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Chan, Y.S. (author)
report 2002
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Chan, Y.S. (author)
report 2002
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Chan, Y.S. (author)
report 2002
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Chan, Y.S. (author)
report 2001
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Chan, Y.S. (author)
report 2001
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Ohman, L.H. (author), Brown, D. (author), Chan, Y.Y. (author), Galway, R.D. (author), Hashim, S.M. (author), Khalid, M. (author), Malek, A. (author), Mokry, M. (author), Tang, N. (author), Thain, J. (author)
The NAE 5ftx5ft blowdown wind tunnel has undergone a major upgrade of its transonic testing capabilities. Two entirely new test sections, one for testing two-dimensional models (2D) and one for testing three-dimensional models and reflection plane models (3D), have been constructed. The two test sections are parts of the so-called Roll-in Roll...
report 1990
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Chan, Y.Y. (author)
The experimental investigation of CAST 10-2/DOA 2 supercritical airfoil previously conducted in the NAE Two-Dimensional Test Facility has been extended to low Reynolds number range at the design Mach number 0.765. The results indicate that with forward transition fixing, the data trend at low Reynolds number is different from that at high...
report 1989
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Chan, Y.Y. (author)
The effects on aerodynamic performance of a supercritical airfoil applying disk or grit tripping for boundary layer transition has been investigated for a typical supercritical airfoil at transonic speeds. It is observed that by allowing the laminar flow passing through the space between the disks, transition takes place a short distance...
report 1988
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Chan, Y.Y. (author)
Experimental data obtained in the NAE Two-Dimensional Test Facility for CAST 10-2jDOA2 supercritical airfoil have been analyzed for the effects of Reynolds number, transition fixing and Mach number. The data were obtained for Reynolds numbers from 6 to 30 million and Mach numbers from 0.3 to 0.8 with fixed and free transitions. The analysis...
report 1988
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Chan, Y.Y. (author)
The experimental study of the transonic equivalence rule with lift, previously reported in Reference 1, has been extended to include a configuration of swept-back wing-body and the corresponding equivalent bodies for lift and zero-lift. For zero lift, the wing-body is shown to have higher wave drag than that of the equivalent body. At lifting...
report 1984
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Chan, Y.Y. (author)
The transonic equivalence rule with lift has been studied experimentally. Under the conditions defined by the rule, wing-body models with the same cross-sectional area distribution but with wings of different aspect ratios and thicknesses were tested at transonic speeds. The correlations of the lift depending wave drag and the lift parameter for...
report 1982
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Chan, Y.Y. (author)
The wind tunnel wall interference in transonic speed is formulated as a perturbation to the basic flow around the airfoil in free air. The perturbation equation is derived from the transonic small disturbance equation and is linear but with variabie coefficients containing the non-linear solution of the basic flow. The equation is solved...
report 1979
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Consigny, H. (author), Chan, C.K. (author), Richards, B.E. (author)
This note presents measurements of heat transfer to a cold surface at conditions simulating advanced aircraft gas turbine flow conditions. They were obtained under isothermal wall conditions in a short duration isentropic light piston tunnel using surface temperature transient techniques. The effects of external turbulence and strong favourable...
report 1979
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Chan, Y.Y. (author)
This report gives the detailed analysis of the nonlinear development of a spatial-growth wave disturbance in the turbulent shear layer of a circular jet. A concise version of the present problem has been published in the Physics of Fluids (Ref. 2). The method of analysis is based on the global consideration of the energy transfer between the...
report 1975
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Chan, Y.Y. (author), Leong, R.K. (author)
The linear spatial stability of a compressible thin turbulent wake bound by two side walls is analyzed by the stability theory of an inviscid shear flow. The disturbance propagating in the wake is assumed to be three-dimensional. For free stream Mach numbers up to 2 the analysis shows that in the high frequency region the most unstable mode of...
report 1974
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Chan, S.K. (author)
report 1973
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Chan, Y.Y. (author)
Based on the data of near field surveys of the sound pressure from a choked jet, a simple model is proposed for the mechanism of the screech generation. A convected wave propagates downstream along the jet boundary and is modulated by its interaction with the shock-expansion waves of the jet. These interactions generate strongdipoleradiations....
report 1972
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Chan, Tzeng-Long (author), Kennedy, John F. (author)
report 1972
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Chan, Y.Y. (author), Gower, A.R. (author), Kolanko, R. (author)
The momentum integral method for laminar boundary layers according to Loitsianskii' s universal equations approach has been extended to compressible flows with mass transfers. The universal forms of the compressible boundary layer equations are derived and series solutions in terms of the pressure gradient and the mass transfer parameters are...
report 1971
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Chan, Y.Y. (author)
The extended mixing length formulation for the computation of incompressible turbulent boundary layers has been applied with success to flows over rough surfaces. The roughness effect is introduced into the computation scheme through the boundary conditions by defining a slip velocity at the surface. The method predicts the mean velocity and the...
report 1971
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