The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane

A first order in frequency theory is developed for the aerodynamic loads on a harmonically oscillating thin wing of finite aspect ratio in a subsonic compressible flow. The downwash in the vicinity of a horizontal tail behind such a wing is also evaluated to the same order in frequency. The results...

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Main Author: Statler, Irving C.
Format: Others
Published: 1956
Online Access:https://thesis.library.caltech.edu/2783/1/Statler_ic_1956.pdf
Statler, Irving C. (1956) The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/1EHQ-B547. https://resolver.caltech.edu/CaltechETD:etd-06302004-095128 <https://resolver.caltech.edu/CaltechETD:etd-06302004-095128>
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spelling ndltd-CALTECH-oai-thesis.library.caltech.edu-27832019-12-22T03:07:31Z The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane Statler, Irving C. A first order in frequency theory is developed for the aerodynamic loads on a harmonically oscillating thin wing of finite aspect ratio in a subsonic compressible flow. The downwash in the vicinity of a horizontal tail behind such a wing is also evaluated to the same order in frequency. The results are then used to determine the stability derivatives of a conventional-type airplane and to set up the stick-free longitudinal equations of motion including the unsteady flow effects. An important conclusion of this study is that, within the limitations of a "lifting-strip" theory, the airloads on the oscillating finite span wing are linear in frequency in the neighborhood of zero frequency. This is in contrast with the two-dimensional results which show a logarithmic singularity there. As an example of a practical application, calculations are made of the frequency, damping and transient responses of the stick-free longitudinal motion of an F-80A airplane and the results compared with those obtained using quasisteady aerodynamic coefficients. The indications are that, while nonsteady flow considerations show considerable influence upon the control surface motion, they have a negligibly small effect upon the airplane motion. 1956 Thesis NonPeerReviewed application/pdf https://thesis.library.caltech.edu/2783/1/Statler_ic_1956.pdf https://resolver.caltech.edu/CaltechETD:etd-06302004-095128 Statler, Irving C. (1956) The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/1EHQ-B547. https://resolver.caltech.edu/CaltechETD:etd-06302004-095128 <https://resolver.caltech.edu/CaltechETD:etd-06302004-095128> https://thesis.library.caltech.edu/2783/
collection NDLTD
format Others
sources NDLTD
description A first order in frequency theory is developed for the aerodynamic loads on a harmonically oscillating thin wing of finite aspect ratio in a subsonic compressible flow. The downwash in the vicinity of a horizontal tail behind such a wing is also evaluated to the same order in frequency. The results are then used to determine the stability derivatives of a conventional-type airplane and to set up the stick-free longitudinal equations of motion including the unsteady flow effects. An important conclusion of this study is that, within the limitations of a "lifting-strip" theory, the airloads on the oscillating finite span wing are linear in frequency in the neighborhood of zero frequency. This is in contrast with the two-dimensional results which show a logarithmic singularity there. As an example of a practical application, calculations are made of the frequency, damping and transient responses of the stick-free longitudinal motion of an F-80A airplane and the results compared with those obtained using quasisteady aerodynamic coefficients. The indications are that, while nonsteady flow considerations show considerable influence upon the control surface motion, they have a negligibly small effect upon the airplane motion.
author Statler, Irving C.
spellingShingle Statler, Irving C.
The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane
author_facet Statler, Irving C.
author_sort Statler, Irving C.
title The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane
title_short The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane
title_full The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane
title_fullStr The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane
title_full_unstemmed The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane
title_sort effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane
publishDate 1956
url https://thesis.library.caltech.edu/2783/1/Statler_ic_1956.pdf
Statler, Irving C. (1956) The effects of nonstationary aerodynamics of the rigid-body dynamic stability of an airplane. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/1EHQ-B547. https://resolver.caltech.edu/CaltechETD:etd-06302004-095128 <https://resolver.caltech.edu/CaltechETD:etd-06302004-095128>
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