UWE Bristol Engineering showcase 2015

SUMIT SUNIL WATHORE
BEng (Hons) AEROSPACE ENGINEERING (MANUFACTURING)
Project Supervisor
Dr. Abdessalem Bouferrouk
University of the West of England, Bristol
WAVE DRAG REDUCTION FOR HIGH SPEED FLIGHT
Investigating 3D Rounded Shock Control Bump to Reduce Wave Drag on Transonic and Supersonic Aerofoil.
In the era of everything is accelerating, aircrafts are actually flying at the slower speed than they use to do. Commercial air travel has not gotten any faster
since 1960s, (Hoagland K., MIT 2014). Main reason is the fuel economy going faster cost more fuel per mile it is all about drag factor and can be overcome with
effective drag reduction technology. With drag reduction just not only it will increase fuel economy but also the operation range of an aircraft. Very few
attempt on 2D and 3D shock control bumps (SCBs) have been investigated on transonic aero foil and none on the Supersonic aero foil. Though research has
been carried at leading aerospace industries but still there not much information available on internet for performance of the SCBs on supersonic aero foil,
fixed SCBs is cost effective and simple method to reduce wave drag and get maximum performance for high speed flights.
Project summary
Computational simulation to investigate the
performance and the effectiveness of 3D rounded
shock control bumps on transonic and supersonic
aerofoil was undertaken; two chord wise variables for
the shock control bumps were varied in conjunction
with tangentially bump height, and chord wise
location. The primary aim of dissertation to reduce
wave drag is successfully achieved.
what is drag ?
Profile Drag – Profile drag produce due to friction and turbulence in the
viscous fluid.
Induced Drag – induced drag occurs due to the lift development in the
aircraft.
Wave drag – wave drag is produce due to the formation of shock waves in
supersonic and transonic flight.
Limitations – in this research only
one SCBs buffet is used to
concentrate on its performance and
the angle of SCBs buffet are
changed to see the performance,
this limits the investigation on the
sets of design SCBs on the aerofoil.
LIFT TO DRAG RATIO
9
8.087
8
7
6
5
4
3
2
1
0
8.36
L/D VS HEIGHT OF THE BUMP
The dissertation carried out with limited resources and
on the 3D aerofoil with finite span
To be tested in the supersonic wind tunnel to verify its
effectiveness experimentally and then more modification
is to be done .Few tests for hypersonic speed shows
diverse results, more work with hypersonic aerofoil with
SCBs is must Rounded SCBs at various locations and
different design pattern should be tested.
8.38
8
0 0.5 1 1.5 2 2.5 3 3.5
7.54
HEIGHT OF THE SCB
6.44
% of drag decrease
Shock wave can be defined as sharp
change of pressure in narrow region
when travelling through a medium
(here air for an aircraft) due to high
speed.
When aircraft travel in low speed less
than 0.8 Mach the air ahead of an
aircraft get separated from its path.
60
50
40
30
20
10
0
-10 -5
-10
0 5 10 15 20
-20
-30
-40
NACA 66-206 at 4*10^5
AOA
NACA 66-206
at 4*10^5
Project Objectives
1) Investigation of SCBs performance on the transonic
and supersonic wing. Main focus on the supersonic
flights, and selecting the rounded SCBs location and
height of bump.
2) Reduction of wave drag using rounded bump
3) Aircraft design optimization for best possible
configuration to get maximum speed of much beyond
the conventional aircrafts.
4) To look into the
Potential benefits of using rounded bumps on
different sections of aircraft to control flow over and
reduced total drag.
Project Conclusion
Rounded shock control bumps are more effective on
supersonic aerofoil than transonic because the
reduction in shock strength in supersonic shock is
greater. The SCBs are effective for reducing wave drag
in supersonic flight but the drag on transonic flight is
not much affected by the shock wave.
Simulation Model has been validated using the
published experimental results obtained for DFVLR-
R4.
The results demonstrated that an active contour
bump, which could change height and move to follow
the shock wave, would likely be required for
application on an aircraft