Preliminary Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61 PDF Download
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Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 30
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Book Description
Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 30
Get Book Here
Book Description
Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 21
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Book Description
The results indicate that the trend found previously of an increase in boundary-layer transition Reynolds number with increase in model cooling continued to higher Reynolds numbers. The highest transition Reynolds number obtained with cooling was 28,500,000. At this Reynolds number, the classical Tollmien-Schlichting wave type of boundary-layer number, the instability was apparently overshadowed by surface roughness effects. The results indicated that, when transition was fixed by surface irregularities or airstream flow disturbances, cooling was not effective in obtaining laminar flow behind the irregularity or disturbances.
Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 23
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Book Description
A preliminary investigation has been made of the effects of heat transfer on boundary-layer transition on a body of revolution at a Mach number of 1.61 and over a Reynolds number range of 7,000,000 to 20,000,000, based on body length. The body had a parabolic-arc profile, blunt-base, and a fineness ratio of 12.2 (NACA RM-10). The results indicated that, by cooling the model an average of about 50 degrees F, the Reynolds number for which laminar boundary-layer flow could be maintained over the entire length of the body was increased from the value of 11,500,000 without cooling to over 20,000,000, the limit of the present tests. Heatig the model an average of about 12 degrees F on the other hand decreased the transition Reynolds number from 11,500,000 to about 8,000,000. These effects of heat transfer on transition were considerably larger than previously found in similar investigations in other wind tunnels. It appears that, if the boundary-layer transition Reynolds number for zero heat transfer is large, as in the present experiments, then the sensitivity of transition to heating or cooling is high; if the zero-heat-transfer transition Reynolds number is low, then transition is relatively insensitive to heat-transfer effects.
Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 11
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 608
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 910
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Author: Royal Aeronautical Society
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 938
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Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 42
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Book Description
Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 13
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Book Description
An investigation has been made to determine the effect of heat transfer on the peak pressure rise associated with the separation of a turbulent boundary layer on a body of revolution (NACA RM-10) at a Mach number of 1.61. Tests were made over a Reynolds number range from 11.6 X 10 to the 6th to 34.8 X 10 to the 6th and with 0 to 120 degrees F of cooling, which corresponds to a ratio of model-wall temperature to stagnation temperature of 0.96 (zero heat transfer) to 0.75. The stagnation temperature was approximately 570 degrees F absolute. Boundary-layer separation was induced by means of forward-facing steps or collars at the base of the model and changes in heat transfer were obtained by cooling the model. The peak pressure rise was determined from shock angles measured from schlieren photographs.
Author: Leo T. Chauvin
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 46
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Book Description
Heat transfer data are presented for a Mach number range of 1.02 to 2.48 and for a Reynolds number range of 3,180,000 to 163,850,000 based on the axial distance from the nose to the point at which temperature measurements were made.
