Flight Development of the Avro CF-100 Mark 5 Aircraft

1958 ◽  
Vol 62 (566) ◽  
pp. 118-122 ◽  
Author(s):  
D. C. Whittley
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Aspect Ratio ◽  
Aerodynamic Characteristics ◽  
Vortex Generators ◽  
High Altitudes ◽  
Trailing Edge ◽  
Flap Deflection ◽  
Performance Gains

SummaryImprovements made to the aerodynamic characteristics of the wing of the Avro CF-100 Mark 5 aircraft are discussed. Modifications to the wing included increase in aspect ratio, addition of vortex generators, and deflection of trailing edge plain flaps. The effect of flap deflection and addition of vortex generators on the aerodynamic characteristics of the wing are shown to be closely associated with interaction of the upper surface shock wave with the boundary layer. Performance gains were demonstrated at high subsonic speeds at high altitudes. Vortex generators improved the buffet boundary, whereas flap deflection both increased aircraft ceiling and improved buffet boundary.

Shock-Wave/Boundary-Layer Interaction in a Large-Aspect-Ratio Test Section

AIAA Journal ◽  
2017 ◽  
Vol 55 (9) ◽  
pp. 2919-2928
Author(s):  
Miranda Pizzella ◽  
Sally Warning ◽  
Mary Jennerjohn ◽  
Mark McQuilling ◽  
Ashley Purkey ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Aspect Ratio ◽  
Test Section ◽  
Ratio Test ◽  
Large Aspect Ratio ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

Investigation of Shock Wave - Boundary Layer Interactions in a 3.57 Aspect Ratio Wind Tunnel

2014 ◽  
Author(s):  
Sally Warning ◽  
Miranda Turlin ◽  
Lyndel M. Carlson ◽  
Phillip Ligrani ◽  
Mark W. McQuilling
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Wind Tunnel ◽  
Aspect Ratio ◽  
Wave Boundary Layer ◽  
Wave Boundary

Experimental Characterization of the Vane Heat Flux Under Pulsating Trailing-Edge Blowing

2016 ◽  
Author(s):  
J. Saavedra ◽  
G. Paniagua ◽  
B. H. Saracoglu
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Shock Wave ◽  
Heat Flux ◽  
Wall Temperature ◽  
Separation Bubble ◽  
Convective Heat Transfer Coefficient ◽  
Trailing Edge ◽  
Power Extraction ◽  
The Impact

The steady improvement of aircraft engine performance has led towards more compact engine cores with increased structural loads. Compact single-stage high-pressure turbines allow high power extraction, operating in the low supersonic range. The shock waves formed at the airfoil trailing edge contribute substantially to turbine losses, mainly due to the shock-boundary layer interactions as well as high-frequency forces on the rotor. We propose to control the vane trailing edge shock interaction with the downstream rotor, using a pulsating vane-trailing-edge-coolant at the rotor passing frequency. A linear cascade of transonic vanes was investigated at different Mach numbers, ranging from subsonic to supersonic regimes (0.8, 1.1) at two engine representative Reynolds numbers (4 and 6 million). The steady and unsteady heat flux was retrieved using thin-film 2-layered gauges. The complexity of the tests required the development of an original heat transfer post-processing approach. In a single test, monitoring the heat flux data and the wall temperature we obtained the adiabatic wall temperature and the convective heat transfer coefficient. The right-running trailing edge shock wave impacts on the neighboring vane suction side. The impact of the shock wave on the boundary layer creates a separation bubble, which is very sensitive to the intensity and angle of the shock wave. Increasing the coolant blowing rate induces the shock to be less oblique, moving the separation bubble upstream. A similar effect is caused by the pulsations of the coolant.

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