Using Sensitivities for Flow Analysis

  • Andrew G. Godfrey
Part of the Progress in Systems and Control Theory book series (PSCT, volume 24)


The capabilities of the sensitivity-equation method are presented in context of aerodynamic analysis of hypersonic flight and air-breathing propulsion systems. The method yields stability derivatives, provides parametric guidance, accurately predicts boundary-layer thinning and growth, the onset of flow separation, separation bubbles, and the driving mechanisms in chemically reacting flows. The accuracy of sensitivity-equation calculations are assessed for viscous, chemically reacting flows with comparisons to theoretical and central-difference results. The sensitivity results are used to prioritize design variables by level of relative influence. Being linear, the sensitivity solutions require 10% or less of the computational effort needed to compute flow solutions.


Equivalence Ratio Flame Front Separation Bubble Sensitivity Equation Airfoil Surface 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  1. [1]
    E. M. Cliff and A. G. Godfrey. Direct Calculation of Aerodynamic Force Derivatives: A Sensitivity Equation Approach, AIAA Paper 98–0393, 36th AIAA Aerospace Sciences Meeting and Exhibit, January 12–15, 1998.Google Scholar
  2. [2]
    J. P. Drummond, R. C. Rogers and M. Y. Hussaini. A Detailed Numerical Model of a Supersonic Reacting Mixing Layer, AIAA Paper 86–1427, AIAA/ASME/SAE/ASEE 22 nd Joint Propulsion Conference, June 16–18, 1986.Google Scholar
  3. [3]
    P. Guntermann and G. Dietz. Investigation of an NLF(1)-0416 Airfoil in Compressible Subsonic Flow, In A Selection of Experimental Test Cases for the Validation of CFD Codes, Vol. I and II, AGARD AR-303, Neuilly-Sur-Seine, Canada, 1994.Google Scholar
  4. [4]
    R. Oldenborg, W. Chinitz, M. Friedman, R. Jaffe, C. Jachimowski, M. Rabinowitz and G. Schott. Hypersonic Combustion Kinetics, NASP TM 1107, National Aeronautics and Space Administration, 1990.Google Scholar
  5. [5]
    D. H. Singh, M. H. Carpenter and A. Kumar. Numerical Simulation of Shock-Induced Combustion/Detonation in a Premixed H2-Air Mixture Using the Navier-Stokes Equations, AIAA Paper 91–3359, AIAA, SAE,ASME, and ASEE 27 th Joint Propulsion Conference, Sacramento, California, June 24–26 1991.Google Scholar
  6. [6]
    D. M. Somers. Design and Experimental Results for a Natural-Laminar-Flow Airfoil for General-Aviation Applications, NASA TP-1861, National Aeronautics and Space Administration, June 1981.Google Scholar
  7. [7]
    R. W. Walters, P. Cinnella, D. C. Slack and D. Halt. Characteristic-Based Algorithms for Flows in Thermo-Chemical Nonequilibrium. AIAA Journal,30(5):1304–1313, 1992.zbMATHCrossRefGoogle Scholar

Copyright information

© Springer Science+Business Media New York 1998

Authors and Affiliations

  • Andrew G. Godfrey
    • 1
  1. 1.AeroSoft, Inc.BlacksburgUSA

Personalised recommendations