Rafale Optimisation: ElementAir mon cher Watson!!!
Rafale optimisation is not a vain word or empty commercial argument.
The aircraft aerodynamic is way more developed than that of the previous design, the Rafale A.
After Rafale A flew first on 4th July 1986, it served its purpose as demonstrator, validating the close-coupled delta-canard formula.
In particular, it meet all of ACX requierements for high maneuvrability and STOL performances, climb rate, sustain dash speed etc.
The proposed Navalised version, ACM was to meet more stringuent requierement from Marine Nationale after a Carrier trial period:
Increased sink rate with a 16* AoA and better downward visibility than the A were among MN demands after Carrier trials.
Design have to evoluate further and Dassault designers didn't do things half-way.
http://img123.imageshack.us/img123/8366/rafalesaserieprofilesuppp0.jpg
The A wings were similar to that of the Mirage IIING, a crancked delta plan which allowed the A to sustain M 2.0 and provided with good qualities at high AoA.
http://img260.imageshack.us/img260/6696/awingplanjg3.jpg
In some instances (as in the case for the EAP), this wingplan can lead to assymetric dispacement of Cl at supersonic speed, the center of lift of the two parts of the wings moving back backward at a different rate. (It depends on wingsweep).
There were also gains to be made by repositioning the wings from low-shoulder to mid-fuelage and this unlocked several other design options starting with a reduction in wave drag:
http://img171.imageshack.us/img171/3229/hybridgs9.jpg
1) This allowed the designers to give the aircraft a sharply sweept LEX which not only gives an increae in lift but also is shaped for supersonic performances.
2) The surfaces of the canard was increeased by 30* and their root shaped so that they can deflect fully at 30* and increase the effect of the deflected airflow above the wing.
3) The LEX leading edge were designed sharper with a tri-dimentional shape, a constant sweept and progressive adrenal.
http://img379.imageshack.us/img379/2929/arrangementdevelopefk0.jpg
The LEX are rooted at the point where the inlets diffuser shock hits the inlet leading edge, and beneficiate from the same weaker shock wave which triggers their own while minimising its intensity.
http://img124.imageshack.us/img124/1733/vortexesdp1.jpg
At lower speeds they provoc several vortexes, one of which is clearly visible here, resulting on a significant increase in lift.
4) There was a marqued increase in wing-fuselage junction volume too, with a more blended shape which reduces wave drag and increases internal fuel volume.
Accessorly this feature is also reducing the aircraft RCS.
http://img69.imageshack.us/img69/5038/c01hybridkn3.jpg
While this would have been more than enough for most design houses, it wasn't so for the Dassault aerodynamicians.
During the Mirage 4000 flight-tests, they notices that the nose cone and front fuselage could be used to accomodate better pressure control and increase overal aerodynamic efficiency around the inlets.
http://img46.imageshack.us/img46/6490/acfareafronths5.jpg
This resulted in the characteristic V-shaped fron fuselage and inlet arrangement which optimises the airflow in front of the diffusers.
http://img296.imageshack.us/img296/1358/05rafaleb3011dn2.jpg
http://img47.imageshack.us/img47/9974/rafrontbe7.gif
This arrangement allows for a higher supersonic performances and a less complex inlet design.
But AGAIN this wasn't enough for Dassault, when they were given the word "OPTIMISEZ"!!!
Using their experience on the Mirage series they developed the conceipt of pressure and wave control even further:
Using the principes of compressive and expensive waves they channeled the boundary layer to the exact point where they wanted these phenomenons to occur: At the limit of the wing root.
There are sdeveral advantages in doing so:
First they do away with the Mirage 2000 strakes, as they are notably unstealthy and offers less control over the boundary layer.
These are normaly rooted at shoulder-level and dynamises the airflow around the fin at high AoA offering increased Yaw stability.
In the case of Rafale, by shaping the inlets in a V, they made it possible to energise BOTH that of the wing at its root and the fin's simultaneously, retain a sleek aircaft and low RCS.
http://img183.imageshack.us/img183/5148/intakeleftarrangementnh9.jpg
These shock takes place from the transonic regime, at point A where the airflow is separated, (part of it recycled by the engine IR-suppressant channel).
