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An Evaluation of Procedures for Calculating Aerodynamic Loads.

AD465433

Publication Date	1965
Personal Author	Schindel, L. H.
Page Count	287
Abstract	Existing theories are examined with the object of selecting the best methods for computing aerodynamic lift distributions for use in structural design. Subsonic, transonic and supersonic Mach numbers are included. Configurations consist of wing-body combinations such as might be employed for airplane-type vehicles. The present investigation is limited to the linear range of angle of attack. The simplest theories which give accuracy consistent with structural design practice are reduced to computational procedure; the accuracy of a theory having been established by comparison with existing experimental data. In cases where no adequate theory is available or experimental data is lacking, further research is recommended. Future extensions to nonlinear regimes, more general configurations, and higher Mach numbers are also described. (Author)
Keywords	Aerodynamic loading Lift Wing body configurations Mathematical analysis Theory Design Computer programming Linear systems Aeroelasticity Supersonic characteristics Subsonic characteristics Transonic characteristics Nonlinear systems Hypersonic flight Flutter Gusts Viscosity Thickness Maneuverability Vortices Aerodynamic heating Slender-body theory
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	46B - Fluid Mechanics
Corporate Authors	Massachusetts Inst Of Tech Cambridge
Document Type	Technical Report
Title Note	Final rept., Feb-Dec 64.
NTIS Issue Number	197716
Contract Number	AF 33(615)-1199

An Evaluation of Procedures for Calculating Aerodynamic Loads.

An Evaluation of Procedures for Calculating Aerodynamic Loads.
AD465433

Publication Date	1965
Personal Author	Schindel, L. H.
Page Count	287
Abstract	Existing theories are examined with the object of selecting the best methods for computing aerodynamic lift distributions for use in structural design. Subsonic, transonic and supersonic Mach numbers are included. Configurations consist of wing-body combinations such as might be employed for airplane-type vehicles. The present investigation is limited to the linear range of angle of attack. The simplest theories which give accuracy consistent with structural design practice are reduced to computational procedure; the accuracy of a theory having been established by comparison with existing experimental data. In cases where no adequate theory is available or experimental data is lacking, further research is recommended. Future extensions to nonlinear regimes, more general configurations, and higher Mach numbers are also described. (Author)
Keywords	Aerodynamic loading Lift Wing body configurations Mathematical analysis Theory Design Computer programming Linear systems Aeroelasticity Supersonic characteristics Subsonic characteristics Transonic characteristics Nonlinear systems Hypersonic flight Flutter Gusts Viscosity Thickness Maneuverability Vortices Aerodynamic heating Slender-body theory
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	46B - Fluid Mechanics
Corporate Authors	Massachusetts Inst Of Tech Cambridge
Document Type	Technical Report
Title Note	Final rept., Feb-Dec 64.
NTIS Issue Number	197716
Contract Number	AF 33(615)-1199