An Experimental Investigation of the Flow Field Around a Yawed Cone PDF Download
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Author: Robert H. Feldhuhn Publisher: ISBN: Category : Cone Languages : en Pages : 106
Book Description
An experimental investigation of the flow field associated with a highly yawed cone was conducted at a Mach number of 5 and a free-stream Reynolds number per foot of 4,400,000. Surface static pressure measurements, flow-field surveys and schlieren photographs were obtained on a sharp five-degree semi-vertex angle cone at an angle of attack of 24 degrees. The results of the measurements indicate that the flow field on the leeward side of a highly yawed cone is very similar to that of a circular cylinder in supersonic cross flow. The essential difference between these two flow fields is the presence of a disturbance from the tip of the cone which separates the gas which has passed through the shock wave on the windward side from the flow which has passed through the weaker portion of the shock wave on the leeward side of the cone. (Author).
Author: Robert H. Feldhuhn Publisher: ISBN: Category : Cone Languages : en Pages : 106
Book Description
An experimental investigation of the flow field associated with a highly yawed cone was conducted at a Mach number of 5 and a free-stream Reynolds number per foot of 4,400,000. Surface static pressure measurements, flow-field surveys and schlieren photographs were obtained on a sharp five-degree semi-vertex angle cone at an angle of attack of 24 degrees. The results of the measurements indicate that the flow field on the leeward side of a highly yawed cone is very similar to that of a circular cylinder in supersonic cross flow. The essential difference between these two flow fields is the presence of a disturbance from the tip of the cone which separates the gas which has passed through the shock wave on the windward side from the flow which has passed through the weaker portion of the shock wave on the leeward side of the cone. (Author).
Author: Hyun Jin Kim Publisher: ISBN: Category : Aerospace engineering Languages : en Pages : 506
Book Description
An experimental investigation has been carried out on the flow transitions around a smooth circular cylinder in the initial stage of the critical Reynolds number region, where drag coefficient starts to decrease. In this Reynolds number region, intermitent reattachment of the separated boundary layer was found, while only initial separation position excursion was observed in the subcritical region. Large spanwise variations in the surface pressure and wake velocity observed in the first critical subregion were associated with local wake width pulsations caused by spanwise phase variations in the unsteady flow reattachment.
Author: Robert H. Feldhuhn Publisher: ISBN: Category : Angle of attack (Aerodynamics) Languages : en Pages : 148
Book Description
Pressure, heat transfer, force, flow field surveys and flow visualization measurements on an inclined cone were obtained in a wind tunnel at a nominal Mach number of 6. Force measurements were also obtained for a 2/3 power law body and two ducted-cone configurations.
Author: Donald E. Gault Publisher: ISBN: Category : Air flow Languages : en Pages : 70
Book Description
Results are presented from an investigation of regions of separated flow caused by separation of the laminar boundary layer (laminar-separation "bubbles"). The investigation was undertaken to obtain measurements which would define a large number of these bubbles for a wide range of Reynolds numbers and pressure gradients. In this manner, existing physical interpretations of the flow along a bubble could be studied in greater detail than in the past and, at the same time, it was hoped that the data would provide further insight into the conditions which control the occurrence and extent of a bubble.
Author: Alois T. Sutor Publisher: ISBN: Category : Airplanes Languages : en Pages : 706
Book Description
Analytical expressions are derived to show the geometric, thermodynamic, and aerodynamic relations among compressor, turbine, and exhaust nozzle for a gas-turbine engine. For a known compressor performance map, a matching method is described to show some of the design compromises that must be made when the components are to be combined into a turbine-propeller engine. A method of predicting engine performance for a range of operating conditions from known component maps is presented. An illustrative example of the matching method and the performance analysis is presented, showing some of the practical limitations of engine operation.
Author: Robert H. Feldhuhn
Author: Robert H. Feldhuhn
Author: Hyun Jin Kim
Author: United States. National Advisory Committee for Aeronautics
Author: Robert H. Feldhuhn
Author: Donald E. Gault
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: 
Author: Alois T. Sutor