0.66% increment in the total efficiency of the propeller–SRV system has been obtained. For the off-design point, an increment of the total efficiency (2.10%) can be observed at low rotating speed. Additionally, the optimized SRV is able to correct the out-flow behavior at the tip region of the vane, where the tip vortex and swirl kinetic energy loss is weaken, and the thrust distribution along the spanwise direction tends to be more uniform.

References

References
1.
Mitchell
,
G. A.
, and
Mikkelson
,
D. C.
,
1982
, “
Summary and Recent Results From the NASA Advanced High-Speed Propeller Research Program
,”
AIAA
Paper No. AIAA-82-1119.
2.
Jeracki
,
R. J.
,
Mikkelson
,
D. C.
, and
Blaha
,
B. J.
,
1979
, “Wind Tunnel Performance of Four Energy Efficient Propellers Designed for Mach 0.8 Cruise,”
SAE
Paper No. 790573.
3.
Thom
,
A.
, and
Duraisamy
,
K.
,
2013
, “
Computational Investigation of Unsteadiness in Propeller Wake-Wing Interactions
,”
J. Aircr.
,
50
(
3
), pp.
985
988
.
4.
Gray
,
W. H.
, and
Biermann
,
D.
,
1941
, “Wind-Tunnel Tests of Eight-Blade Single- and Dual-Rotating Propellers in the Traction Position,” NASA Langley Research Center, Hampton, VA, Report No.
NACA-WR-L-384
.https://ntrs.nasa.gov/search.jsp?R=19930093332
5.
Gazzaniga
,
J. A.
, and
Rose
,
G. E.
,
1992
, “Wind Tunnel Performance Results of Swirl Recovery Vanes as Tested With an Advanced High Speed Propeller,”
AIAA
Paper No. AIAA-92-3770.
6.
Wang
,
Y.
,
Li
,
Q.
,
Eitelberg
,
G.
,
Veldhuis
,
L. L. M.
, and
Kotsonis
,
M.
,
2014
, “
Design and Numerical Investigation of Swirl Recovery Vanes for the Fokker 29 Propeller
,”
Chin. J. Aeronaut.
,
27
(
5
), pp.
1128
1136
.
7.
Li
,
Q.
,
Wang
,
Y.
, and
Eitelberg
,
G.
,
2016
, “
An Investigation of Tip Vortices Unsteady Interaction for Fokker 29 Propeller With Swirl Recovery Vane
,”
Chin. J. Aeronaut.
,
29
(
1
), pp.
117
128
.
8.
Montgomery
,
D. C.
,
2008
,
Design and Analysis of Experiments
,
7th ed.
,
Wiley
,
New York
.
9.
Fisher
,
R. A.
,
1958
,
Statistical Methods for Research Workers
,
13th ed.
,
Oliver and Boyd
,
Edinburgh, UK
.
10.
Fisher
,
R. A.
,
1966
,
The Design of Experiments
,
8th ed.
,
Haffner Publishing
,
New York
.
11.
Box
,
G. E. P.
, and
Wilson
,
K. B.
,
1992
, “
On the Experimental Attainment of Optimum Conditions
,”
Breakthroughs in Statistics
, Springer, New York, pp. 270–310.
12.
Deng
,
S.
,
Percin
,
M.
,
van Oudheusden
,
B. W.
,
Bijl
,
H.
,
Remes
,
B.
, and
Xiao
,
T.
,
2017
, “
Numerical Simulation of a Flexible X-Wing Flapping-Wing Micro Air Vehicle
,”
AIAA J.
,
55
(
7
), pp.
2295
2306
.
You do not currently have access to this content.