Research on analytical scaling method and scale effects for subscale flight test of blended wing body civil aircraft

2020 ◽  
Vol 106 ◽  
pp. 106114
Author(s):  
Gang Wang ◽  
Minghui Zhang ◽  
Yujin Tao ◽  
Jie Li ◽  
Dong Li ◽  
...  
Keyword(s):  
Scale Effects ◽  
Flight Test ◽  
Scaling Method ◽  
Civil Aircraft ◽  
Blended Wing Body

scholarly journals Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

2019 ◽  
Vol 256 ◽  
pp. 02004
Author(s):  
Nornashiha Mohd Saad ◽  
Wirachman Wisnoe ◽  
Rizal Effendy Mohd Nasir ◽  
Zurriati Mohd Ali ◽  
Ehan Sabah Shukri Askari
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Cfd Simulation ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Flight Test ◽  
Longitudinal Direction ◽  
Static Stability ◽  
Pitching Moment ◽  
Aerial Vehicle ◽  
Blended Wing Body

This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft.

scholarly journals Research on Civil Aircraft Flight Test of Power Supply Quality Analysis

2021 ◽  
Vol 2136 (1) ◽  
pp. 012016
Author(s):  
Jingtao Wu ◽  
Pei Wang ◽  
Jin Cai ◽  
Ying Liu
Keyword(s):  
Power Supply ◽  
Flight Test ◽  
Quality Standard ◽  
Test Method ◽  
Quality Analysis ◽  
Quality Test ◽  
Test Characteristic ◽  
Aircraft Flight ◽  
Civil Aircraft ◽  
Test Requirements

Abstract In the process of civil aircraft airworthiness, analyzing power quality is the key to verify whether the power supply system meets the requirements of the clause. This paper makes deep research on the domestic and foreign power supply quality standard files and detailed introduces the characteristics of the power supply quality standard files. Then, comparative and analysis give suggestions which tally with power supply quality test requirements. Finally, define the special power supply quality test method for the practical engineering specifically, and power supply quality test characteristic in civil aircraft flight test, to provide guidance help for the future civil aircraft models.

The Effect of Belly-Flap on Aerodynamic Performance of Blended Wing Body Civil Aircraft

2013 ◽  
Vol 378 ◽  
pp. 69-73
Author(s):  
Chen Fang Cai ◽  
Yong Ming Qin ◽  
Jiang Hao Wu
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Angle Of Attack ◽  
Aerodynamic Performance ◽  
Design Parameters ◽  
Flight Safety ◽  
Optimized Design ◽  
Flight Condition ◽  
Civil Aircraft ◽  
Blended Wing Body

The effect of Belly-flap on aerodynamic performance of BWB civil aircraft are investigated in take-off and landing by computational fluid dynamics. And the overload of BWB with Belly-flap also is calculated in the same flight condition. Six parameters are discussed as design parameters of the Belly flap. It is shown that the proper combination of design parameters of Belly-flap can increase the maximum of lift and reduce the angle of attack and nose down moment to improve the flight safety in take-off and landing. When the aircraft with Belly-flap encounters the gust, the maximum overload is very close to 2.5 which are requested by FAR. It is suggested the optimized design of Belly-flap should be done if the Belly-flap is applied in BWB civil aircraft.

The Effect of Gust on Blended-Wing-Body Civil Aircraft

2014 ◽  
Vol 1016 ◽  
pp. 359-364 ◽  
Author(s):  
Chen Fang Cai ◽  
Jiang Hao Wu ◽  
Bin Liang
Keyword(s):  
Dynamic Response ◽  
Stokes Equations ◽  
Dynamic Properties ◽  
Equations Of Motion ◽  
Navier Stokes ◽  
Complete Model ◽  
Navier Stokes Equations ◽  
Aerodynamic Properties ◽  
Civil Aircraft ◽  
Blended Wing Body

In this paper, aerodynamic properties of Blended Wing Body (BWB) civil aircraft are studied by two models: one calls complete model that is computed by numerical simulation coupling equations of motion with the Navier-Stokes equations, and the other doesn’t consider the equations of motion (without dynamic response). The results show that the model without dynamic response can also correctly predict the trend of the dynamic properties compared with complete model. Nevertheless, there are some quantitative differences existing between the complete model and the model without dynamic response.

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