Panel method, Supersonic Analyze, Delta wing

[Cheol-Kyun Choi]

Hello Everyone?

I'm trying to using panel method for delta wing

but the result is not so good...

I tried some case

increase U, W, tip treatment, iter number, etc..

but the result still not so good.

for example, CL is over the 1 in AoA -2 to 4

1) how can I get the good result using panel method in supersonic?

2) And I notice that over the transoinic(also supersonic), VLM method have more accuracy than panel method

    I don't know why....

[Cheol-Kyun Choi]

I'll add something

I compared with the Wind tunnel data used AVRO720 scaled model

and, also used the PANAIR(A502I)

Condition

=======================

M 2.0, compare Lift coefficient

VSPAero: VLM, Batch, Jacobi, Leading edge checked

PANAIR: Doublet matching condtion(matchw: 1) /  Isotropic option used(matchw: 3)

VSPAero VLM method result(Orange) is similar with PANAIR - Doublet matching, didn't used trefftz plane option(Yellow)

Wind tunnel data(Blue) is similar with PANAIR - Isotropic option, used trefftz plane option(Green)

[Rob McDonald]

The VSPAERO thick-surface panel method formulation has not been
extended to supersonic flow. Only the VLM is expected to work for
supersonic flow.

Rob

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[Cheol-Kyun Choi]

Thank you for your reply!

I have more question.

1) Then the supersonic delta wing result that Dave Kinney did is using VLM method?

2) AVL also using VLM method and Prandtl-Glauert compressibility rule. But in manual, AVL can get good result under M 0.6

   VSPAero also using same thing, but how can it analyze supersonic flow??

   It's amazing

CK

2017년 11월 14일 화요일 오후 10시 33분 42초 UTC+9, Rob McDonald 님의 말:

[Rob McDonald]

Yes, the supersonic delta wing results that Kinney presented are using
the VLM mode.

In this regard, VSPAERO's formulation is more similar to that of VORLAX:

https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19780008059.pdf

Rob

[Cheol-Kyun Choi]

Thank you Rob!

Have a good day!

2017년 11월 16일 목요일 오후 12시 37분 38초 UTC+9, Rob McDonald 님의 말: