Rose Project Highlights
Duration: Spring 2023
Tools Used:
- SOLIDWORKS for CAD design
- Sensors for lift and airspeed detection
- Data analysis tools for generating lift-to-airspeed graphs
- MATLAB for data processing
Project Summary:
LiftKit 3 was developed as a tool to calculate lift coefficients for non-uniform airfoils used in the ROSE project. The system, mounted on a vehicle, utilized sensors to measure lift and airspeed, allowing for the creation of lift-to-airspeed graphs. This data was crucial for refining aircraft performance and served as a practical substitute for traditional wind tunnel testing.
Highlights and Insights Gained:
- Gained hands-on experience in sensor integration and data collection.
- Improved skills in data analysis and graph generation for aerodynamic performance.
- Applied theoretical knowledge in aerodynamics to real-world testing scenarios.
- Developed innovative solutions for testing airfoil performance outside of a wind tunnel.
Collecting and analyzing data
Driving and Collecting Data: The data collection process involved mounting the airfoil testing system on top of a vehicle and driving at various speeds. As the vehicle moved, the system recorded lift values through a force sensor and airspeed data through a dedicated airspeed sensor. This real-time data collection was crucial for capturing how the airfoil performed under actual conditions, allowing for a detailed analysis of its aerodynamic properties.
Handling Different Polling Rates with MATLAB: Once the data was collected, it needed to be adjusted to account for the different polling rates of the sensors. This was done using a MATLAB program, which synchronized the data streams from the force sensor and the airspeed sensor. By ensuring that both datasets were aligned, the program provided accurate, usable data for further analysis.
Calculating Lift Coefficients: With the synchronized data in hand, the next step was to calculate the lift coefficient for the airfoil. The MATLAB program processed the data, incorporating variables such as the airfoil's cross-sectional area, air density, and angle of attack. The results were then cross-referenced with data from a CLARK Y airfoil, a standard reference model, to validate the assumptions and calculations. This process allowed for accurate approximations of the airfoil's lift characteristics.
Rose Project Summary
The design is based on a lever system, where the airfoil is mounted in such a way that, when the vehicle is stationary, the lever is perfectly balanced, and the force sensor beneath the airfoil reads zero. As the vehicle drives and air flows over the airfoil, lift is generated, causing the lever to rise on one side. The force sensor records these changes, capturing lift values at different airspeeds.
An airspeed sensor located beneath the airfoil works in tandem with the force sensor, collecting data that, when combined, allows us to establish a relationship between airspeed and lift. Before each test, the airfoil's angle of attack is measured and can be adjusted between tests to explore different aerodynamic conditions. This setup enables us to generate comprehensive data, mapping out the lift produced at varying airspeeds and angles of attack.
Once the data is collected, it is adjusted to account for the different polling rates of the sensors. This synchronization ensures accuracy in the results. We then plot a graph of airspeed versus lift, which, after linearization and incorporating factors such as the airfoil's cross-sectional area, air density, and angle of attack, allows us to calculate the lift coefficient for the airfoil.
This method is particularly advantageous for testing complex airfoils with dynamic or inconsistent angles of attack, as well as for evaluating the performance of flaps and other control surfaces. By providing reliable data that can be directly applied to the project, this system serves as an effective and practical alternative to the challenges and costs associated with large-scale wind tunnel testing.