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Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45°
Language: en
Pages: 64

Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45°

Authors: John O. Reller
Categories: Aerodynamics
Type: BOOK - Published: 1955 - Publisher:

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Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, a
Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees
Language: en
Pages: 56

Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees

Authors: John O. Jr Reller
Categories:
Type: BOOK - Published: 1955 - Publisher:

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Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8
Language: en
Pages: 0

Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8

Authors:
Categories:
Type: BOOK - Published: 1957 - Publisher:

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Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95
Language: en
Pages: 32

Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95

Authors: Jerome D. Julius
Categories: Heat
Type: BOOK - Published: 1959 - Publisher:

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Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9
Language: en
Pages: 64

Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9

Authors:
Categories:
Type: BOOK - Published: 1953 - Publisher:

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Temperature recovery factors were determined on the cylindrical surface of a number of 40 deg cone cylinder models at zero angle of attack and at M = 2.86. The
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