Experimental investigation of temperature recovery factors on a 10 degree cone at angle of attack at a Mach number of 3.12 / John R. Jack and Barry Moskowitz.
Temperature recovery factors on a thin-walled, metal, 10 degree included angle cone were obtained at a Mach number of 3.12 over a range of angles of attack from 0 to 10 degrees and for Reynolds numbers per foot from 1,500,000 to 8,000,000. Over the Reynolds number range investigated, an increase in...
Saved in:
| Main Author: | |
|---|---|
| Corporate Author: | |
| Other Authors: | |
| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
[1954]
|
| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
3256. |
| Subjects: |
| Summary: | Temperature recovery factors on a thin-walled, metal, 10 degree included angle cone were obtained at a Mach number of 3.12 over a range of angles of attack from 0 to 10 degrees and for Reynolds numbers per foot from 1,500,000 to 8,000,000. Over the Reynolds number range investigated, an increase in angle of attack increased the equilibrium surface temperature in the laminar and turbulent boundary-layer regions. The equilibrium surface temperatures in regions of probable cross-flow separation were in the same range as those obtained for fully turbulent flow. For the windward surface of the model, local recovery factors in the fully laminar and turbulent regions were not significantly affected by changes in angle of attack. At all angles of attack, increasing the free-stream Reynolds number moved the transition region upstream. For a given angle of attack, the transition region on the leeward surface is substantially upstream of that on the windward surface. |
|---|---|
| Item Description: | "July 1954." NACA TN Number 3256. |
| Physical Description: | 15 pages : illustrations ; 27 cm. |
| Bibliography: | Includes bibliographical references. |