翼型
外倾角(空气动力学)
NACA翼型
升阻比
航空航天工程
升力系数
飞机
海洋工程
阻力系数
攻角
Lift(数据挖掘)
升力诱导阻力
空气动力学
阻力
环境科学
航空学
计算机科学
工程类
物理
气象学
雷诺数
数据挖掘
湍流
作者
Muhammad Agung Bramantya,Ray Rhido Ribuna Ginting
出处
期刊:Nucleation and Atmospheric Aerosols
日期:2020-01-01
被引量:4
摘要
Unmanned aerial vehicles (UAV) are used in the military field for missions such as observation, surveillance and seeking object. UAV observation can be used to monitor humans, weather, forests, agriculture, and fisheries and so on. UAV can be operated for very broad missions with low development costs compared to manned aerial vehicles with a low risk of death. The design of an aircraft affects the performances of the aircraft itself. Aircraft flying characteristics are influenced by the value of coefficient of drag (CD) and coefficient of lift (CL). The value of CD affects how much aircraft friction with the air, while the value of CL affects how much lifting force the aircraft is produced so it can fly. The design output needs the most optimal CD and CL values to get the optimal aircraft performance. In this study, we simulated the effect of 4 digit NACA changes on the characteristics of the plane’s CD and CL. This study uses variations modification of NACA digits with different variables. NACA airfoil 4 digit series (MPXX) designates camber lines, maximum camber position and thickness. Based on the results of this study, the optimal CD and CL values for the Airfoil NACA with the Aerosonde UAV model are designs that have a large ratio of lift and drag (CL / CD). The lower the CD value and the higher the CL value, the better the performance of the UAV. The design that has the largest CL / CD is the NACA 6412 Airfoil.
科研通智能强力驱动
Strongly Powered by AbleSci AI