Aerodynamic Performance and Static Stability Characteristics of a Blunt Nosed, Boattailed, 13 Deg Half Cone at Mach Numbers from 0.6 to 5.0
Title | Aerodynamic Performance and Static Stability Characteristics of a Blunt Nosed, Boattailed, 13 Deg Half Cone at Mach Numbers from 0.6 to 5.0 PDF eBook |
Author | |
Publisher | |
Pages | 76 |
Release | 1961 |
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The Aerodynamic Characteristics of a Blunt Half Cone Entry Configurations Obtained from Ballistic Range Tests at Mach Numbers Near 3
Title | The Aerodynamic Characteristics of a Blunt Half Cone Entry Configurations Obtained from Ballistic Range Tests at Mach Numbers Near 3 PDF eBook |
Author | |
Publisher | |
Pages | 38 |
Release | 1961 |
Genre | |
ISBN |
A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0
Title | A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 PDF eBook |
Author | Robert S. Osborne |
Publisher | |
Pages | 20 |
Release | 1960 |
Genre | Aerodynamics |
ISBN |
Aerodynamic Characteristics of a Blunt Half-cone Entry Configuration at Mach Numbers of 5.2, 7.4, and 10.4
Title | Aerodynamic Characteristics of a Blunt Half-cone Entry Configuration at Mach Numbers of 5.2, 7.4, and 10.4 PDF eBook |
Author | |
Publisher | |
Pages | 78 |
Release | 1963 |
Genre | |
ISBN |
Static Stability Characteristics of Blunt Low-fineness-ratio Bodies of Revolution at a Mach Number of 24.5 in Helium
Title | Static Stability Characteristics of Blunt Low-fineness-ratio Bodies of Revolution at a Mach Number of 24.5 in Helium PDF eBook |
Author | Robert D. Witcofski |
Publisher | |
Pages | 54 |
Release | 1964 |
Genre | Aerodynamics |
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.
Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85
Title | Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 PDF eBook |
Author | Peter T. Bernot |
Publisher | |
Pages | 48 |
Release | 1963 |
Genre | Mach number |
ISBN |