Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Numbers of 1.93, 2.55, and 3.05
Title | Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Numbers of 1.93, 2.55, and 3.05 PDF eBook |
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Pages | 44 |
Release | 1961 |
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Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Number of 1.93, 2.55 and 3.05
Title | Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Number of 1.93, 2.55 and 3.05 PDF eBook |
Author | Odell A. Morris |
Publisher | |
Pages | 40 |
Release | 1961 |
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An Investigation to Determine the Stability Characteristics of Three Supersonic-impact Ballistic Reentry Shapes at Mach Numbers from 1.2 to 4.2
Title | An Investigation to Determine the Stability Characteristics of Three Supersonic-impact Ballistic Reentry Shapes at Mach Numbers from 1.2 to 4.2 PDF eBook |
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Pages | 52 |
Release | 1962 |
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Static Stability Investigation of Supersonic-impact Ballistic Reentry Shapes at Mach Numbers of 2.55 and 3.05
Title | Static Stability Investigation of Supersonic-impact Ballistic Reentry Shapes at Mach Numbers of 2.55 and 3.05 PDF eBook |
Author | John M. Swihart |
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Pages | 16 |
Release | 1959 |
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Calculated Pressure Distributions and Components of Total-drag Coefficients for 18 Constant-volume Slender Bodies of Revolution at Zero Incidence for Mach Numbers from 2.0 to 12.0, with Experimental Aerodynamic Characteristics for Three of the Bodies
Title | Calculated Pressure Distributions and Components of Total-drag Coefficients for 18 Constant-volume Slender Bodies of Revolution at Zero Incidence for Mach Numbers from 2.0 to 12.0, with Experimental Aerodynamic Characteristics for Three of the Bodies PDF eBook |
Author | Louis S. Stiver |
Publisher | |
Pages | 108 |
Release | 1971 |
Genre | Aerodynamic load |
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Supersonic-tunnel Tests of Projectiles in Germany and Italy
Title | Supersonic-tunnel Tests of Projectiles in Germany and Italy PDF eBook |
Author | Antonio Ferri |
Publisher | |
Pages | 76 |
Release | 1945 |
Genre | Aerodynamic load |
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Summary: Tests were performed in the Göttingen (Germany) and Guidonia (Italy) supersonic tunnels in order to determine the aerodynamic characteristics of projectiles of various shapes. The Mach numbers ranged from about 1.3 to 3.2 for the Göttingen tests and from 1.44 to 2.66 for the Guidonia tests. The results show that increasing the relative length of the nose causes the drag coefficient to decrease and the center of pressure to move forward. For a given length, the nose having minimum drag has a curved profile; the curvature is greatest at the tip and decreases to a very small value toward the rear of the nose, where the shape becomes approximately conical. As the Mach number increases, the drag coefficient decreases and the center of pressure moves toward the tail. For the higher Mach numbers the variation of the drag coefficient and the movement of the center of pressure are small. Existing aerodynamic theory gives values of the aerodynamic characteristics close to those determined experimentally for small flow deviations.
Aerodynamic Characteristics in Pitch of Six Ballistic Reentry Models at a Mach Number of 10.03
Title | Aerodynamic Characteristics in Pitch of Six Ballistic Reentry Models at a Mach Number of 10.03 PDF eBook |
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Pages | 28 |
Release | 1963 |
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