Author: Jack N. Nielsen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 63
Book Description
An exact theoretical method is developed that permits the determination of the pressure field of a wing-body combination having a circular body and wings with supersonic leading and trailing edges. Detailed calculations are performed for the case of a rectangular wing or all-movable control surface on a body at zero angle of attack. Design charts are presented showing the effect of interference on the lift and center-of-pressure position of the wings. The physical basis of the interference is discussed.
Wing-body Interference at Supersonic Speeds with an Application to Combinations with Rectangular Wings
General Theory of Wave-drag Reduction for Combinations Employing Quasi-cylindrical Bodies with an Application to Swept-wing and Body Combinations
Author: Jack N. Nielsen
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 82
Book Description
The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 82
Book Description
The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
WING-BODY INTERFERENCE AT SUPERSONIC SPEEDS.
An Analysis of the Stability and Ultimate Compressive Strength of Short Sheet-stringer Panels with Special Reference to the Influence of the Riveted Connection Between Sheet and Stringer
Author: Benjamin H. Beam
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 312
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 312
Book Description
Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-body Combinations Having Cambered Wings with an Aspect Ratio of 3.5 and a Taper Ratio of 0.2
Author: Ross B. Robinson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
linearized theory of steady high-speed flow
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.
An Integrated Approach to the Analysis and Design of Wings and Wing-body Combinations in Supersonic Flow
Author: Ralph L. Carmichael
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
Missile Configuration Design
Author: S. S. Chin
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 304
Book Description
Beskriver principperne i f.m. konstruktionen af styrede missiler.
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 304
Book Description
Beskriver principperne i f.m. konstruktionen af styrede missiler.