Effects of Afterbody Shape on the Aerodynamic Characteristics of a Fineness-ratio-10 Cone- Cylinder Configuration at Mach Numbers from 1.57 to 4.65 Including Design Parameter Curves for Circular Afterbody Flares
Title | Effects of Afterbody Shape on the Aerodynamic Characteristics of a Fineness-ratio-10 Cone- Cylinder Configuration at Mach Numbers from 1.57 to 4.65 Including Design Parameter Curves for Circular Afterbody Flares PDF eBook |
Author | A. B. Carraway |
Publisher | |
Pages | 124 |
Release | 1960 |
Genre | |
ISBN |
Effect of Afterbody Geometry and Sting Diameter on the Aerodynamic Characteristics of Slender Bodies at Mach Number from 1.57 to 2.86
Title | Effect of Afterbody Geometry and Sting Diameter on the Aerodynamic Characteristics of Slender Bodies at Mach Number from 1.57 to 2.86 PDF eBook |
Author | Dennis E. Fuller |
Publisher | |
Pages | 38 |
Release | 1963 |
Genre | Aerodynamics |
ISBN |
Aerodynamic Force Characteristics of a Series of Lifting Cone and Cone-cylinder Configurations at a Mach Number of 6.83 and Angles of Attack Up to 1300
Title | Aerodynamic Force Characteristics of a Series of Lifting Cone and Cone-cylinder Configurations at a Mach Number of 6.83 and Angles of Attack Up to 1300 PDF eBook |
Author | Jim A. Penland |
Publisher | |
Pages | 50 |
Release | 1961 |
Genre | Mach number |
ISBN |
Aerodynamic Characteristics of 2-, 3-, and 4-, Caliber Tangent-ogive Cylinders with Nose Bluffness Ratios of 0.00, 0.25, 0.50, and 0.75 at Mach Numbers from 0.6 to 4.0
Title | Aerodynamic Characteristics of 2-, 3-, and 4-, Caliber Tangent-ogive Cylinders with Nose Bluffness Ratios of 0.00, 0.25, 0.50, and 0.75 at Mach Numbers from 0.6 to 4.0 PDF eBook |
Author | Carroll B. Butler |
Publisher | |
Pages | 248 |
Release | 1977 |
Genre | Radomes |
ISBN |
This report summarizes wind tunnel test data on various body alone configurations which provide a data matrix for bluff and pointed bodies of revolution with systematic variations in nose bluffness, nose fineness ratio, and cylinder afterbody fineness ratio. Modular model components were used to obtain static stability and drag data, with emphasis on the effect of nose bluffness on drag. Although data is included for tangent ogive noses of fineness ratio 2, 2.25, 2.5, 3.0, and 4, the nose fineness ratios of 2, 3, and 4 calibers include a systematic variation in nose bluffness ratios of 0.00, 0.25, 0.50, and 0.75 on cylindrical midsections of 5, 7, 9, and 11 calibers. A 1-caliber cylindrical afterbody is used with all configurations in this report.
Aerodynamic Characteristics for Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-stream Mach Numbers from 1.50 to 1.99
Title | Aerodynamic Characteristics for Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-stream Mach Numbers from 1.50 to 1.99 PDF eBook |
Author | Robert J. Cohen |
Publisher | |
Pages | 31 |
Release | 1951 |
Genre | |
ISBN |
Stability Investigation of a Blunted Cone and a Blunted Ogive with a Flared Cylinder Afterbody at Mach Numbers from 0.30 to 2.85
Title | Stability Investigation of a Blunted Cone and a Blunted Ogive with a Flared Cylinder Afterbody at Mach Numbers from 0.30 to 2.85 PDF eBook |
Author | Lucille C. Coltrane |
Publisher | |
Pages | 32 |
Release | 1962 |
Genre | Aircraft |
ISBN |
Effect of Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20
Title | Effect of Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20 PDF eBook |
Author | Clyde Hayes |
Publisher | |
Pages | 44 |
Release | 1965 |
Genre | Lift (Aerodynamics) |
ISBN |