Research on the Performance of Slender Aircraft with Flare-Stabilized-Skirt
Abstract
:1. Introduction
2. Geometrical Model Description
3. Theoretical Modeling of the Aircraft Static Stability
4. Aerodynamic Performance Analysis of the Flared-Skirt Stabilized Aircrafts
4.1. Computational Model and Numerical Method
4.2. Code Validation
4.3. Influence of Deployable Flare Skirt on Aircraft Pressure Distribution
4.4. Influence of Flared Skirts on the Static Stability of Aircrafts
5. Results and Discussion
- (1)
- The deployable flared skirt has a significant effect on adjusting the pressure distribution, which can make the center of pressure of the aircraft move backward.
- (2)
- The influence of flared skirt opening angle θ on static stability: The aircraft is statically unstable when the opening angles are 0°, 10°, or 20°, and the aircraft is statically stable under the partial angle of attack conditions when the opening angle at 30°.
- (3)
- The influence of the angle of attack α on static stability: Under the same Mach number conditions, the static stability of different configurations has the similar trend with the angle of attack. The static stability of the aircraft decreases as α increases when α < 5°. The static stability of the aircraft does not change significantly as α increases when α > 5°.
- (4)
- The influence of Mach number on static stability: At the exact angle of attack, the greater the Ma, the stronger the static stability of the aircraft.
- (5)
- The deployable flared skirt can adjust the flight stability without significantly reducing the lift–drag ratio of the aircraft.
6. Conclusions
Author Contributions
Funding
Data Availability Statement
Conflicts of Interest
Nomenclature
Diameter of the aircraft body (m); | |
Drag (N); | |
Lateral forces (N), ; | |
Lift (N), ; | |
Rolling moment (Nm); | |
Yawing moment (Nm); | |
Pitching moment (Nm); | |
Reference length (m); | |
The relative coordinate of the pressure center on the axis of the body (the dimension is 1); | |
The relative coordinate of the centroid on the axis of the body (the dimension is 1); | |
The derivative of the lateral force coefficient; | |
The derivative of the lift coefficient; | |
Yaw angle (°); | |
Angle of attack (°); | |
Incoming flow pressure (Pa), ; | |
Reference area (m2); | |
Pitch moment coefficient gradient; | |
Yaw moment coefficient gradient; | |
Derivative of the pitching moment coefficient concerning the lift coefficient; | |
Pitch moment coefficient gradient at the common point. |
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Configuration | Length of Head Ln/m | Length of Body Lb/m | Length of Skirt Ls/m | Deployment Angle of the Skirt θ/° |
---|---|---|---|---|
V1 | 3 d | 11 d | d | 0 |
V2 | 3 d | 11 d | d | 10 |
V3 | 3 d | 11 d | d | 20 |
V4 | 3 d | 11 d | d | 30 |
Experimental Conditions | Temperature (k) | Atmospheric Density (kg/m3) | Mach Number | Viscosity Coefficient (Ns/m2) |
---|---|---|---|---|
Value | 89.3 | 0.0371 | 8.2 | 6.161 × 10−6 |
Configuration | V1 | V2 | V3 | V4 |
CG/m | 2.9096 | 2.9081 | 2.9063 | 2.9059 |
/m | 2.908 |
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Pan, X.; Yue, H.; Liu, S.; Yang, F.; Lu, Y.; Chen, G. Research on the Performance of Slender Aircraft with Flare-Stabilized-Skirt. Aerospace 2023, 10, 844. https://doi.org/10.3390/aerospace10100844
Pan X, Yue H, Liu S, Yang F, Lu Y, Chen G. Research on the Performance of Slender Aircraft with Flare-Stabilized-Skirt. Aerospace. 2023; 10(10):844. https://doi.org/10.3390/aerospace10100844
Chicago/Turabian StylePan, Xueting, Honghao Yue, Shufeng Liu, Fei Yang, Yifan Lu, and Gang Chen. 2023. "Research on the Performance of Slender Aircraft with Flare-Stabilized-Skirt" Aerospace 10, no. 10: 844. https://doi.org/10.3390/aerospace10100844