Author: Franklin Moore
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 756
Book Description
First-order relations were obtained for attenuation of shock and flow deflection outward along the shock. These relations probably conform closely to physical fact, provided the entrance slope is small. These relations contain an error, but become exact as the radial coordinate approaches inifinity. The error is thus probably of the second order over the entire shock front.
Linearized Supersonic Axially Symmetric Flow about Open-nosed Bodies Obtained by Use of Stream Function
Author: Franklin Moore
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 756
Book Description
First-order relations were obtained for attenuation of shock and flow deflection outward along the shock. These relations probably conform closely to physical fact, provided the entrance slope is small. These relations contain an error, but become exact as the radial coordinate approaches inifinity. The error is thus probably of the second order over the entire shock front.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 756
Book Description
First-order relations were obtained for attenuation of shock and flow deflection outward along the shock. These relations probably conform closely to physical fact, provided the entrance slope is small. These relations contain an error, but become exact as the radial coordinate approaches inifinity. The error is thus probably of the second order over the entire shock front.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1304
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1304
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 616
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 616
Book Description
Bibliography of Technical Reports
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 376
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 376
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 498
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 498
Book Description
List of Technical Notes, 1947-1953
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 162
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 162
Book Description
Tables of Characteristic Functions for Solving Boundary-value Problems of the Wave Equation with Application to Supersonic Interference
Author: Jack Norman Nielsen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 682
Book Description
Tables are presented containing 69,000 values of a set of characteristic functions which first arose in problems of supersonic wing-body interference. The tables are useful in problems of supersonic flow involving aerodynamic shapes which are wholly or in part quasi-cylinders of nearly circular cross section. A number of uses are described in the aerodynamics of bodies alone, body-body or shock-body interference, wing-body interference, the vortex-panel interference. Three illustrative examples are worked out in detail. First, the pressure field due to fuselage indentation is calculated and presented in a form independent of Mach number. Secondly, the tables are applied to a problem involving a previously unpublished solution to the Navier-Stokes equations; namely, the boundary-layer profiles of a circular cylinder moved impulsively with a constant axial force in a viscous incompressible fluid. In the final example, the wave drag of corrugated circular cylinders is calculated as a function of the number of corrugations and their wave length. Several nonaerodynamic applications are pointed out in the fields of acoustics and heat conduction. Generally speaking, the tables are applicable to boundary-value problems of the second kind involving the wave equation in three dimensions with approximately circular cylindrical boundaries or involving the unsteady heat-conduction equation in two space dimensions with nearly circular boundaries.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 682
Book Description
Tables are presented containing 69,000 values of a set of characteristic functions which first arose in problems of supersonic wing-body interference. The tables are useful in problems of supersonic flow involving aerodynamic shapes which are wholly or in part quasi-cylinders of nearly circular cross section. A number of uses are described in the aerodynamics of bodies alone, body-body or shock-body interference, wing-body interference, the vortex-panel interference. Three illustrative examples are worked out in detail. First, the pressure field due to fuselage indentation is calculated and presented in a form independent of Mach number. Secondly, the tables are applied to a problem involving a previously unpublished solution to the Navier-Stokes equations; namely, the boundary-layer profiles of a circular cylinder moved impulsively with a constant axial force in a viscous incompressible fluid. In the final example, the wave drag of corrugated circular cylinders is calculated as a function of the number of corrugations and their wave length. Several nonaerodynamic applications are pointed out in the fields of acoustics and heat conduction. Generally speaking, the tables are applicable to boundary-value problems of the second kind involving the wave equation in three dimensions with approximately circular cylindrical boundaries or involving the unsteady heat-conduction equation in two space dimensions with nearly circular boundaries.
Technical Note
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 692
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 692
Book Description
Experimental Investigation of a 90 Degree Cascade Diffusing Bend with an Area Ratio of 1.45:1 and with Several Inlet Boundary Layers
Author: Daniel Friedman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 804
Book Description
An experimental investigation was conducted in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and a 19-inch square inlet with several inlet-boundary-layer shapes and thicknesses. The maximum mean inlet Mach number was 0.41 and the corresponding airfoil Reynolds number was 950,000. The experimental results seem to indicate that, when the duct configuration requires a bend, a certain amount of diffusion can be obtained without an appreciable rise in the total-pressure losses. If length is important, this configuration requires much less space than the usual diffuser-bend combination.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 804
Book Description
An experimental investigation was conducted in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and a 19-inch square inlet with several inlet-boundary-layer shapes and thicknesses. The maximum mean inlet Mach number was 0.41 and the corresponding airfoil Reynolds number was 950,000. The experimental results seem to indicate that, when the duct configuration requires a bend, a certain amount of diffusion can be obtained without an appreciable rise in the total-pressure losses. If length is important, this configuration requires much less space than the usual diffuser-bend combination.