The shock created there is of the compressive type, and results on an increase in temperature, pressure and density, the airflow velocity becoming lower which means higher energy.
From point D and E, where it matters most, this same airflow is submited to another Shockwave, this time of the Expensive type.
http://img252.imageshack.us/img252/6682/condiii1.jpg
A new Mach line is created, resulting on lower pressures, density, temperature but a higher velocity which energises the airflow coming from the canard surfaces and the rest of the airframe.
This particular feature works so WELL thats its effects can even be seen when the aircraft is stationary due to paint tear and wear.
http://img441.imageshack.us/img441/1521/vortexeffectsairframeoq6.jpg
So to finish, the Supersonic optimisation of the wing.
Many tends to think that a 50*+ sweept angle would allow for better "performances".
Well it's true and untrue at the same time, the wing of a Mirage 2000 will drag more and have a lower lift coefficient at higher AoA.
There are advantages for higher sweept wings, higher Critical Mach is one but you need an accordingly overal reduced drag wave to take advantage of this.
For example: Mid-fuselage mounted wings and well blended fuselage wings areas, Rafale have this too...
Lower mid-to-high supersonic drag is another but this can be CONTROLED with different design features.
http://img47.imageshack.us/img47/3638/chocsli8.jpg
This is a composite image from different sources. One being NASA.
It shows the use of their little gizmo called ShockModeler and when applied to an aircraft design can bring a FEW surprises.
In the case of Rafale it appears that the designers have managed a "tour de force":
They combined the effect of both the LEX and wings shockwaves in a way that it reduces its supersonic drag where the moderate 48* sweep angle would be the most needing it = Above M 1.65.
As shown in this image, the shock wave from the LEX creates a second zone (2 in purple) ahead of the wing leading edge.
Schock_M1.674.jpg. http://img127.imageshack.us/img127/8346/schockm1674eg9.jpg
This appears from <> M 1.655 and doesn't change from M 1.8 (as shown here) to speed well in eccess of M 2.0.
Schock_M2.0.jpg. http://img171.imageshack.us/img171/7184/schockm20eq1.jpg
Before that due to their combination BOTH LEX and WING shockwaves are perpendicalar to the relative wing and are called "NORMAL".
This compresses the whole design transonic zone, and reduces its transonic and supersonic drag further = increased optimisation.
The SMART bit is that the combination of the TWO waves are hitting the JUNCTION between the LEX and the wing (Hence the LEX particular frontal design) parralel to the ambiant air from <> M 1.674, where supersonic drag gets higher.
http://img379.imageshack.us/img379/2929/arrangementdevelopefk0.jpg
This results on the creation of two other zones, one (zone 3) adopting the characteristics of the free airflow, the fourth resulting from a NEW and weaker shockwave (Expension) created by its interection with the previous.
The limit between the zones 3 and 4 is called Slip Surface and is parralel to the wing leading edge.
This artificially incereased the high mach characteristics of the main wing by lowering the pressures while increasing the airflow velocity in front of the leading edge and reducing the shock intensities... = Expansion wave AGAIN.
As a result, the LEX can bedesigned with a much higher sweep angle which if it reduces their surface doesn't result on a lower increase in LIFT, particularly so at higher Mach.
When was the last time someone asked WHY would Rafale have a higher payload and 250 nm better range with 3 X 2.000 L than a F-35 CLEAN while flying at a similar cruising speed?
Apparently, when some are buzy screwing their weight targets while CATIA, at Dassault they're buzy doing the best job an aerodynamicist can do with it and then some...
I think it's time to stop claiming superiority for somne designs which feature only (and comparatively) caterpilar-like aerodynamics.
Chapeau messieurs!!! http://img46.imageshack.us/img46/96/asterix01bu8.gif
"In Rafale the angle of attack is 16° but it can fly easily at 30° . Deck landings in the past were very stressful for the pilot. Now [in the Rafale] they are easy."
http://img402.imageshack.us/img402/6469/0630190ve9.jpg
Chief test pilot Yves Kerherve.
