درباره ما
NACA-RM-L53L28 REV A
Pressures and associated aerodynamic and load characteristics for two bodies of revolution at transonic speeds
Year: 1954
Abstract: INTRODUCTION
A detailed study of the pressures and resulting forces for a body of revolution, designated "curved body" in this report, at transonic speeds has been presented in reference 1.
The present tests were undertaken in order to provide aerodynamic load data for a body of revolution having an ogive nose and cylindrical afterbody and to compare the aerodynamic characteristics of this body with the body of reference 1 at transonic speeds. The body used in the present test is designated "cylindrical body" herein. A comparison of various theoretical aerodynamic parameters with experimental values is included.
The tests reported herein were made for a Mach number range from 0.6 to 1.13 and an angle-of-attack range from Oo t o 20°. Reynolds number range corresponding to the Mach number range varied from 3.3 x 10 6 t o 3.9 x 10 6 per foot of length.
A detailed study of the pressures and resulting forces for a body of revolution, designated "curved body" in this report, at transonic speeds has been presented in reference 1.
The present tests were undertaken in order to provide aerodynamic load data for a body of revolution having an ogive nose and cylindrical afterbody and to compare the aerodynamic characteristics of this body with the body of reference 1 at transonic speeds. The body used in the present test is designated "cylindrical body" herein. A comparison of various theoretical aerodynamic parameters with experimental values is included.
The tests reported herein were made for a Mach number range from 0.6 to 1.13 and an angle-of-attack range from Oo t o 20°. Reynolds number range corresponding to the Mach number range varied from 3.3 x 10 6 t o 3.9 x 10 6 per foot of length.
-
Statistics
NACA-RM-L53L28 REV A
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:09:42Z | |
| date available | 2017-09-04T15:09:42Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | APSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/7835 | |
| description abstract | INTRODUCTION A detailed study of the pressures and resulting forces for a body of revolution, designated "curved body" in this report, at transonic speeds has been presented in reference 1. The present tests were undertaken in order to provide aerodynamic load data for a body of revolution having an ogive nose and cylindrical afterbody and to compare the aerodynamic characteristics of this body with the body of reference 1 at transonic speeds. The body used in the present test is designated "cylindrical body" herein. A comparison of various theoretical aerodynamic parameters with experimental values is included. The tests reported herein were made for a Mach number range from 0.6 to 1.13 and an angle-of-attack range from Oo t o 20°. Reynolds number range corresponding to the Mach number range varied from 3.3 x 10 6 t o 3.9 x 10 6 per foot of length. | |
| language | English | |
| title | NACA-RM-L53L28 REV A | num |
| title | Pressures and associated aerodynamic and load characteristics for two bodies of revolution at transonic speeds | en |
| type | standard | |
| page | 35 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |