Aerodynamics of Stream Thrust Probes

Hiers, Robert S.; Sirbaugh, J. R.; Sverdrup, Jacobs

doi:10.2514/6.2003-1092

Cited by 6 publications

(7 citation statements)

References 5 publications

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“…If the probe shape can automatically resolve the desired component of momentum, there would be no need to separately determine the flow angle. 2 Consider an axisymmetric pitot probe immersed in a flow of angle, α, as illustrated in Fig. 1.…”

Section: Introductionmentioning

confidence: 99%

“…Ideal, perfect gas behavior was assumed in order to illustrate the technique, which requires a probe shape that automatically compensates for flow direction. 2 A computational fluid dynamics (CFD) study compared the flow angle compensation characteristics of two proposed probe geometries. 2 In the present paper, the flow angle sensitivity of one of the probe shapes is investigated experimentally.…”

Section: Introductionmentioning

confidence: 99%

“…2 A computational fluid dynamics (CFD) study compared the flow angle compensation characteristics of two proposed probe geometries. 2 In the present paper, the flow angle sensitivity of one of the probe shapes is investigated experimentally. The probe nose shape is designed such that the measured pressure is proportional to the component of momentum along the probe axis over a broad range of flow angles.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Verification of the Aerodynamics of Stream Thrust Probes

Hiers

Sirbaugh

McCann

et al. 2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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Determining the local stream thrust (a vector quantity) from a measured pitot pressure (a scalar quantity) requires either knowledge of the flow direction or a probe shape that compensates for flow direction. This compensation ideally would make the measured pressure directly proportional to the component of momentum along the probe axis. The flow angle sensitivity required to resolve this component of momentum was previously determined theoretically. A proposed probe nose shape was analyzed using computational fluid dynamics (CFD) and was found to produce a flow angle sensitivity close to the required sensitivity. In the current work, the proposed nose shape was tested in a wind tunnel at Mach numbers 1.67, 2.45, and 3.48 at angles of attack from 0 to 15 deg. The test results indicate that the flow angle sensitivity of the proposed nose shape agrees with the required sensitivity to within 1 percent up to a flow angle of 15 deg.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Experimental Verification of the Aerodynamics of Stream Thrust Probes

Hiers

Sirbaugh

McCann

et al. 2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

Self Cite

View full text Add to dashboard Cite

show abstract

“…Ideal, perfect gas behavior was assumed to illustrate the technique, which requires a probe shape that automatically compensates for flow direction. 2 A CFD study compared the flow angle compensation characteristics of two proposed probe geometries. 2 The probe nose shape is designed such that the measured pressure is proportional to the component of momentum along the probe axis over a broad range of flow angles.…”

Section: Figure 1 Static Thrust Measurements (Refs 1 and 2)mentioning

confidence: 99%

“…2 A CFD study compared the flow angle compensation characteristics of two proposed probe geometries. 2 The probe nose shape is designed such that the measured pressure is proportional to the component of momentum along the probe axis over a broad range of flow angles. This is in contrast to the typical requirement for a pitot probe to be insensitive to flow angle.…”

Section: Figure 1 Static Thrust Measurements (Refs 1 and 2)mentioning

confidence: 99%

The Influence of Viscosity and Surface Curvature on the Pressure Distribution of a Stream Thrust Probe

Pasman

Cummings

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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Determining the local stream thrust (a vector quantity) from a measured pitot pressure (a scalar quantity) requires either knowledge of the flow direction, or a probe shape that compensates for flow direction. This compensation would ideally make the measured pressure directly proportional to the component of momentum along the probe axis. The flow angle sensitivity required to resolve this component of momentum was determined theoretically previously. A proposed probe nose shape was analyzed using CFD and found to produce flow angle sensitivity close to the required sensitivity. The proposed nose shape was also tested in a wind tunnel at Mach 1.67, 2.45, and 3.48 at angles of attack from 0 to 15 degrees. The test results indicate that the flow angle sensitivity of the proposed nose shape agrees with the required sensitivity to within 1% up to a flow angle of 15°. The current work extends the original theoretical development for the optimum nose shape to include viscous affects and surface curvature. The new second-order theory agrees well with experimental results for both the stream thrust probe as well as other, independent data. Further work can be done to refine the theory.

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