While designing any aerodynamic body an unspoken assumption of bilateral or mirror symmetry is taken into consideration. Argument against this bilateral symmetry states that “once the velocity of sound is exceeded, the laws of aerodynamics change in such a way as to make it seem inadvisable to arrange the components of an airplane side by side or abreast in a supersonic stream unless there are compelling reasons for such an arrangement.“
2.1.1 Wave Drag
This type of drag is formed as a result of shock waves formed around an aircraft. Wave drag is the main reason behind the designing of oblique wings. This design has been found to reduce wave drag for a supersonic aircraft and can be believed as an aerodynamic evolution to swept wings on symmetric aircraft configurations. This wing is not symmetric at supersonic speeds, but rotates about a central pivot, which allows the maximum cross sectional area perpendicular to the flow to be half that of a similar symmetric design.
The …show more content…
This is achieved by placing the wing at an angle of yaw which such that the component Mach number normal to its long axis be subsonic. M⊥ = M∞ cos β
Where β is angle of sweep.
Let us assume that the critical “drag divergence” mach number of the wing section is 0.7, then the angle of yaw must be such as to reduce the component Mach number to this value. For M-1.0 the angle of yaw required is then 45 deg.
2.3.2 Increased extension of the wing in the flight direction
One of the major advantage of yawed/oblique wing over swept wing depensd on an increased extension of wing in the flight direction. We know that spreading the lift over a greater length weakens sonic boom intensity and drag. For a given structured slenderness the single yawed wing have nearly double the projected length of the equivalent swept
2.1.1 Wave Drag
This type of drag is formed as a result of shock waves formed around an aircraft. Wave drag is the main reason behind the designing of oblique wings. This design has been found to reduce wave drag for a supersonic aircraft and can be believed as an aerodynamic evolution to swept wings on symmetric aircraft configurations. This wing is not symmetric at supersonic speeds, but rotates about a central pivot, which allows the maximum cross sectional area perpendicular to the flow to be half that of a similar symmetric design.
The …show more content…
This is achieved by placing the wing at an angle of yaw which such that the component Mach number normal to its long axis be subsonic. M⊥ = M∞ cos β
Where β is angle of sweep.
Let us assume that the critical “drag divergence” mach number of the wing section is 0.7, then the angle of yaw must be such as to reduce the component Mach number to this value. For M-1.0 the angle of yaw required is then 45 deg.
2.3.2 Increased extension of the wing in the flight direction
One of the major advantage of yawed/oblique wing over swept wing depensd on an increased extension of wing in the flight direction. We know that spreading the lift over a greater length weakens sonic boom intensity and drag. For a given structured slenderness the single yawed wing have nearly double the projected length of the equivalent swept