2d flow applications - virginia techdevenpor/aoe3114/15 - 2d flow...shock interactions 2. engine...
TRANSCRIPT
![Page 1: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/1.jpg)
2D Flow Applications2D Flow Applications
1. Shock Interactions
2. Engine Intakes2. Engine Intakes
3. Supersonic Jets
![Page 2: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/2.jpg)
1. Shock fl
βB1
3
βCReflection
δ=12oβA
23
M1 =6
Find M2, M3, p2/p1, p3/p1δ=12oβA
TABLES
![Page 3: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/3.jpg)
βBM1 =6
M3 =3.41
1
2
3
1
βC
δ=12oβA δ 12βA
More Reflections?More Reflections?
TABLES
![Page 4: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/4.jpg)
1b. Shock βB
3
δB=5o
Intersection1
OPPOSITE FAMILIES
δ 12β
1
2M1 =3
δA=12oβA
![Page 5: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/5.jpg)
1b. Shock βB
3
δB=5o
Intersection1
OPPOSITE FAMILIES
4
5
φ
δ 12β
1
2M1 =3
4
δA=12oβA
![Page 6: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/6.jpg)
1c. Shock Intersection
1
SAME FAMILY
ββB
1
2
3
M1 =3 δB=6o
δ 12βA δA=12o
![Page 7: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/7.jpg)
2. Supersonic Engine Intakes2. Supersonic Engine Intakes
• Designed toDesigned to– Compress the flow– Decelerate it to subsonic speed
– Minimum p0 loss
• Most intakes are designed to direct the flow more than one shock wave
![Page 8: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/8.jpg)
Why Multiple Shocks?Why Multiple Shocks?Consider deceleration of a Mach 2 flow to subsonic….
SINGLE NORMAL SHOCKSINGLE NORMAL SHOCK
M=2
OBLIQUE / NORMAL SHOCK COMBINATION
1 2
OBLIQUE / NORMAL SHOCK COMBINATION
M=2
1 2
3M 2
45o
![Page 9: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/9.jpg)
Two‐Dimensional InletTwo Dimensional Inlet
M∞M∞
![Page 10: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/10.jpg)
Wind‐Tunnel VisualizationMach number 1.95
history.nasa.gov/SP‐4302/ch2.12.htm
![Page 11: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/11.jpg)
Northrup F‐5
![Page 12: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/12.jpg)
F‐4 Phantom
![Page 13: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/13.jpg)
Concorde/ Olympus 563Concorde/ Olympus 563TAKE OFF
http://www.concordesst.com/powerplant.html
SUPERSONIC CRUISE
![Page 14: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/14.jpg)
Axisymmetric InletAxisymmetric Inlet
M∞ = MDESIGN
M∞ < MDESIGN
M∞ > MDESIGNDESIGN
![Page 15: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/15.jpg)
Mirage F1
![Page 16: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/16.jpg)
General Dynamics F‐111
![Page 17: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/17.jpg)
SR‐71
![Page 18: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/18.jpg)
SR‐71 InletSR 71 Inlet
![Page 19: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/19.jpg)
3. Supersonic Jets SATURN V ROCKET(APOLLO 15, 11, 11)
TAKEOFF 39 MILES ALTITUDETRANSONIC
![Page 20: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/20.jpg)
![Page 21: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/21.jpg)
XCOR 5M15 Liquid Methane/Oxygen Rocket EngineRocket Engine
http://www.xcor.com/
![Page 22: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/22.jpg)
2D Over‐Expanded JetREGULAR REFLECTION
E i M 1
pbAmbient
Exit Me>1p=pe>pb p=pb p>pb
p=pb
P i i d f i l h l b• Pressure is raised from pe to pb as it leaves the nozzle by an oblique shock.
• Shock also deflects flow down toward plane of symmetry.• Deflection can’t be sustained at symmetry plane so a 2nd
shock is formed to deflect the flow parallel to the symmetry plane once more.
• This also raises the pressure above pb• To bring the pressure back down to pb the shock as to
reflect from the jet edge as an expansion wave, but this j g p ,then deflects the flow away from the plane of symmetry.
![Page 23: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/23.jpg)
pb=0.2pcAmbientExampleMe=2pe=0.1278pc p=pb p>pb
p=pbFind pressures, Mach numbers and flow directions
1
2
3
4
![Page 24: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/24.jpg)
pb=0.2pcAmbientExampleMe=2pe=0.1278pc p=pb p>pb
p=pbFind pressures, Mach numbers and flow directions
1
2
3
4M2=1.702
M3=1.409p3=0.3pc
![Page 25: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/25.jpg)
2D Over Expanded JetMACH REFLECTION
E i M 1
pbAmbient
Exit Me>1p=pe>pb
p=pbp>pb
p=pb
• Occurs when the Mach number downstream of the 1stshock is too low for regular reflection (i e theshock is too low for regular reflection (i.e. the maximum turn angle for the second wave would be less than the deflection produced by the first.)B k i t th th t f l fl ti• Back pressure is greater than that for regular reflection, and less than that for a shock at the exit.
![Page 26: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/26.jpg)
pbAmbientExampleMe=2pe=0.1278pc p>pb
p=pbFind back pressure at which Mach reflection first appears
1
2
3
4p=pb
appears
TABLES
![Page 27: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/27.jpg)
Axisymmetric Over‐Expanded Jet
http://www.aerospaceweb.org/ Space Shuttle Main Engine
![Page 28: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/28.jpg)
2D Under‐Expanded JetpbAmbient
p=pbp=pb
Exit Me>1p=pe<pb
p=pb
P<pb
p=pb
• Pressure is reduced from pe to pb as it leaves the nozzle by an expansion wave centered on the nozzle lipW l d fl fl f h l f• Wave also deflects flow up away from the plane of symmetry.
• Deflection can’t be sustained at symmetry plane so a another expansion is formed to deflect the flow parallel to the symmetry plane once moreplane once more.
• This also lowers the pressure below pb• To bring the pressure back up to pb the expansion reflects from the
jet edge as an compression wave, but this then deflects the flowjet edge as an compression wave, but this then deflects the flow toward the plane of symmetry.
![Page 29: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/29.jpg)
ExampleAmbientpb=0.05pc
Exit Me=2pb=0.1278
p=pb
P<p
p=pbCompute angle and Mach number of flow after first turn
1
2
P<pb1
![Page 30: 2D Flow Applications - Virginia Techdevenpor/aoe3114/15 - 2D Flow...Shock Interactions 2. Engine Intakes 3. Supersonic Jets 1. Shock fl β B 1 3 β C Re ection βA δ=12o 2 3 M 1 =6](https://reader035.vdocuments.mx/reader035/viewer/2022071605/6142325155c1d11d1b3409dd/html5/thumbnails/30.jpg)
Axisymmetric Under‐Expanded Jet
http://www.aerospaceweb.org/
Kinki University, Japan