Figure 1 Flush Airdata Sensing

Figure 1:  Mechanical Air Data Boom tested in 4x4 tunnel

Air data can be acquired by mean of mechanical probes protruding from the airframe. In many cases was also possible to find a placement for the probe that is out of the body modified airfield. Very common is the nose mounted air data boom. In Figure 1 you find one mechanical air data boom tested within a wind tunnel in 1958 (Source: NASA).

Mechanical Air Data Booms are able to reach a notable degree of accuracy and are used in some modern applications, you see a miniature mechanical Air Data Boom mounted on the Terrafugia prototype in Figure 2.

Figure 2 Flush Airdata SensingFigure 2: SpaceAge Control miniature 100400 Air Data Boom

Apart the weight and the size, this solution should deal with its intrinsic mechanical nature, mechanical-friction, inertia and robustness consideration are of high impact on overall probe design and performances. Mechanical related problems are exalted in both at low and high airspeed. At low airspeed, we have a low aerodynamic force to win the wind vanes frictions. At high airspeed, the aerodynamic damp of the wind vane will decrease and can lead to an unacceptable dynamic behavior. Anyway, an alternative to the classical probes is to reconstruct wind direction using multiple pressure readings. That defines two big families of probes the first is the so-called Multi Holes Probes and the second the Flush Airdata Sensors.

Figure 3 Aeroprobe-Micro-ADC Flush Airdata SensingFigure 3: Aeroprobe ADC with 6 holes MHP

With a classical probe, the information on wind direction is available directly from the two wind vanes angular sensors signal, in a pressure based system that information should be reconstructed from different pressure readings. Refer for example to the commercial MHP of Figure 3. On this probe tip, there are presents six different pressure ports. There is a central hole that can give exactly the same pressure reading of that measured by the total pressure hole of a Pitot-Static probe. There is an annular pressure port, at a certain distance from the probe tip, that measures the static pressure; in a similar way of the Pitot-Static probe static port. There are 4 supplementary holes on the probe head. They can be used, for example, but not only, in couples to determine the angle of attack and the angle of sideslip. Data reduction algorithms can use the combined data from all the six pressure taps to reconstruct

\(P_t\) Total pressure or impact pressure
\(P_s\) Static pressure
\(\alpha\) Angle of attack
\(\beta\) Angle of sideslip

The pressure at ports is correlated to the relative wind magnitude and direction, you find a developed example of the angle of attack measurement case in this link. This kind of probes is used usually in many research and industry fields, including turbomachinery. MHP probes can reach dimensions under the 6 mm diameter.

FADS are similar under many aspects to MHP but the probe surface is usually one airframe surface exposed directly to the air stream. In many cases, the sensor openings are over a modified nose cone. Refer to Figure 4, here you find a FADS system; description of the system here.

FIGURE 4 b23_f3-1a Flush Airdata Sensing
Figure 4:  NCAR Sabreliner aircraft equipped with both the differential pressure probe and the radome with pressure ports

This kind of probe is commonly used in research applications. Many studies were conducted by Langley NASA research center for the shuttle space program [page 6]. Dryden Flight Research center continued the work and produced different interesting articles. You can find notable information within this NASA work or in this work on X-33 FADS. Regarding real time data reduction consideration please consider that other article.

Both the families of probes can reach notable performances. Calibration, both aerodynamic and of single pressure sensors, and reduction algorithms for the FADS can pose a more that respectable practical problem. I've no notice, to date, of any DIY probe of that kind. It is to be noted that DIY aircraft have reduced flight speeds, that signifies that magnitude of pressures measured or differential measured differential pressure is really of small value; for a medium demanding application, we may need to have pressure measurements accurate to about a Pa. It's clear that an extremely well-calibrated measurement hardware is needed. It seems neither easy nor cheap to go under one degree of overall accuracy on AOA measurement. As many users are interested in the topic we will develop it in time and publish the results online. For the same reason if you think you can contribute to development please enter in contact with us.

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Comment by Jerry Giant on July 25, 2016 at 9:53am

i always wanted a mems magnetic angular sensor to do this. glad some people are building something in this interest.

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