Lifting Surface Theory for Wings of Arbitrary Planform

reportActive / Technical Report | Accession Number: ADA028449 | Open PDF

Abstract:

This theory permits the calculation of pressure distributions over a thin airfoil in steady, inviscid, incompressible flow or given a desired chordwise pressure distribution the camber line of an ideal wing can be determined. The method treats the circulation about the wing as a continuous vortex sheet of variable strength covering the wing planform and trailing downstream to infinity. The results of the present numerical solution for the pressure distribution solution are not conclusive. However the solution for the camber line of an ideal wing is in reasonable agreement with published two dimensional results.

Author(s):
Parks, John L.
Author Organization(s):
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Descriptive Note:
Engineer's thesis
Pagination:
0070

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Monitor Series:
NPS
 Subject Terms
Joint Capability Areas:
JCA_1.4.2_Health Service Delivery; JCA_1.4_Force Support; JCA_5_Command and Control; JCA_5.3_Planning; JCA_1.2_Force Preparation; JCA_1_Force Support
Modernization Areas:
Directed Energy
Communities of Interest:
Air Platforms
Descriptor(s):
*AERODYNAMIC CHARACTERISTICS, *LIFTING SURFACES, CAMBER, CIRCULATION, COMPUTATIONS, INVISCID FLOW, NUMERICAL METHODS AND PROCEDURES, PRESSURE DISTRIBUTION, THEORY, THESES, THIN WINGS, VORTICES
Field(s)/Group(s):
Aerodynamics, Fluid Mechanics
Keyword(s):
VORTEX SHEETS
Report Date:
1976 Mar 01