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Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Osculating Inward turning Cone Waverider/Inlet (OICWI) Design
Analysis and Experimental Study
1) Air-breathing Hypersonic Research Center CARDC Mianyang China 621000
2) Science and Technology on Scramjet Laboratory Hypervelocity Aerodynamics Institute CARDC Mianyang China 621000
Wu Yingchuan; He Xuzhao; Le Jialing
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Contents
Introduction Basic inward turning cone flow field design
and analysis Design methods for Osculating Inward
turning Cone Waverider forebody Inlet Numerical analysis of the integrated OICWI’s
performance Experimental study for the integrated OICWI Conclusion
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
• Waverider has high lift to drag ratio, it is suitable to be air-breathing Hypersonic vehicle’s forebody or body.
• In engineering practice, several kinds of air breathing vehicles are using or partially using integrated wave rider forebody/inlet design methods
Japhar X-51A Blackswift
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
• In present paper, an waverider inlet integration design methods are put forward which is basing on osculation axisymmetric and stream line tracing theory. This design method is called Osculating Inward truing Cone Waverider Inlet design method. This method is conformed and verified by comparison of the OICWI’s design results and inviscid on design condition results. The viscous results on design condition and on off design conditions are also presented in this paper. The wind tunnel experimental studies on design and on off design condition are conducted which is Mach number 5,6, 7 and angel of attach -2,0,2,4,6 degree.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
2. Basic inward turning cone flow field design and analysis
Fig1. Basic inward turning cone flow field structure
JB
Axisymmetric Axis
Center Body G
E'
H
F
O O'
Cowl Wall
Shock Cancel Region
I
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig2. Inward turning cone Mach number contour by MOC design
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig.3 Inward turnin cone flow field pressure contour comparison between MOC and CFD
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
X/Rs
P/P
0 0.5 1 1.5 2 2.5 30
2
4
6
8
10
12
14
CFD CenterbodyMOC CenterbodyMOC CowlCFD Cowl
8
Fig.4 Center body and cowl wall presure comparison between MOC and CFD results
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
3. Design methods for Osculating Inward turning Cone Waverider forebody
Inlet(OICWI)
The design method of integrated OIC waverider forebody inlet is developed from Osculating Inward turning Cone method. Combining Osculating axisymmetric method and streamline tracing technical, the OICWI design method uses OIC method and streamline tracing method to integrated waverider forebody inlet design. In the design procedure of OICWI, it has not geometrical modification and geometrical shape changing process.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig.5 Osculating methods sketch map in the OICWI cowl lip plane
ICC
FCT
A
B
C
D
E E′
D′
C′
B′
A′
Inlet Capture Area
(BB′CC′)
1. firstly we define inlet cone leading edge shock curve(Inlet Capture Curve) ICC.
2. The forebody inlet’s leading edge(front capture ratio FCT) use straight line add parabolic curve to generate.
3. Along the ICC curve, the ICC curve’s curve center is generated. For example, in the point B of ICC curve, the corresponding curve center A is generated. The point B in ICC curve and the curve center A generate the osculating plane AB.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
B
Axisymmetric Axis
Center Body G
E
F
O O'
Cowl Wall
Streamline
A
E
D D
CX/Rs 100
Y/Rs100
100 200 300
50
100
150
200
250
300
350
X
X
Fig.6 OICWI streamline tracing methods in the Oculating plane AB
In the actual design, only a part of ICC curve(section BB′) act as inlet capture section, the corresponding inlet cowl leading edge capture area is BB′CC′. the inlet side wall surface is constructed by the corresponding osculating
plane. In fig5, they are BC and B′C′ line.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
• Fig7 is an integrated OICWI which is designed by above described design method. The integrated waverider forebody inlet has a width of 0.3 meter. The waverider forebody’s length is 0.33 meter, and total length up to isolate exit plane is 0.68 meter. The inlet capture flow path width is 0.14 meter. The total compression ratio of this integrated OICWI is 4.47 and the inner compression ratio is 1.85.
Fig.7 3D view map o the designed OICWI
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
4. Numerical analysis of the integrated OICWI’s performance
The inviscid and viscous performance of the designed OICWI is simulated on design condition. The comparison is given for the inviscid numerical simulating result and the design result. For the design condition, the free stream flow is Mach number 6, to simulate the 25Km high atmosphere condition. The numerical simulation is using CFD software AHL3D, the inviscid flux construction method is third order MUSCL interpolation AUSMPW+ scheme. The turbulence model use two equation k-w TNT, using the wall function method to improve the simulation result accuracy. Total computational grid number is about 2 million.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig.9 Viscous Mach number and pressure contour in ICWI’s symmetry plane
Fig.8 Inviscid Mach number and pressure contour in OICWI’s symmetry plane
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
13.9
15.0 14.7
14.5
14.2
10.3
10.0
10.310.5
10.313.8
3.803.803.422.63
Z(m)
Y(m
)
-0.05 0 0.050.1
0.15
0.2
Flow field comparison in waverider-inlet exit plane
viscous P/P
viscous Mach number inviscid Mach number
inviscid P/P 88
Fig.10 Viscous and inviscid Mach number contour comparison in inlet cowl lip plane
Fig.11 viscous and inviscid Mach number and Pressure comparison in isolate exit
plane
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig.12 3D view of integrated OICWI inviscid flow field structure
Fig.13 3D view of integrated OICWI viscous flow field structure
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Table1 comparison of theory, inviscid and viscous result of OICWI’ on design condition
Table 1 is the Mach number, total pressure recovery, pressure rise ratio and mass flux capture ratio of theoretical design, inviscid simulation and viscid simulation results for the integrated waverider forebody inlet’s isolate exit plane. It shows that the theoretical design results and inviscid simulation results are fit with each other very well. For the OICWI’s flow field structure, the inviscid simulation and theoretical design results fit with each other well too. From those two points, we can see that present OICWI design method is correct.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
5. Experimental study for the integrated OICWI
The experiment study is fulfilled in China aerodynamic research and development center’s 0.5m hypersonic wind tunnel. The experiment section has radios of 0.5m. Experimental mach number range is 4.9~11.7. The accuracy of the Mach number is 0.005. The simulation height range of this wind tunnel is 20km~48km.
