A Viscous/Potential Flow Interaction Analysis for Circulation-Controlled Airfoils.

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Abstract:

A method developed for the analysis of the incompressible viscous flow over circulation-controlled airfoils is described. A surface vorticity method is used to solve the inviscid portion of the flow and a combination of integral and finite difference methods is used to calculate the development of the viscous layers. An iterative process is used to arrive at final solutions which satisfy an appropriate trailing-edge condition and incorporate the interaction between the viscous and potential regions of the flow. Comparisons between calculated and experimental results show good agreement for surface pressure distributions and lift coefficients over a range of blowing momentum coefficient from 0 to 0.12. A discussion of the possibility of Coanda jet detachment when circulation-controlled airfoils are operating at high subsonic Mach Numbers is included in an Appendix. Author

Author(s):
Dvorak, F. A.
Author Organization(s):
ANALYTICAL METHODS INC BELLEVUE WASH
Descriptive Note:
Final rept.,
Pagination:
0052

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
7710
Contract/Grant Number(s):
N00600-76-C-1494
 Subject Terms
Joint Capability Areas:
JCA_5_Command and Control; JCA_5.3_Planning; JCA_1.2.7_Experimentation; JCA_1.4.2_Health Service Delivery; JCA_1.4_Force Support; JCA_1_Force Support; JCA_3.2_Engagement; JCA_3_Force Application
Modernization Areas:
Quantum Science and Computing
Communities of Interest:
Ground and Sea Platforms
Descriptor(s):
*VISCOUS FLOW, *BOUNDARY LAYER CONTROL, *POTENTIAL FLOW, VORTICES, AIRFOILS, FINITE DIFFERENCE THEORY, COEFFICIENTS, INTEGRAL EQUATIONS, LIFT, ITERATIONS, PRESSURE DISTRIBUTION, INCOMPRESSIBLE FLOW, MOMENTUM, COANDA EFFECT
Field(s)/Group(s):
Aircraft, Fluid Mechanics
Report Date:
1978 May 01