Handbook of supersonic aerodynamics. Section 20. Wind tunnel instrumentation and operation

doi:10.1016/0016-0032(61)90593-2

Cited by 4 publications

References 8 publications

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Diamond port jet interaction with supersonic flow

樊怀国

张春晓

何川

2005

Appl. Math. Mech.-Engl. Ed.

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Interaction flow field of the sonic air jet through diamond shaped orifices at different incidence angles (10 degrees, 27. 5 degrees, 45 degrees and 90 degrees) and total pressures (0. 10 MPa and 0.46 MPa) with a Mach 5.0 freestream was studied experimentally. A 90 degrees circular injector was examined for comparison. Crosssection Mach number contours were acquired by a Pitot-cone five-hole pressure probe.The results indicate that the low Mach semicircular region close to the wall is the wake region. The boundary layer thinning is in the areas adjacent to the wake. For the detached case, the interaction shock extends further into the freestream, and the shock shape has more curvature, also the low-Mach upwash region is larger. The vortices of the plume and the height of the jet interaction shock increase with increasing incidence angle and jet pressure. 90 degrees diamond and circular injector have stronger plume .vorticity, and for the circular injector low-Mach region is smaller than that for the diamond injector. Tapered ramp increases the plume vorticity, and the double ramp reduces the level of vorticity. The three-dimensional interaction shock shape was modeled from the surface shock shape, the center plane shock shape, and crosssectional shock shape. The shock total pressure was estimated with the normal component of the Mach number using normal shock theory. The shock induced total pressure losses decrease with decreasing jet incidence angle and injection pressure, where the largest losses are incurred by the 90 degrees, circular injector.

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Diamond port jet interaction with supersonic flow

樊怀国

张春晓

何川

2005

Appl. Math. Mech.-Engl. Ed.

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Three-Component Force Measurements for Scramjet Engines 2) Effects of External Flow and Boundary Layer Ingestion

Mitani¹,

Tarukawa²,

Izumikawa³

et al. 2003

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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In the engine wind tunnels, the test cell pressure does not coincide with the nozzle static pressure and the forces (thrust, lift and pitching moment) are influenced by change of the nozzle pressure ratio. In order to separate effects by the external flow from the force measurement, experiments were conducted by using M3.4 and M5.4 subscale wind tunnels. The three component force was measured by a force balance and the effects of the external flow were investigated by controlling of the nozzle pressure ratio. Measurements of the engine wall pressure enabled to itemize the force distribution delivered by the engine internal flow. The results showed that the external drag of engine occupied from 36% to 70% of the total drag. The nozzle pressure ratio varied the drag coefficient by more than 20% in the M3.4 wind tunnel and greatly influenced the lift and the pitching moment. The boundary layer ingestion promoted the engine unstart especially in higher Mach number testing. The inlet wall pressure was lowered and the pressure distribution was smeared by the ingestion of boundary layer. However, it was found that the engine drag was not affected by it under the operation condition far from the engine unstart.

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Ring-Force Balance System for Small Wind Tunnels

Iwakawa

Osuka

Shoda

et al. 2015

AEROSPACE TECHNOLOGY JAPAN

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A ring-force balance system for a supersonic wind tunnel with a small test section was developed. This force balance system can measure an applied force independently by measuring the strain on the ring part. A theoretical analysis of this system was conducted under three conditions: an infinitesimally thin ring-force balance, a ring-force balance with finite thickness, and a ring-force balance with a support arm. From the analytical results, the azimuthal location, where the strain is zero for certain force components, varied based on the balance characteristics, such as the thickness or diameter of the ring part. A ring-force balance, which is based on this analysis, was designed and fabricated. The calibrated results showed that the designed balance was able to measure the force components with high accuracy and minimal interaction.

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Handbook of supersonic aerodynamics. Section 20. Wind tunnel instrumentation and operation

Cited by 4 publications

References 8 publications

Diamond port jet interaction with supersonic flow

Diamond port jet interaction with supersonic flow

Three-Component Force Measurements for Scramjet Engines 2) Effects of External Flow and Boundary Layer Ingestion

Ring-Force Balance System for Small Wind Tunnels

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