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Evaluation method of longitudinal static stability of tailless airplane. Mubiyokuki no tate no seianteisei no hyokaho

Journal Article:

Abstract

As for the tailless airplane which has the swept taper wing of linear leading and tailing edges, the longitudinal static stability was evaluated by using the modified strip or airfoil theory and the lifting surface theory (DLM method). The sectional lift coefficient of the whole wing, the pitching moment coefficient around the center of gravity, and the equation relating to the elevon were shown. It is thought as a weak point of any tailless airplane that the spanwise lift distribution may keep away from the optimal one because the wash-out is necessary to keep the longitudinal static stability. In order to evaluate this fact, the inductive drag was calculated by using the calculation soft for the induced drag based on the lift surface method to obtain the airplane efficiency factor. The Northrop XB-35 was used for the model of this calculation. Both theories agreed qualititatively. The allowable range of longitudinal center of gravity was 12.5% of the mean chord length. The structural twist is about 9{degree}, and this value gives hardly any adverse effect to the airplane efficiency factor for crusing configuration. 13 refs., 9 figs., 2 tabs.
Authors:
Ando, S; Kajita, H [1] 
  1. Nagoya University, Nagoya (Japan). Faculty of Engineering
Publication Date:
Jan 05, 1992
Product Type:
Journal Article
Reference Number:
NEDO-92-911265; EDB-92-125054
Resource Relation:
Journal Name: Nippon Koku Uchu Gakkai-Shi (Journal of the Japan Society for Aeronautical and Space Sciences); (Japan); Journal Volume: 40:456
Subject:
32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION; 42 ENGINEERING; AIRCRAFT; AIRFOILS; DRAG; EFFICIENCY; GEOMETRY; GRAVITATION; MOTION; NAVIGATION; STABILITY; AERODYNAMICS; AIRCRAFT COMPONENTS; INCLINATION; SHAPE; STANDARDIZATION; FLUID MECHANICS; MATHEMATICS; MECHANICS; 320201* - Energy Conservation, Consumption, & Utilization- Transportation- Air & Aerospace; 420400 - Engineering- Heat Transfer & Fluid Flow
OSTI ID:
5074390
Country of Origin:
Japan
Language:
Japanese
Other Identifying Numbers:
Journal ID: ISSN 0021-4663; CODEN: NKGAB
Submitting Site:
NEDO
Size:
Pages: 14-22
Announcement Date:

Journal Article:

Citation Formats

Ando, S, and Kajita, H. Evaluation method of longitudinal static stability of tailless airplane. Mubiyokuki no tate no seianteisei no hyokaho. Japan: N. p., 1992. Web.
Ando, S, & Kajita, H. Evaluation method of longitudinal static stability of tailless airplane. Mubiyokuki no tate no seianteisei no hyokaho. Japan.
Ando, S, and Kajita, H. 1992. "Evaluation method of longitudinal static stability of tailless airplane. Mubiyokuki no tate no seianteisei no hyokaho." Japan.
@misc{etde_5074390,
title = {Evaluation method of longitudinal static stability of tailless airplane. Mubiyokuki no tate no seianteisei no hyokaho}
author = {Ando, S, and Kajita, H}
abstractNote = {As for the tailless airplane which has the swept taper wing of linear leading and tailing edges, the longitudinal static stability was evaluated by using the modified strip or airfoil theory and the lifting surface theory (DLM method). The sectional lift coefficient of the whole wing, the pitching moment coefficient around the center of gravity, and the equation relating to the elevon were shown. It is thought as a weak point of any tailless airplane that the spanwise lift distribution may keep away from the optimal one because the wash-out is necessary to keep the longitudinal static stability. In order to evaluate this fact, the inductive drag was calculated by using the calculation soft for the induced drag based on the lift surface method to obtain the airplane efficiency factor. The Northrop XB-35 was used for the model of this calculation. Both theories agreed qualititatively. The allowable range of longitudinal center of gravity was 12.5% of the mean chord length. The structural twist is about 9{degree}, and this value gives hardly any adverse effect to the airplane efficiency factor for crusing configuration. 13 refs., 9 figs., 2 tabs.}
journal = {Nippon Koku Uchu Gakkai-Shi (Journal of the Japan Society for Aeronautical and Space Sciences); (Japan)}
volume = {40:456}
journal type = {AC}
place = {Japan}
year = {1992}
month = {Jan}
}