Enjoy.
Rafale optimisation is not a vain word or empty commercial argument.
The aircraft aerodynamic is way more developed than that of the previous design, the Rafale A.
After Rafale A flew first on 4th July 1986, it served its purpose as demonstrator, validating the close-coupled delta-canard formula.
In particular, it meet all of ACX requierements for high maneuvrability and STOL performances, climb rate, sustain dash speed etc.
The proposed Navalised version, ACM was to meet more stringuent requierement from Marine Nationale after a Carrier trial period:
Increased sink rate with a 16* AoA and better downward visibility than the A were among MN demands after Carrier trials.
Design have to evoluate further and Dassault designers didn't do things half-way.
http://img123.imageshack.us/img123/8366/rafalesaserieprofilesuppp0.jpg
The A wings were similar to that of the Mirage IIING, a crancked delta plan which allowed the A to sustain M 2.0 and provided with good qualities at high AoA.
http://img260.imageshack.us/img260/6696/awingplanjg3.jpg
In some instances (as in the case for the EAP), this wingplan can lead to assymetric dispacement of Cl at supersonic speed, the center of lift of the two parts of the wings moving back backward at a different rate. (It depends on wingsweep).
There were also gains to be made by repositioning the wings from low-shoulder to mid-fuelage and this unlocked several other design options starting with a reduction in wave drag:
http://img171.imageshack.us/img171/3229/hybridgs9.jpg
1) This allowed the designers to give the aircraft a sharply sweept LEX which not only gives an increae in lift but also is shaped for supersonic performances.
2) The surfaces of the canard was increeased by 30* and their root shaped so that they can deflect fully at 30* and increase the effect of the deflected airflow above the wing.
3) The LEX leading edge were designed sharper with a tri-dimentional shape, a constant sweept and progressive adrenal.
http://img379.imageshack.us/img379/2929/arrangementdevelopefk0.jpg
The LEX are rooted at the point where the inlets diffuser shock hits the inlet leading edge, and beneficiate from the same weaker shock wave which triggers their own while minimising its intensity.
http://img124.imageshack.us/img124/1733/vortexesdp1.jpg
At lower speeds they provoc several vortexes, one of which is clearly visible here, resulting on a significant increase in lift.
4) There was a marqued increase in wing-fuselage junction volume too, with a more blended shape which reduces wave drag and increases internal fuel volume.
Accessorly this feature is also reducing the aircraft RCS.
http://img69.imageshack.us/img69/5038/c01hybridkn3.jpg
While this would have been more than enough for most design houses, it wasn't so for the Dassault aerodynamicians.
During the Mirage 4000 flight-tests, they notices that the nose cone and front fuselage could be used to accomodate better pressure control and increase overal aerodynamic efficiency around the inlets.
http://img46.imageshack.us/img46/6490/acfareafronths5.jpg
This resulted in the characteristic V-shaped fron fuselage and inlet arrangement which optimises the airflow in front of the diffusers.
http://img296.imageshack.us/img296/1358/05rafaleb3011dn2.jpg
http://img47.imageshack.us/img47/9974/rafrontbe7.gif
This arrangement allows for a higher supersonic performances and a less complex inlet design.
But AGAIN this wasn't enough for Dassault, when they were given the word "OPTIMISEZ"!!!
Using their experience on the Mirage series they developed the conceipt of pressure and wave control even further:
Using the principes of compressive and expensive waves they channeled the boundary layer to the exact point where they wanted these phenomenons to occur: At the limit of the wing root.
There are sdeveral advantages in doing so:
First they do away with the Mirage 2000 strakes, as they are notably unstealthy and offers less control over the boundary layer.
These are normaly rooted at shoulder-level and dynamises the airflow around the fin at high AoA offering increased Yaw stability.
In the case of Rafale, by shaping the inlets in a V, they made it possible to energise BOTH that of the wing at its root and the fin's simultaneously, retain a sleek aircaft and low RCS.
http://img183.imageshack.us/img183/5148/intakeleftarrangementnh9.jpg
These shock takes place from the transonic regime, at point A where the airflow is separated, (part of it recycled by the engine IR-suppressant channel).
