Cover Image

Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence

This paper presents results of quasi-steady and unsteady damping derivatives of a delta wing whose leading edge is straight. Results are computed for a wide range of Mach numbers and angles of attack. Here the contribution to the damping derivatives due to the rate of change of angle of attack is es...

Full description

Saved in:
Bibliographic Details
Main Authors: Renita, sharon Monis, Crasta, Asha, Khan, Sher Afghan
Format: Article
Language:English
Published: Science and Engineering Research Support Society 2020
Subjects:
TJ210.2 Mechanical devices and figures. Automata. Ingenious mechanism. Robots (General)
TL780 Rockets
Online Access:http://irep.iium.edu.my/81244/1/81244_Est%C4%B1mat%C4%B1on%20of%20Hyperson%C4%B1c%20Unsteady.pdf
http://irep.iium.edu.my/81244/
http://sersc.org/journals/index.php/ijast
Tags: Add Tag
No Tags, Be the first to tag this record!
id my.iium.irep.81244
record_format dspace
spelling my.iium.irep.812442020-12-08T08:35:02Z http://irep.iium.edu.my/81244/ Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence Renita, sharon Monis Crasta, Asha Khan, Sher Afghan TJ210.2 Mechanical devices and figures. Automata. Ingenious mechanism. Robots (General) TL780 Rockets This paper presents results of quasi-steady and unsteady damping derivatives of a delta wing whose leading edge is straight. Results are computed for a wide range of Mach numbers and angles of attack. Here the contribution to the damping derivatives due to the rate of change of angle of attack is estimated separately. The results show that with the increase in Mach number, there is a progressive decrease in the damping derivatives for both the cases (i.e., unsteady and quasi-steady). With the further rise in the Mach values, the magnitude of decline has diminished for Mach number M = 10 and above the state of steady-state is achieved. For the entire range of the Mach number, the location of the center of pressure remained unchanged for a fixed value of the flow deflection angle δ. For the lower flow deflection angle of the wing, the magnitude of the damping derivatives is smaller as compared to the higher values of δ. The contribution to the damping derivatives from the rate of change of angle of attack is around 20 percent of the quasi-steady one. The results for flow deflection angles of ten degrees and twenty degrees show a different trend. When we compare the results of the damping derivatives for a fixed pivot position, it is seen that the damping derivatives show different behavior for two different values of the flow deflection angle δ. The steady-state varies for two values of δ. When we look at the damping derivatives at hinge point k = 0.6, the magnitude is small. The steady-state is attained early for quasi-steady in comparison to the unsteady damping derivatives. Science and Engineering Research Support Society 2020-06-30 Article PeerReviewed application/pdf en http://irep.iium.edu.my/81244/1/81244_Est%C4%B1mat%C4%B1on%20of%20Hyperson%C4%B1c%20Unsteady.pdf Renita, sharon Monis and Crasta, Asha and Khan, Sher Afghan (2020) Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence. International Journal of Advanced Science and Technology, 29 (6). pp. 6844-6863. ISSN 2005-4238 E-ISSN 2207-6360 http://sersc.org/journals/index.php/ijast
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
language English
topic TJ210.2 Mechanical devices and figures. Automata. Ingenious mechanism. Robots (General)
TL780 Rockets
spellingShingle TJ210.2 Mechanical devices and figures. Automata. Ingenious mechanism. Robots (General)
TL780 Rockets
Renita, sharon Monis
Crasta, Asha
Khan, Sher Afghan
Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence
description This paper presents results of quasi-steady and unsteady damping derivatives of a delta wing whose leading edge is straight. Results are computed for a wide range of Mach numbers and angles of attack. Here the contribution to the damping derivatives due to the rate of change of angle of attack is estimated separately. The results show that with the increase in Mach number, there is a progressive decrease in the damping derivatives for both the cases (i.e., unsteady and quasi-steady). With the further rise in the Mach values, the magnitude of decline has diminished for Mach number M = 10 and above the state of steady-state is achieved. For the entire range of the Mach number, the location of the center of pressure remained unchanged for a fixed value of the flow deflection angle δ. For the lower flow deflection angle of the wing, the magnitude of the damping derivatives is smaller as compared to the higher values of δ. The contribution to the damping derivatives from the rate of change of angle of attack is around 20 percent of the quasi-steady one. The results for flow deflection angles of ten degrees and twenty degrees show a different trend. When we compare the results of the damping derivatives for a fixed pivot position, it is seen that the damping derivatives show different behavior for two different values of the flow deflection angle δ. The steady-state varies for two values of δ. When we look at the damping derivatives at hinge point k = 0.6, the magnitude is small. The steady-state is attained early for quasi-steady in comparison to the unsteady damping derivatives.
format Article
author Renita, sharon Monis
Crasta, Asha
Khan, Sher Afghan
author_facet Renita, sharon Monis
Crasta, Asha
Khan, Sher Afghan
author_sort Renita, sharon Monis
title Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence
title_short Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence
title_full Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence
title_fullStr Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence
title_full_unstemmed Estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence
title_sort estımatıon of hypersonıc unsteady and qausı-steady dampıng derıvatıves for a delta wings at large incıdence
publisher Science and Engineering Research Support Society
publishDate 2020
url http://irep.iium.edu.my/81244/1/81244_Est%C4%B1mat%C4%B1on%20of%20Hyperson%C4%B1c%20Unsteady.pdf
http://irep.iium.edu.my/81244/
http://sersc.org/journals/index.php/ijast
_version_ 1685578530116599808
score 13.211869

Similar Items