Modified Schrenk distribution?
 

I need a spanwise (and better still, chordwise as well) load distribution model for a delta wing with a lot of washout.

One approach is to modify the standard Schrenk result, but does anybody know of anything that's been done already which is accessible / published, and might save me a lot of work ?

G

G,

Have you tried the ESDU datasheets, Digital DATCOM, AIAA ?

I think you may need to have a look at the work Reinhold Stadler who did some work based on that of Hans Multhopp.

Z





http://members.cox.net/twitt/page5.jpg

That looks promising, thanks Zeke - particularly since now doing a quick search on the names this gent was working on Horten flying wings, which is incredibly close to what I'm worrying about.

I will look up what's in the RAeS library when I next get up to town, but it's easier if one knows where to start looking - these gent's work I didn't know about, but armed with some prior knowledge I'm better equipped to start.

Cheers,

G

G,

In that case have a look at the following, it may save you a visit ...

The Nurflügel Page .

Multhopp, Hans: "Methods for Calculating the Lift Distribution of Wings (Subsonic Lifting Surface Theory)"; ARC RM 2884; 1950

Basic deign of flying wing models

The Panknin Twist Formula

Performance analysis of the "Horten IV" Flying Wing

Weissinger.: "The Lift Distribution of Swept Back Wings" NACA TM 1120,1947.

Wilkinson, K.G.: "The Horten Tailless Aircraft", RAE Report FA 259/1, T.N. No. Aero 1703, October, 1945.

Stadler. R. "Solutions for the Bell-Shaped Lift Distribution" PDF version

Z

You are a gentleman and a scholar sir (well certainly the latter anyhow) and I'm in your debt.

G