Experimental Studies of Laminar, Transitional, and Turbulent Hypersonic Flows Over Elliptic Cones at Angles of Attack PDF Download
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Author: Michael Holden
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ISBN:
Category :
Languages : en
Pages : 58
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An experimental study has been performed to examine the three-dimensional characteristics of laminar, transitional and turbulent flow over an elliptic cone lifting body configuration. The experimental studies were performed at Mach numbers between 8 and 12 at Reynolds numbers, based on model length from 5 x 10(exp 5) to 5 x 10(exp 6). Detailed measurements of the distribution of heating and pressure were made along the leading edges and on the windward and leeward surfaces of the model with over 200 high-frequency, thin-film heat transfer gages and piezoelectric high-frequency pressure transducers. Measurements were also performed using temperature sensitive paints to further delineate the properties of the three-dimensional transitional flow. Schlieren photographs were also obtained of the transitional flow field over the models. Flowfield calibration measurements were made in the LENS facility with intrusive pitot and total heating transducers and nonintrusive electron beam, and infrared radiometer techniques. These data have been incorporated into the CUBRC/AFOSR Hypersonic Database which has been modified to run on the Windows platform.
Author: Michael Holden
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
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Book Description
An experimental study has been performed to examine the three-dimensional characteristics of laminar, transitional and turbulent flow over an elliptic cone lifting body configuration. The experimental studies were performed at Mach numbers between 8 and 12 at Reynolds numbers, based on model length from 5 x 10(exp 5) to 5 x 10(exp 6). Detailed measurements of the distribution of heating and pressure were made along the leading edges and on the windward and leeward surfaces of the model with over 200 high-frequency, thin-film heat transfer gages and piezoelectric high-frequency pressure transducers. Measurements were also performed using temperature sensitive paints to further delineate the properties of the three-dimensional transitional flow. Schlieren photographs were also obtained of the transitional flow field over the models. Flowfield calibration measurements were made in the LENS facility with intrusive pitot and total heating transducers and nonintrusive electron beam, and infrared radiometer techniques. These data have been incorporated into the CUBRC/AFOSR Hypersonic Database which has been modified to run on the Windows platform.
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Category :
Languages : en
Pages : 0
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This work involved the study of instabilities and transition to turbulence in boundary layers on cones at different angles of attacks at high supersonic and hypersonic Mach numbers. It utilized facilities at NASA Langley Research Center, which makes use of 'quiet' design nozzles to minimize the level of acoustic disturbances. The experiments involved two models. The first was a 7 half-angle circular cross-section cone designed by Cavalier. It was used in experiments at zero angle of attack, where the principle instability is pairs of traveling oblique wave pairs; and at angles of attack where the principle instability is cross-flow modes. The circular cone at an angle of attack has a 3-D boundary layer, which is similar to that on elliptic cone, which was the second model built. This consisted of a 10 half-angle cone with a 4:1 elliptic cross-section. The elliptic cone was designed to operate in a new Mach 8 tunnel at NASA Langley. It mounts on a sting, which placed it inside the worst-case estimate on the location of the nozzle quiet zone. The model is annealed and hardened to withstand the 900 deg F free-stream temperature, and maintain a polished finish. A 3-D traversing mechanism capable of following the tapered elliptic surface, and operating at high temperatures in the hypersonic flow was also designed. Unfortunately, the elliptic cone was never used because of technical problems with the Mach 8 tunnel, which prevented it from ever operating. However, the elliptic cone was also designed to operate in the Mach 3.5 tunnel used for the circular cone experiments. A pending AFOSR proposal describes an experimental program for its use at the lower Mach number.
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ISBN:
Category :
Languages : en
Pages : 0
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Book Description
This work involved the study of instabilities and transition to turbulence in boundary layers on cones at different angles of attacks at high supersonic and hypersonic Mach numbers. It utilized facilities at NASA Langley Research Center, which makes use of 'quiet' design nozzles to minimize the level of acoustic disturbances. The experiments involved two models. The first was a 7 half-angle circular cross-section cone designed by Cavalier. It was used in experiments at zero angle of attack, where the principle instability is pairs of traveling oblique wave pairs; and at angles of attack where the principle instability is cross-flow modes. The circular cone at an angle of attack has a 3-D boundary layer, which is similar to that on elliptic cone, which was the second model built. This consisted of a 10 half-angle cone with a 4:1 elliptic cross-section. The elliptic cone was designed to operate in a new Mach 8 tunnel at NASA Langley. It mounts on a sting, which placed it inside the worst-case estimate on the location of the nozzle quiet zone. The model is annealed and hardened to withstand the 900 deg F free-stream temperature, and maintain a polished finish. A 3-D traversing mechanism capable of following the tapered elliptic surface, and operating at high temperatures in the hypersonic flow was also designed. Unfortunately, the elliptic cone was never used because of technical problems with the Mach 8 tunnel, which prevented it from ever operating. However, the elliptic cone was also designed to operate in the Mach 3.5 tunnel used for the circular cone experiments. A pending AFOSR proposal describes an experimental program for its use at the lower Mach number.
Author: Antonio Ferri
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 90
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: John C. Adams (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 124
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Application of three-dimensional inviscid and viscous (laminar boundary layer) analyses for cold wall hypersonic flows over sharp cones at incidence is presented relative to experimental data, showing surface upwash angles and entrained vortex formation leading to crossflow-induced boundary-layer transition. Three-dimensional neutral inviscid stability theory for stationary disturbances is used to calculate the angular orientation of the entrained vortices in the boundary layer while a maximum crossflow Reynolds number concept is applied for correlation of the onset to vortex formation due to crossflow instability.
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Category :
Languages : en
Pages : 0
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An elliptic cone similar to the one used by other investigators, a 4:1 aspect ratio elliptic cone with the cone angle on the major axis of 17.5 deg and 4.5 deg along the minor axis, in a Mach 2.8 tunnel was used in the present work. The Reynolds number used in this work was much higher than that used in other experimental work. The purpose is to examine the transition process as well as the turbulent structure of a three-dimensional boundary layer after transition. The primary focus of this study is on the structure of the turbulence, which was explored using advanced optical diagnostics. Both surface flow visualizations and Filtered Rayleigh Scattering (FRS) based flow visualizations were used in this study. The results showed that the boundary layer developing along the major centerline, the flattest region on the cone surface, underwent transition to turbulence approximately 35 mm downstream of the cone tip. Surface cross flow was observed primarily near the minor centerline of the cone, the area with the largest curvature. No cross flow was observed around the major centerline after 10 mm downstream of the cone tip.
Author:
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ISBN:
Category : Fluid dynamics
Languages : en
Pages : 686
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Author: Joseph W. Cleary
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 52
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Author: Joseph W. Cleary
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 82
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