[adit_YA]

Is it "possible" to design a planar supersonic wind tunnel nozzle design using the minimum length method? As far as I know, the minimum length method is where we "pre-define" the maximum expansion angle, theta, such that it is one-half the prandtl meyer angle corresponding to the exit mach number. The right running characteristic from the inflection point (point of max theta) would then have the desired mach number on the axis of symmetry.

Designing a nozzle using the minimum length method typically results in a sharp throat without an expansion section. However, wind tunnel nozzles are usually designed with a gradually expanding section. If we start with an initial curve, such as an arc or a polynomial of various degrees for the expansion section, and discretize the curve into 'n' points, with the last point being the inflection point where the maximum expansion is half of the Prandtl-Meyer angle, would this approach be feasible?(Basically minimum length method)

Also, can "minimum length" wind tunnel nozzles be implemented or fabricated?. As far as I know, Sivell's design is the best procedure.


Any insights and clarity on this matter is highly appreciated! Been stuck on this doubt for a while!

Thank you!