Since my last thread on lifting bodies I started thinking about a Horton Wingless-like configuration, like the one on the right in the drawing below:
Simple construction, made to fly and not to fall in a controlled manner, true-airfoil shaped fuselage, no vortex lift. However, there is one element which I am struggling with: the wing twist.
Entering the data in several spreadsheets (Culver and Pankin) in order to get a general idea, I always get a needed twist angle between 60 and 70 degrees. Even with Cm=0 airfoils I always get an extreme twist output.
Do twist calculations have a limit when it comes to low AR tailless configurations? Is twist not needed past a certain AR? ''Simply'' choose a reflexed airfoil, calculate the trim needed and let the 3D flow (in the case of an highly swept delta) do the rest? Here is a three-view drawing of the soviet SAM-9, built without any software analysis and successfully flown in 1937 to illustrate my point:
Link to the lifting-body thread:
https://www.homebuiltairplanes.com/...17-what-if-propeller-driven-lifting-body.html
Any input would be appreciated.
Simple construction, made to fly and not to fall in a controlled manner, true-airfoil shaped fuselage, no vortex lift. However, there is one element which I am struggling with: the wing twist.
Entering the data in several spreadsheets (Culver and Pankin) in order to get a general idea, I always get a needed twist angle between 60 and 70 degrees. Even with Cm=0 airfoils I always get an extreme twist output.
Do twist calculations have a limit when it comes to low AR tailless configurations? Is twist not needed past a certain AR? ''Simply'' choose a reflexed airfoil, calculate the trim needed and let the 3D flow (in the case of an highly swept delta) do the rest? Here is a three-view drawing of the soviet SAM-9, built without any software analysis and successfully flown in 1937 to illustrate my point:
Link to the lifting-body thread:
https://www.homebuiltairplanes.com/...17-what-if-propeller-driven-lifting-body.html
Any input would be appreciated.
