additional comments: Delta wings can produce high lift at high angle of attack, HOWEVER: You need a LOT of thrust to keep it up in the air. Drag is WAY higher than on traditional planforms when you go to high angles of attack. The lading edge angle should make sure that he wing is within the mach cone of the shockwave generated at the fuselage/wing junction.
Good points, especially about the shock wave angle. This angle also changes with speed. So the faster you go, the sharper the leading edge should be swept. It also reminds be of the F-14 tomcat, with it's movable wings. That was pretty cool.
Mainly because they aren't swept back enough, but also because they usually don't have sharp enough leading edges. As such, the flow just separates and doesn't roll up coherently into a vortex.
Follow up question regarding lift distribution, your example is at the back of the wing, but if you were to move that cross section towards the cockpit, would the high points of that distribution follow that low pressure vortex?
![[Aero Fundamentals #44] Whitcomb Area Rule](http://i.ytimg.com/vi/kAIzya4RbVQ/mqdefault.jpg)
![[Aero Fundamentals #44] Whitcomb Area Rule](/img/tr.png)
additional comments:
Delta wings can produce high lift at high angle of attack, HOWEVER: You need a LOT of thrust to keep it up in the air. Drag is WAY higher than on traditional planforms when you go to high angles of attack.
The lading edge angle should make sure that he wing is within the mach cone of the shockwave generated at the fuselage/wing junction.
Good points, especially about the shock wave angle. This angle also changes with speed. So the faster you go, the sharper the leading edge should be swept.
It also reminds be of the F-14 tomcat, with it's movable wings. That was pretty cool.
Please can you show us how to intergrate the area under curve to find the lift 🙏
Sure!
@@PremierAerodynamics thanks mate!
So the air flow splits apart and creates a vortex. What is a vortex I'm having trouble understanding.
Rotating air
In this video, we go through the mathematics of it: ua-cam.com/video/zInIjWOXoRw/v-deo.html
Hopefully it helps.
Why doesn't that vortex form over traditional wings at high AOA?
Mainly because they aren't swept back enough, but also because they usually don't have sharp enough leading edges.
As such, the flow just separates and doesn't roll up coherently into a vortex.
@@PremierAerodynamicsIdk why I didn't get a notification for this! Thank you so much for the response! I adore your channel!
Follow up question regarding lift distribution, your example is at the back of the wing, but if you were to move that cross section towards the cockpit, would the high points of that distribution follow that low pressure vortex?