Author: Charles B. RumseyPublisher:
ISBN:
Category :
Languages : en
Pages : 43
Book Description
Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2
Author: Charles B. RumseyMeasurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 150 Cone in Free Flight at Supersonic Mach Numbers Up to 5.2
Author: Charles B. RumseyPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description
Abstract:
Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9
Author: Charles B. RumseyPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 42
Book Description
Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7
Author: Charles R. RumseyPublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 66
Book Description
Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2
Author: Charles B. RumseyPublisher:
ISBN:
Category :
Languages : en
Pages : 43
Book Description
Measurements of aerodynamic heat transfer have been made at several stations on the 15 degree total-angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 5.2. Data are presented for a range of local Mach number just outside the boundary layer from 1.40 to 4.65 and a range of local Reynolds number from 3.8 times 10 to the 6th power to 46.5 times 10 to the 6th power, based on length from the nose tip to a measurement station. Laminar, transitional, and turbulent heat-transfer coefficients were measured. The laminar data were in agreement with laminar theory for cones, and the turbulent data agreed well with turbulent theory for cones using Reynolds number based on length from the nose tip. (Author).
Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15° Cone in Free Flight at Supersonic Mach Numbers Up to 5.2
Author: Charles B. RumseyMeasurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9
Author: Charles B. RumseyPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 38
Book Description
Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9
Author: Charles B. RumseyMeasurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 150 Cone in Free Flight at Supersonic Mach Numbers Up to 5.2
Author: Charles B. RumseyPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Abstract:
Author: Charles B. Rumsey