Document Type
Article
Author ORCID Identifier
Benjamin C. Moulton https://orcid.org/0000-0003-2100-1160
Journal/Book Title/Conference
Aerospace
Volume
11
Issue
6
Publisher
MDPI AG
Publication Date
6-19-2024
Journal Article Version
Version of Record
Creative Commons License
This work is licensed under a Creative Commons Attribution 4.0 License.
First Page
1
Last Page
22
Abstract
In the preliminary design of aircraft lifting surfaces, accurate mass and inertia properties can be difficult to obtain. Typically, such methods as computer-aided design or statistical processes are used to determine these properties. These methods require significant time and effort to implement. The present paper presents an exact analytic method for calculating the volume, mass, center of gravity, and inertia properties of wing segments and rotors of constant density. The influence of taper, spanwise thickness distribution, airfoil geometry, and sweep are included. The utility of the method is presented, and the accuracy is evaluated with various test cases via percent difference with a corresponding computer-aided design model. These case studies demonstrate the present method to be accurate to within about 1% for typical wing geometries and within about 1.3% for typical propeller geometries.
Recommended Citation
Moulton, B.C.; Hunsaker, D.F. Analytic Solutions for Volume, Mass, Center of Gravity, and Inertia of Wing Segments and Rotors of Constant Density. Aerospace 2024, 11, 492. https://doi.org/10.3390/aerospace11060492
