Abstract Foremost amongst rocket nozzle relations is the area–Mach number expression linking the local velocity normalized by the speed of sound to the area ratio A t / A , and the ratio of specific heats. Known as Stodolaʼs equation, the attendant expression is transcendental and requires iteration or numerical root finding in extracting the solution under subsonic or supersonic nozzle operation. In this work, a novel analytical inversion of the problem is pursued to the extent of providing the local Mach number directly at any given cross-section. The inversion process is carried out using two unique approaches. In the first, Bürmannʼs theorem is employed to undertake a functional reversion from which the subsonic solution may be retrieved. In the second, the Successive Approximation Approach is repeatedly applied to arrive at a closed-form representation of the supersonic root. Both methods give rise to unique recursive approximations that permit the selective extraction of the desired solution to an arbitrary level of accuracy. Results are verified numerically and the precision associated with the supersonic solution is shown to improve with successive increases in the ratio of specific heats.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Direct calculation of the average local Mach number in converging–diverging nozzles


    Contributors:

    Published in:

    Publication date :

    2011-10-20


    Size :

    5 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Equilibrium Between Phases in Converging-Diverging Nozzles

    Penner, S. S. / Williams, F. A. | AIAA | 1962


    Nonideal isentropic gas flow through converging-diverging nozzles

    Bober, W. / Chow, W.L. | Tema Archive | 1990



    Analysis of Real Fluid Flows in Converging Diverging Nozzles

    Li, Ding / Xia, Guoping / Merkle, Charles | AIAA | 2003