난류 구체 방식: 풍동 흐름 품질 평가
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Overview
출처: 호세 로베르토 모레토와 샤오펑 리우, 항공 우주 공학부, 샌디에고 주립 대학, 샌디에고, 캘리포니아
풍동 테스트는 사용 중에 공기 흐름을 받는 차량 및 구조물의 설계에 유용합니다. 풍동 데이터는 연구 중인 물체의 모델에 제어된 공기 흐름을 적용하여 생성됩니다. 테스트 모델은 일반적으로 유사한 형상을 가지고 있지만 전체 크기의 개체에 비해 작은 축척입니다. 저속 풍동 테스트 중에 정확하고 유용한 데이터가 수집되도록 테스트 모델과 전체 크기의 물체에 대한 실제 유동 필드 간에 레이놀즈 수의 동적 유사성이 있어야 합니다.
이 데모에서는 흐름 특성이 잘 정의된 매끄러운 구를 통해 풍동 흐름을 분석합니다. 구는 잘 정의된 유동 특성을 가지고 있기 때문에, 효과적인 레이놀즈 수와 테스트 레이놀즈 수의 상관관계가 있는 풍동의 난기류 계수는 풍동의 자유 스트림 난류 강도를 결정할 수 있다.
Principles
Procedure
Results
For each sphere, the stagnation pressure and the pressure at the aft ports were measured. The difference between these two values gives the pressure difference, ΔP. The total pressure, Pt, and static pressure, Ps, of the test section were also measured, which are used to determine the test dynamic pressure, q = Pt – Ps, and the normalized pressure 
. The ambient air pressure, Pamb, and the airflow temperature was also recorded to calculate the air flow properties, including the air density, ρtest, and viscosity, μtest. The density is obtained using the ideal gas law, and the viscosity is obtained using Sutherland's formula. Once the air density and viscosity are determined, the test Reynolds number can be computed.
By plotting the test Reynolds number with respect to the normalized pressure difference, the critical Reynolds number for each sphere was determined (Figure 1). The critical Reynolds number corresponds to a normalized pressure value of = 1.220. The three curves for the three spheres provide a more accurate estimate of the critical Reynolds number, ReCtunnel, because an averaged value is used. With the ReCtunnel estimate, the turbulence factor, TF, and the effective Reynolds number can be determined according to the following equations:
and
Figure 1. Critical Reynolds number for each sphere.
Applications and Summary
Turbulence spheres are used to determine wind tunnel turbulence factor and estimate the turbulence intensity. This is a very useful method to evaluate a wind tunnel flow quality because it is simple and efficient. This method does not directly measure the air velocity and velocity fluctuations, such as hotwire anemometry or particle image velocimetry, and it cannot provide a complete survey of the flow quality of the wind tunnel. However, a complete survey is extremely cumbersome and expensive, so it is not suitable for periodic checks of the wind tunnel turbulence intensity.
The turbulence factor can be checked periodically, such as after making minor modifications to the wind tunnel, to gauge the flow quality. These quick checks can indicate the necessity of a complete flow turbulence survey. Other important information obtained from the turbulence factor is the effective Reynolds number of the wind tunnel. This correction on the Reynolds number is important to ensure the dynamic similarity and the usefulness of data obtained from scaled models and their application to full-scale objects.
The turbulence sphere principle can be also used to estimate the turbulence level in other environments besides the wind tunnel test section. For example, this method can be used to measure inflight turbulence. A turbulence probe can be developed based on the principles of the turbulence sphere and installed in airplanes to measure turbulence levels in the atmosphere in real-time [2].
Another application is the study of flow structures during a hurricane. In situ measurements of the flow inside a hurricane can be extremely dangerous and complicated to obtain. Methods like hotwire anemometry and particle image velocimetry are unattainable in these conditions. The turbulence sphere principle can be used to make an expendable measurement system which can be placed in a region prone to hurricanes to measure the flow turbulence inside a hurricane safely and at a low cost [3].
| Name | Company | Catalog Number | Comments |
| Equipment | |||
| Low-speed wind tunnel | SDSU | Closed return type with speeds in the range 0-180 mph | |
| Test section size 45W-32H-67L inches | |||
| Smooth spheres | SDSU | Three spheres, diameters 4", 4.987", 6" | |
| Miniature pressure scanner | Scanivalve | ZOC33 | |
| Digital Service Module | Scanivalve | DSM4000 | |
| Barometer | |||
| Manometer | Meriam Instrument Co. | 34FB8 | Water manometer with 10" range. |
| Thermometer |
References
- Barlow, Rae and Pope. Low speed wind tunnel testing, John Wiley & Sons, 1999.
- Crawford T.L. and Dobosy R.J. Boundary-Layer Meteorol. 1992. 59; 257-78.
- Eckman R.M., Dobosy R.J., Auble D.L., Strong T.W., and Crawford T.L. J. Atmos. Ocean. Technol. 2007; 24; 994-1007.
Transcript
In aerodynamics testing, wind tunnels are invaluable to determining the aerodynamic properties of various objects and scaled aircraft. Wind tunnel data is generated by applying a controlled flow of air to a testing model, which is mounted inside the test section. The testing model typically has similar geometry, but at a smaller scale, as compared to the real object.
In order to ensure usefulness of the data generated in wind tunnel tests, we must ensure dynamic similarity between the wind tunnel flow field and the actual flow field over the real object. To maintain dynamic similarity, the Reynolds number of the wind tunnel experiment must be the same as the Reynolds number of the flow phenomenon being tested.