CARDC Hypersonic wind tunnel
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig14. the experimental study model of integrated waverider forebody inlet
Fig15 the unstart map for OICWI symmetry plane under 106 back pressure
ratios and free stream Mach number 5
Fig16. the self start map for OICWI symmetry plane when high pack pressure vanished
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig 18. the wind tunnel experimental model for integratd OICWI
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Ma5 AOA 4 Ma5 AOA 2
Ma5 AOA 0 Ma5 AOA -2
Fig19 flow field shadow graph map at free stream mach number 4.95, total pressure 0.74Mpa , total temperature 363K,AOA from 4 to -4 degree.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig20 flow field shadow graph map at free stream mach number 5.96, total pressure 1.44Mpa , total temperature 475K,AOA from 4 degree to -4 degree.
Ma6 AOA 4 Ma6 AOA 2
Ma6 AOA 0 Ma6 AOA -2
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig21 flow field shadow graph map at free stream mach number 6.97, total pressure 3.02Mpa , total temperature 602K,AOA from 4 to -4 degree.
Ma7 AOA 4 Ma7 AOA 2
Ma7 AOA 0 Ma7 AOA -2
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
From the experimental shadow graph picture, the integrated OICWI can start smoothly from Mach number 5 to Mach number7, from AOA 4 degree to -4 degree. In the waverider forebody inlet’s flow field, there are 2 main shock waves. The first shock wave is the forebody compression shock wave, the second shock wave is the inlet cowl reflect shock wave. Those two shock waves have obviously three dimensional characteristics. In the Mach number 5 to Mach number 7 conditions, the shadow graphs show that the leading edge shock is very close to the inlet cowl leading edge. Those phenomena mean that OICWI has high mass flow capture ability and small mass flow spillage under non design conditions.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig22. Body side symmetry plane CFD and experimental pressure distribution comparison at
flow condition Mach number 5.96, AOA0 degree.
Fig 23 cowl side symmetry plane CFD and experimental pressure distribution comparison at
flow condition Mach number 5.96, AOA0 degree.
X(mm)
P/P
-600 -400 -200 02
12
22
32
42
CFD pressureEXP pressure
8
symmetry body wall
symmetry cowl wall
X(mm)
P/P
-600 -400 -200 02
12
22
32
42
CFD pressureEXP pressure
8
symmetry body wall
symmetry cowl wall
The computation and experiment comparison studies are conduction under Mach number 5.96, total pressure P0=1.44Mpa, total temperature T0=475K, AOA=0 degree condition.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig24. width direction(from forebody leading edge ) pressure distribution comparison
between CFD and experimental data at mach number 5.96 AOA0.
Fig25 3D view of OICWI experimental model flow field structure at mach number 5.96 AOA0.
Z(mm)
P/P
-60 -40 -20 0 20 40 60
2
4
6
8
10
CFD pressureEXP pressure
8
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Fig 26 isolate exit mach number andpressure contour at Mach number 5.96, 0 angle of attack.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
6. Conclusion An waverider forebody inlet integrated design method:
Osculating Inward turning Cone Waverider Inlet (OICWI) design methods are presented in present paper. The numerical and experimental studies are conducted for this kind of integrated waverider forebody inlet on design and off design conditions. From present studies, it shows that OICWI has some good characteristics such as:
1. The design methods for OICWI using streamline tracing and osculating inward cone technical, the design processes are according with aerodynamic principles.
2. The OICWI’s shape, inner compression ratio and isolate exit flow parameter can be easily adjusted through ICC and FCT curve, the design of an OICWI is flexible and easily.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
3. From the comparison of inviscid simulation results on design condition and OICWI’s design results, they compare with each other well and the consistent results show that present OICWI design method is correct.
4. From the simulation and experimental studies result on design and off design conditions, it shows that OICWI has high pressure recovery, good flow parameter uniformity and good flow capture characteristics. It has small flow spillage in three dimensional design and off design conditions.
5. The experimental studies are performed in present studies, the experimental study results have good consistency with numerical simulation results, experimental and numerical simulation result are compared with each other well.
Airbreathing Hypersonics Laboratory
China Aerodynamics Research and Development Center
Thank you for your attention!