Author: Robert S. Swanson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 58
Book Description
Summary: An investigation was made by lifting-surface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagnetic-analogy method. From the results, aspect-ratio corrections for the damping in roll and aileron hinge moments for a wing in steady roll were obtained that are considerably more accurate than those given by lifting-line theory. First-order effects of compressibility were included in the computations. The results obtained by lifting-surface theory indicate that the damping in roll for a wing of aspect ratio 6 is 13 percent less than that given by lifting-line theory and 5 percent less than that given by lifting-line theory with the edge-velocity correction derived by Robert T. Jones applied. The results are extended to wings of other aspect ratios.
Lifting-surface-theory Values of the Damping in Roll and of the Parameter Used in Estimating Aileron Stick Forces
Author: Robert S. Swanson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 58
Book Description
Summary: An investigation was made by lifting-surface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagnetic-analogy method. From the results, aspect-ratio corrections for the damping in roll and aileron hinge moments for a wing in steady roll were obtained that are considerably more accurate than those given by lifting-line theory. First-order effects of compressibility were included in the computations. The results obtained by lifting-surface theory indicate that the damping in roll for a wing of aspect ratio 6 is 13 percent less than that given by lifting-line theory and 5 percent less than that given by lifting-line theory with the edge-velocity correction derived by Robert T. Jones applied. The results are extended to wings of other aspect ratios.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 58
Book Description
Summary: An investigation was made by lifting-surface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagnetic-analogy method. From the results, aspect-ratio corrections for the damping in roll and aileron hinge moments for a wing in steady roll were obtained that are considerably more accurate than those given by lifting-line theory. First-order effects of compressibility were included in the computations. The results obtained by lifting-surface theory indicate that the damping in roll for a wing of aspect ratio 6 is 13 percent less than that given by lifting-line theory and 5 percent less than that given by lifting-line theory with the edge-velocity correction derived by Robert T. Jones applied. The results are extended to wings of other aspect ratios.
Lifting-surface-theory Values of the Damping in Roll and of the Parameter Used in Estimating Aileron Stick Forces
Author: Langley Aeronautical Laboratory
Publisher: Hassell Street Press
ISBN: 9781015180680
Category :
Languages : en
Pages : 58
Book Description
This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Publisher: Hassell Street Press
ISBN: 9781015180680
Category :
Languages : en
Pages : 58
Book Description
This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1078
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1078
Book Description
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 696
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 696
Book Description
Report
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
Book Description
Compressive Strength of 24S-T Aluminum-alloy Flat Panels with Longitudinal Formed Hat-section Stiffeners Having a Ratio of Stiffener Thickness to Skin Thickness Equal to 1.00
Author: William A. Hickman
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 558
Book Description
Results are present for part of a test program on 24S-T aluminum-alloy flat compression panels with hat-section stiffeners. The results show the effect of the relative dimensions of a panel on the buckling stress and average stress at maximum load. Comparative envelope curves are presented to provide some indication of the relative structural efficiencies of hat- and Z-stiffened panels having a ratio of stiffener thicknews to skin thickness of one.
Publisher:
ISBN:
Category : Aluminum alloys
Languages : en
Pages : 558
Book Description
Results are present for part of a test program on 24S-T aluminum-alloy flat compression panels with hat-section stiffeners. The results show the effect of the relative dimensions of a panel on the buckling stress and average stress at maximum load. Comparative envelope curves are presented to provide some indication of the relative structural efficiencies of hat- and Z-stiffened panels having a ratio of stiffener thicknews to skin thickness of one.
Experimental Determination of Effect of Structural Rigidity on Rolling Effectiveness of Some Straight and Swept Wings at Mach Numbers from 0.7 to 1.7
Author: H. Kurt Strass
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 46
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 46
Book Description
Technical Note
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 494
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 494
Book Description
Annual Report of the National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 652
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 652
Book Description