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Volumn 44, Issue 3, 2008, Pages 357-366

Combined application of pressure sensitive paint and particle image velocimetry to the flow above a delta wing

Author keywords

[No Author keywords available]

Indexed keywords

FLOW MEASUREMENT; VORTEX FLOW;

EID: 39149136190     PISSN: 07234864     EISSN: None     Source Type: Journal    
DOI: 10.1007/s00348-007-0445-5     Document Type: Article
Times cited : (20)

References (17)
  • 1
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    • Experimental surface pressure data obtained on 65° delta wing across Reynolds number and Mach number ranges
    • Chu J, Luckring JM (1996) Experimental surface pressure data obtained on 65° delta wing across Reynolds number and Mach number ranges, NASA TM 4645
    • (1996) NASA TM , vol.4645
    • Chu, J.1    Luckring, J.M.2
  • 3
    • 33845423357 scopus 로고    scopus 로고
    • Effects of boundary layer formation on the vortical flow above Slender Delta Wings
    • RTO specialists' meeting on enhancement of NATO military flight vehicle performance by management of interacting boundary layer transition and separation, Prague, Czech Republic, 4-7 October 2004
    • Hummel D (2004) Effects of boundary layer formation on the vortical flow above Slender Delta Wings, RTO specialists' meeting on enhancement of NATO military flight vehicle performance by management of interacting boundary layer transition and separation, Prague, Czech Republic, 4-7 October 2004, Meeting Proceedings RTO-MP-AVT-111, pp 30-1 to 30-22
    • (2004) Meeting Proceedings RTO-MP-AVT-111
    • Hummel, D.1
  • 5
    • 33845403580 scopus 로고    scopus 로고
    • A new vortex flow experiment for computer code validation
    • RTO AVT symposium on vortex flow and high angle of attack aerodynamics, Loen, 7-11 May 2001 SYA 8-1 to 8-31
    • Hummel D, Redeker G (2003) A new vortex flow experiment for computer code validation, RTO AVT symposium on vortex flow and high angle of attack aerodynamics, Loen, 7-11 May 2001, Meeting Proceedings RTO-MP-069 (I), SYA 8-1 to 8-31
    • (2003) Meeting Proceedings RTO-MP-069 (I)
    • Hummel, D.1    Redeker, G.2
  • 6
    • 24144448605 scopus 로고    scopus 로고
    • Application of pressure-sensitive paint for determination of the pressure field and calculation of the forces and moments of models in a wind tunnel
    • Klein C, Engler RH, Henne U, Sachs W (2005) Application of pressure-sensitive paint for determination of the pressure field and calculation of the forces and moments of models in a wind tunnel. Exp Fluids 39:475-483
    • (2005) Exp Fluids , vol.39 , pp. 475-483
    • Klein, C.1    Engler, R.H.2    Henne, U.3    Sachs, W.4
  • 7
    • 33845444295 scopus 로고    scopus 로고
    • Development of PSP technique for application on the VFE-2 65° delta wing configuration in sub- and transonic flow
    • Klein C, Sachs W, Henne U, Engler RH, Wiedemann A, Konrath R (2006) Development of PSP technique for application on the VFE-2 65° delta wing configuration in sub- and transonic flow, AIAA-Paper 2006-0059
    • (2006) AIAA-Paper 2006-0059
    • Klein, C.1    Sachs, W.2    Henne, U.3    Engler, R.H.4    Wiedemann, A.5    Konrath, R.6
  • 8
    • 34250759802 scopus 로고    scopus 로고
    • Analysis of PSP results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speed
    • Konrath R, Klein C, Engler RH, Otter D (2006a) Analysis of PSP results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speed, AIAA-Paper 2006-0060
    • (2006) AIAA-Paper 2006-0060
    • Konrath, R.1    Klein, C.2    Engler, R.H.3    Otter, D.4
  • 9
    • 33845428022 scopus 로고    scopus 로고
    • Analysis of PIV results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speeds
    • Konrath R, Schröder A, Kompenhans J (2006b) Analysis of PIV results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speeds, AIAA-Paper 2006-3003
    • (2006) AIAA-Paper 2006-3003
    • Konrath, R.1    Schröder, A.2    Kompenhans, J.3
  • 10
    • 2942715250 scopus 로고    scopus 로고
    • Compressibility and leading-edge bluntness effects for a 65° delta-wing
    • Luckring JM (2004a) Compressibility and leading-edge bluntness effects for a 65° delta-wing. AIAA Paper 2004-0765
    • (2004) AIAA Paper 2004-0765
    • Luckring, J.M.1
  • 11
    • 78149428493 scopus 로고    scopus 로고
    • Reynolds number, compressibility, and leading-edge bluntness effects on delta-wing aerodynamics
    • Paper 4.1.4
    • Luckring JM (2004b) Reynolds number, compressibility, and leading-edge bluntness effects on delta-wing aerodynamics, ICAS Proceedings, Paper 4.1.4
    • (2004) ICAS Proceedings
    • Luckring, J.M.1
  • 13
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    • Iterative image deformation methods in PIV
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    • (2002) Meas Sci Technol , vol.13
    • Scarano, F.1
  • 17
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    • Stereoscopic digital particle image velocimetry for application in wind tunnel flows
    • Willert C (1997) Stereoscopic digital particle image velocimetry for application in wind tunnel flows. Meas Sci Technol 8:1465-1479
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    • Willert, C.1


* 이 정보는 Elsevier사의 SCOPUS DB에서 KISTI가 분석하여 추출한 것입니다.