Firstly, lets blow in a new age of enlightenment where only knowledge is useful. Facts, methodologies, deeply considered insights, all good. Emotional reactions, dismissive comments, presenting something that is particular/peculiar or half understood as universal principal, all bad.
My son announcing the new beginning. Looking like he missed the call sheet for day 1 on the Gladiator movie set.
So please, only replies that fit the title. If we keep the thread clean, it could be a good place to share ideas, reading, references and research. If someone has a strong negative thesis such as aero being non useful, they should start their own thread.
It may help if I state that I am interested in opportunities inherent in the aero and I'm not aiming at any particular category of velomobile. It may be that the result is only useful for high speed or racing "velomobiles"....
Separately, I'm hoping that Michael (mrue) will start a CFD version of this thread. CFD is such a rabbit hole (as in Alice in Wonderland) that it needs it's own place.
And so, the fun begins..(trumpet noises...)
Can we learn something from the drag values of the sailplane fuselage..?
For now, ignore the long tail boom. It's normally included, so it will add an increment to drag.
The modern sailplane fuselage, the pod, has a fairly simple shape that takes the boundary layer (BL) through a single cycle from laminar, to a transition zone to turbulent, then a pressure recovery zone, before arriving on the tail boom. This simple unitary pod shape can shift the transition point (laminar/turblent) back. It has very low drag values, maybe close to Cd=0.03 at its best (reference area is body section).
Should be noted that the wing roots fair into the rear of the sailplane fuselage pod and do increase drag. Minimized in later iterations, but still there.
If we ignore for the moment the proximity to the ground. Can the velomobile body package the rider, his pedaling legs and the wheels, give the rider comfort, freedom to move, see, enjoy and stay cool....but aim in the direction of these low drag values by managing the pressure distribution to maximize laminar flow.
This is a very open question and some will not like it. Many are committed to the idea of shrink wrapping the surfaces to achieve low frontal area. Even on an intuitive level one should see that this is problematic for the boundary layer.
Back to the sailplane fuselage drag. I looked for something recent. This is an interesting reference and I tried to be careful extracting the data.
"Design of a Flapped Laminar Airfoil for High Performance Sailplane"
Krzysztof Kubrynski...
Graph shows Cd contributions at varying CL. I thought this might be data from analysis on the LS8 or ASW27 or the Diana. He's studied the Diana before so I went with that.
I took the fuse Cd values graphically from the Table 1 graph. Error may be 5% on the smallest values.
Assume rho=1,225 kg/m^3
Assume graph is for the Diana sailplane, at AUW=empty+90kg pilot, so 2720N. Diana wing area Sw=8.16m^2
Assume all Cd contributions are non-dimensionalised with reference area =Sw (Diana)
I'm calling Cda the drag coefficient non-dimensionalised with ref area =As, the fuse section at max thickness, approx 0.346m^2.
Dynamic pressure q=1/2 rho V^2
drag D=Cd 1/2 rho V^2 Sw
D/q=Cd Sw=Cda As=cwA
So, easy enough now to compare the drag of the sailplane fuselage to the velomobiles and to the theoretical minimums.
I may post some drawings from generic shapes that will illustrate some of the ideas above, and might help velomobile aero solutions. We'll see.
Gregg...
My son announcing the new beginning. Looking like he missed the call sheet for day 1 on the Gladiator movie set.
So please, only replies that fit the title. If we keep the thread clean, it could be a good place to share ideas, reading, references and research. If someone has a strong negative thesis such as aero being non useful, they should start their own thread.
It may help if I state that I am interested in opportunities inherent in the aero and I'm not aiming at any particular category of velomobile. It may be that the result is only useful for high speed or racing "velomobiles"....
Separately, I'm hoping that Michael (mrue) will start a CFD version of this thread. CFD is such a rabbit hole (as in Alice in Wonderland) that it needs it's own place.
And so, the fun begins..(trumpet noises...)
Can we learn something from the drag values of the sailplane fuselage..?
For now, ignore the long tail boom. It's normally included, so it will add an increment to drag.
The modern sailplane fuselage, the pod, has a fairly simple shape that takes the boundary layer (BL) through a single cycle from laminar, to a transition zone to turbulent, then a pressure recovery zone, before arriving on the tail boom. This simple unitary pod shape can shift the transition point (laminar/turblent) back. It has very low drag values, maybe close to Cd=0.03 at its best (reference area is body section).
Should be noted that the wing roots fair into the rear of the sailplane fuselage pod and do increase drag. Minimized in later iterations, but still there.
If we ignore for the moment the proximity to the ground. Can the velomobile body package the rider, his pedaling legs and the wheels, give the rider comfort, freedom to move, see, enjoy and stay cool....but aim in the direction of these low drag values by managing the pressure distribution to maximize laminar flow.
This is a very open question and some will not like it. Many are committed to the idea of shrink wrapping the surfaces to achieve low frontal area. Even on an intuitive level one should see that this is problematic for the boundary layer.
Back to the sailplane fuselage drag. I looked for something recent. This is an interesting reference and I tried to be careful extracting the data.
"Design of a Flapped Laminar Airfoil for High Performance Sailplane"
Krzysztof Kubrynski...
Graph shows Cd contributions at varying CL. I thought this might be data from analysis on the LS8 or ASW27 or the Diana. He's studied the Diana before so I went with that.
I took the fuse Cd values graphically from the Table 1 graph. Error may be 5% on the smallest values.
Assume rho=1,225 kg/m^3
Assume graph is for the Diana sailplane, at AUW=empty+90kg pilot, so 2720N. Diana wing area Sw=8.16m^2
Assume all Cd contributions are non-dimensionalised with reference area =Sw (Diana)
I'm calling Cda the drag coefficient non-dimensionalised with ref area =As, the fuse section at max thickness, approx 0.346m^2.
Dynamic pressure q=1/2 rho V^2
drag D=Cd 1/2 rho V^2 Sw
D/q=Cd Sw=Cda As=cwA
So, easy enough now to compare the drag of the sailplane fuselage to the velomobiles and to the theoretical minimums.
I may post some drawings from generic shapes that will illustrate some of the ideas above, and might help velomobile aero solutions. We'll see.
Gregg...
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