However, experiments performed in wind tunnels or in free-air even with the same test Reynolds number can provide different results due to the effects of free-stream turbulence inside the wind tunnel test section. These differences may be perceived as a higher effective Reynolds number for the wind tunnel. So how do we correlate testing in the wind tunnel to free-air experiments?
We can estimate the intensity of the free-stream turbulence in the wind tunnel using a well-defined object with known flow behavior, like a sphere. This method is called the turbulence sphere method. The turbulence sphere method relies on the well-studied condition called the sphere drag crisis.
The sphere drag crisis describes the phenomenon where the drag coefficient of a sphere suddenly drops as the Reynolds number reaches a critical value. When the flow reaches the critical Reynolds number, the boundary layer transitions from laminar to turbulent very close to the leading edge of the sphere. This transition, as compared to flow at a low Reynolds number, causes delayed flow separation and a thinner turbulent wake and thus decreased drag.
Therefore, we can measure the drag coefficient of a sphere at a range of test Reynolds numbers to determine the critical Reynolds number. This enables us to determine the turbulence factor, which correlates the test Reynolds number to the effective of Reynolds number.
In this experiment, we will demonstrate the turbulence sphere method using a wind tunnel and several different turbulence spheres with built-in pressure taps.
This experiment utilizes an aerodynamic wind tunnel as well as several turbulence spheres with varying diameter to determine the turbulence level of the free-stream flow in the tunnel test section. The turbulence spheres, each with a pressure tap at the leading edge as well as 4 pressure taps located 22.5° from the trailing edge, have well-defined flow characteristics, which help us analyze turbulence in the wind tunnel.
To set up the experiment, first connect the wind tunnel pitot tube to pressure scanner port number 1. Then, connect the wind tunnel static pressure port to port number 2. Now, lock the external balance. Fix the sphere strut in the balance support inside the wind tunnel.
Then, install the 6 in sphere. Connect the leading edge pressure tap to the pressure scanner port number 3 and connect the four aft pressure taps to port 4. Connect the air supply line to the pressure regulator, and set the pressure to 65 psi. Then, connect the manifold of the pressure scanner to the pressure line regulated at 65 psi.
Start up the data acquisition system and pressure scanner. While the system equilibrates, estimate the maximum dynamic pressure, q max, necessary for the test based on the free-air critical Reynolds number for a smooth sphere.
Here, we list the recommended test parameters for the first and second test of each sphere. Now, using these parameters, define the dynamic pressure test range from zero to q max, and then define the test points by dividing the range into 15 intervals.
Before running the experiment, read the barometric pressure in the room and record the value. Also, read the room temperature and record its value. Apply the corrections to the barometric pressure using the room temperature and the geolocation using equations supplied by the manometer manufacturer.
Now, set up the data acquisition software by first opening the scanning program. Then, connect the software DSM 4000, which reads and calibrates the signal from the pressure sensor, by setting the proper IP address and pressing connect. Insert the commands as shown, which are defined by the manufacturer, remembering to press enter after each command.
Now that the software is ready, check to make sure that the test section and wind tunnel are free from debris and loose parts. Then, close the test section doors and check to see that the wind tunnel speed is set to zero. Turn on the wind tunnel, and then turn on the wind tunnel cooling system.
With the wind speed equal to zero, start recording data on the data acquisition system, then type the command scan to start pressure measurement. Then, record the wind tunnel temperature. Since wind speed is directly related to the dynamic pressure, increase the wind speed until you reach the next dynamic pressure test point. Then, wait until the air speed stabilizes and commence the pressure scan again. Be sure to record the wind tunnel temperature. Continue the experiment by conducting a pressure scan at each of the dynamic pressure points, recording the wind tunnel temperature each time. When all points have been measured for the 6-inch sphere, repeat the stabilization and pressure scan experiment for the 4.987 inch and 4-inch turbulence spheres.
For each sphere, we measured the stagnation pressure at pressure port 3 and the pressure at the aft ports via pressure port 4, which are subtracted to give the pressure difference, delta P. We also measured the test section total pressure, Pt, from pressure port one and the static pressure, Ps, from pressure port two, which are used to determine the test dynamic pressure, q.
Then we can calculate the normalized pressure, which is equal to the pressure difference divided by the dynamic pressure. The air pressure and the airflow temperature were also recorded, enabling the calculation of airflow properties. Recall that there is a slot in the test section, meaning that it is open to ambient air. Therefore, assuming that there is no streamwise pressure gradient in the test section, the absolute value of the local static pressure of the free-stream flow can be used as the ambient air pressure.
The density is obtained using the ideal gas law and the viscosity obtained using Sutherland’s formula. Once the air density and viscosity have been determined, we can calculate the Reynolds number. Here we show a plot of the Reynolds number versus the normalized pressure difference, delta P over q.
Using this plot, we can determine the critical Reynolds number for each sphere, since the critical Reynolds number corresponds to a normalized pressure value 1.22. With each critical Reynolds number, we can evaluate the turbulence factor and the effective Reynolds number. The turbulence factor is correlated to the intensity of the turbulence in the wind tunnel.
In summary, we learned how the free-stream turbulence affects testing in a wind tunnel. We then used several smooth spheres to determine the turbulence factor and intensity of the wind tunnel flow and evaluate its quality.