Interacllon of supersonic wing tip vortices with a normal shock

Iraj M. Kalkhoran, Michael K. Smart, Alexander Betti

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

An experimental study involving interaction of concentrated streamwise wing tip vortices and normal shock fronts was carried out in a Mach 2.49 flow. The interaction scheme involved positioning a vortex-generator wing section upstream of a pitot type normal shock inlet such that the wing tip vortices interacted with the normal shock formed in front of the inlet. The vortex strength was varied by placing the vortex generator wing at different angles of attack while a normal shock was created by adjusting the mass flow rate passing through the inlet. Spark shadowgraphs, laser sheet planar visualizations, and pitot pressure measurements of the flowfield indicated a significant change in the structure of streamwise vortices generated by the vortex generator wing at 5 and 10 degrees angle of attack upon encountering a normal shock discontinuity. Results of the investigation showed that the interactions lead to the formation of an unsteady conical shock wave far upstream of the inlet as well as a highly turbulent flow downstream for both vortices. Pitot pressure measurements using a fast response pressure transducer in conjunction with the spark shadowgraphs revealed a bimodal feature of the flowfield. The frequency of oscillation of the generated structure was found to be higher for increased vortex strength.

Original languageEnglish (US)
Title of host publicationFluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-13
Number of pages13
StatePublished - 1995
EventFluid Dynamics Conference, 1995 - San Diego, United States
Duration: Jun 19 1995Jun 22 1995

Other

OtherFluid Dynamics Conference, 1995
CountryUnited States
CitySan Diego
Period6/19/956/22/95

Fingerprint

Vortex flow
Gas generators
Angle of attack
Pressure measurement
Electric sparks
Pressure transducers
Shock waves
Mach number
Turbulent flow
Visualization
Flow rate
Lasers

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology

Cite this

Kalkhoran, I. M., Smart, M. K., & Betti, A. (1995). Interacllon of supersonic wing tip vortices with a normal shock. In Fluid Dynamics Conference (pp. 1-13). American Institute of Aeronautics and Astronautics Inc, AIAA.

Interacllon of supersonic wing tip vortices with a normal shock. / Kalkhoran, Iraj M.; Smart, Michael K.; Betti, Alexander.

Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 1995. p. 1-13.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Kalkhoran, IM, Smart, MK & Betti, A 1995, Interacllon of supersonic wing tip vortices with a normal shock. in Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, pp. 1-13, Fluid Dynamics Conference, 1995, San Diego, United States, 6/19/95.
Kalkhoran IM, Smart MK, Betti A. Interacllon of supersonic wing tip vortices with a normal shock. In Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA. 1995. p. 1-13
Kalkhoran, Iraj M. ; Smart, Michael K. ; Betti, Alexander. / Interacllon of supersonic wing tip vortices with a normal shock. Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 1995. pp. 1-13
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