An Evaluation of Procedures for Calculating Aerodynamic Loads
Report Number: AFFDL TR 65-18
Author(s): Schindel, Leon H.
Corporate Author(s): Massachusetts institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-05
Pages: 312
Contract: AF 33(615)-1199
DoD Project: 1367
DoD Task: 136715
Identifier: AD0465433
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.
Provenance: AFRL/VACA
Author(s): Schindel, Leon H.
Corporate Author(s): Massachusetts institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-05
Pages: 312
Contract: AF 33(615)-1199
DoD Project: 1367
DoD Task: 136715
Identifier: AD0465433
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.
Provenance: AFRL/VACA