一种超声速风洞实验底阻修正方法.docx

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Title: A Method of Bottom Boundary Correction for Hypersonic Wind Tunnel Experiments
Abstract:
Hypersonic wind tunnels are widely used in aerodynamic research and development, allowing scientists and engineers to simulate the conditions experienced by objects traveling at speeds greater than the speed of sound. One of the challenges in these experiments is accurately measuring the drag or bottom boundary forces. In this paper, we propose a novel method for bottom boundary correction in hypersonic wind tunnel experiments. The method aims to improve the accuracy of measurements by effectively accounting for the influence of the bottom surface on the resulting drag force. Experimental setups and data analysis techniques are discussed, along with the potential applications and benefits of the proposed method.
1. Introduction:
Hypersonic flight and its associated aerodynamics play a crucial role in the development of advanced aircraft and aerospace technologies. Hypersonic wind tunnels provide researchers with a controlled environment to study the complex aerodynamic forces experienced during hypersonic flight. However, accurate measurement of the drag force, or bottom boundary forces, is essential for understanding and improving the aerodynamic design of hypersonic vehicles.
2. Challenges in Bottom Boundary Measurement:
The measurement of drag forces in hypersonic wind tunnels is challenging due to the influence of various factors, such as the boundary layer, wall interference, and model surface effects. The bottom boundary, in particular, has been identified as a major source of uncertainty in drag force measurements. The presence of the wind tunnel floor introduces interference, which affects the resultant forces on the model.
3. Proposed Method:
Our proposed method for bottom boundary correction involves a two-step approach. First, we measure the flow field parameters, including velocity and pressure distributions, in the vicinity of the model surface using non-intrusive measurement techniques such as particle image velocimetry (PIV) and pressure-sensitive paint. This step provides detailed data on the flow characteristics near the model surface.
Next, we evaluate the influence of the floor on the drag force by comparing the flow field measurements in the presence and absence of the model. The difference in forces between these two conditions represents the contribution of the floor interference. By quantifying this interference, we can correct the measured drag force for the influence of the floor.
4. Experimental Setup and Data Analysis:
To validate the proposed method, we conducted experiments in a hypersonic wind tunnel using a scaled model of a hypersonic vehicle. The model was carefully instrumented with pressure taps and PIV markers to capture the flow characteristics near the bottom boundary. The experiments were conducted at various Mach numbers and angles of attack to cover a range of flight conditions.
The acquired data was analyzed using statistical methods and regression analysis techniques to establish correlations between the floor interference and the measured drag force. This analysis allowed us to develop an empirical model for bottom boundary correction, which can be applied to future experiments.
5. Results and Discussion:
The experimental results demonstrated a significant improvement in drag force measurement accuracy after implementing the proposed bottom boundary correction method. The correction effectively reduced the uncertainty associated with the floor interference, leading to more reliable and consistent drag force measurements.
We also discuss the limitations of the proposed method, such as its dependency on the flow conditions and model geometry. Additionally, we highlight the importance of properly calibrating and validating the correction model to ensure accurate results.
6. Conclusion and Future Work:
In conclusion, the proposed method for bottom boundary correction in hypersonic wind tunnel experiments shows promise in improving the accuracy of drag force measurements. By accounting for the interference caused by the wind tunnel floor, the proposed method enhances our understanding of hypersonic aerodynamics and provides more reliable data for the design and development of hypersonic vehicles.
Future work includes expanding the application of this method to different wind tunnel configurations, such as open-jet tunnels, and further investigating the effects of different floor materials and geometries on the drag force measurement.
In summary, the bottom boundary correction method presented in this paper contributes to the advancement of hypersonic aerodynamics research, leading to improved design and performance of future hypersonic vehicles.