The shock created there is of the compressive type, and results on an increase in temperature, pressure and density, the airflow velocity becoming lower which means higher energy.
From point D and E, where it matters most, this same airflow is submited to another Shockwave, this time of the Expensive type.
http://img252.imageshack.us/img252/6682/condiii1.jpg
A new Mach line is created, resulting on lower pressures, density, temperature but a higher velocity which energises the airflow coming from the canard surfaces and the rest of the airframe.
This particular feature works so WELL thats its effects can even be seen when the aircraft is stationary due to paint tear and wear.
http://img441.imageshack.us/img441/1521/vortexeffectsairframeoq6.jpg
So to finish, the Supersonic optimisation of the wing.
Many tends to think that a 50*+ sweept angle would allow for better "performances".
Well it's true and untrue at the same time, the wing of a Mirage 2000 will drag more and have a lower lift coefficient at higher AoA.
There are advantages for higher sweept wings, higher Critical Mach is one but you need an accordingly overal reduced drag wave to take advantage of this.
For example: Mid-fuselage mounted wings and well blended fuselage wings areas, Rafale have this too...
Lower mid-to-high supersonic drag is another but this can be CONTROLED with different design features.
http://img47.imageshack.us/img47/3638/chocsli8.jpg
This is a composite image from different sources. One being NASA.
It shows the use of their little gizmo called ShockModeler and when applied to an aircraft design can bring a FEW surprises.
In the case of Rafale it appears that the designers have managed a "tour de force":
They combined the effect of both the LEX and wings shockwaves in a way that it reduces its supersonic drag where the moderate 48* sweep angle would be the most needing it = Above M 1.65.
As shown in this image, the shock wave from the LEX creates a second zone (2 in purple) ahead of the wing leading edge.
Schock_M1.674.jpg. http://img127.imageshack.us/img127/8346/schockm1674eg9.jpg
This appears from <> M 1.655 and doesn't change from M 1.8 (as shown here) to speed well in eccess of M 2.0.
Schock_M2.0.jpg. http://img171.imageshack.us/img171/7184/schockm20eq1.jpg
Before that due to their combination BOTH LEX and WING shockwaves are perpendicalar to the relative wing and are called "NORMAL".
This compresses the whole design transonic zone, and reduces its transonic and supersonic drag further = increased optimisation.
The SMART bit is that the combination of the TWO waves are hitting the JUNCTION between the LEX and the wing (Hence the LEX particular frontal design) parralel to the ambiant air from <> M 1.674, where supersonic drag gets higher.
http://img379.imageshack.us/img379/2929/arrangementdevelopefk0.jpg
This results on the creation of two other zones, one (zone 3) adopting the characteristics of the free airflow, the fourth resulting from a NEW and weaker shockwave (Expension) created by its interection with the previous.
The limit between the zones 3 and 4 is called Slip Surface and is parralel to the wing leading edge.
This artificially incereased the high mach characteristics of the main wing by lowering the pressures while increasing the airflow velocity in front of the leading edge and reducing the shock intensities... = Expansion wave AGAIN.
As a result, the LEX can bedesigned with a much higher sweep angle which if it reduces their surface doesn't result on a lower increase in LIFT, particularly so at higher Mach.
When was the last time someone asked WHY would Rafale have a higher payload and 250 nm better range with 3 X 2.000 L than a F-35 CLEAN while flying at a similar cruising speed?
Apparently, when some are buzy screwing their weight targets while CATIA, at Dassault they're buzy doing the best job an aerodynamicist can do with it and then some...
I think it's time to stop claiming superiority for somne designs which feature only (and comparatively) caterpilar-like aerodynamics.
Chapeau messieurs!!! http://img46.imageshack.us/img46/96/asterix01bu8.gif
"In Rafale the angle of attack is 16° but it can fly easily at 30° . Deck landings in the past were very stressful for the pilot. Now [in the Rafale] they are easy."
http://img402.imageshack.us/img402/6469/0630190ve9.jpg
Chief test pilot Yves Kerherve.
Enjoy.
Last edited: