The Dihedral Effectiveness Ratio (Yδ) is a parameter used to quantify the effectiveness of dihedral in an aircraft’s wing design. Yδ is the Dihedral Effectiveness Ratio, ΔY is the change in lateral force (side force), δ is the aileron deflection.
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The Equivalent Flat Plate Area (Aeq) in aerodynamics is used to represent the drag characteristics of an aircraft Aeq is the Equivalent Flat Plate Area, CD 0 is the zero-lift drag coefficient (drag when lift is zero), S is the reference area (usually the wing area).
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Specific Impulse (Isp) is a measure of the efficiency of a propulsion system, particularly rocket engines. Isp: Specific Impulse T: Thrust m˙fuel: Fuel flow rate g0: Gravitational acceleration (standard value, approximately 9.81 m/s29.81 m/s2)
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Centripetal acceleration is the acceleration directed towards the center of the circular path in which an object is moving ac is the centripetal acceleration, V is the velocity of the aircraft, R is the radius of the turn.
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The Yawing Moment is the moment about the vertical axis of an aircraft Cn is the yawing moment coefficient. β is the sideslip angle.
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The aspect ratio of a fuselage is a dimensionless parameter that characterizes the elongation or stretching of the fuselage shape. AR is the aspect ratio of the fuselage. L is the length of the fuselage. D is the maximum diameter or width of the fuselage.
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The Lift Curve Slope (a) is a key parameter in aerodynamics that describes the rate at which the lift coefficient (CL) changes with the angle of attack (α) for a wing. a is the lift curve slope. ΔCL is the change in lift coefficient. Δα is the change in angle of attack
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The Flow Mach Number (M) is a dimensionless parameter used to characterize the speed of an object moving through a fluid, particularly in the context of compressible flow like in aerodynamics M is the Flow Mach Number. V is the velocity of the object. a is the local speed of sound in the fluid.
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The Elliptical Lift Distribution Lift Coefficient (CL elliptical) is a parameter used to describe the lift distribution across the span of an aircraft wing when it follows an elliptical lift distribution CL elliptical is the elliptical lift distribution lift coefficient. b is the wingspan of the aircraft. S is the wing reference area.
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The Vortex Lift Coefficient (CLvortex) is a parameter used in the analysis of aircraft aerodynamics, particularly in the context of vortex lift generated by leading-edge vortices CLvortex is the vortex lift coefficient. Γ is the circulation around the wing (strength of the vortex). ρ is the air density. V is the velocity of the
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