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[6]: 92 If the center of gravity is forward of the neutral point, the static margin is positive. [7]: 8 If the center of gravity is aft of the neutral point, the static margin is negative. The greater the static margin, the more stable the aircraft will be.
In engineering, a factor of safety (FoS) or safety factor (SF) expresses how much stronger a system is than it needs to be for an intended load.Safety factors are often calculated using detailed analysis because comprehensive testing is impractical on many projects, such as bridges and buildings, but the structure's ability to carry a load must be determined to a reasonable accuracy.
The stiffness does not only depend on the static stability term , it also contains a term which effectively determines the angle of attack due to the body rotation. The distance of the center of lift, including this term, ahead of the centre of gravity is called the maneuver margin. It must be negative for stability.
The metacentric height (GM) is a measurement of the initial static stability of a floating body. [1] It is calculated as the distance between the centre of gravity of a ship and its metacentre . A larger metacentric height implies greater initial stability against overturning.
The expression to calculate the aerodynamic force is: = ... Difference between static pressure and free current pressure ... Static margin; Weathervane effect;
The Static Margin can then be used to quantify the AC: = where: C n = yawing moment coefficient; C m = pitching moment coefficient; C l = rolling moment coefficient; C x = X-force ≈ Drag; C y = Y-force ≈ Side Force; C z = Z-force ≈ Lift; ref = reference point (about which moments were taken) c = reference length
Margin of Safety is the common method for design criteria. It is defined MS = P u /P − 1. For example, to achieve a factor of safety of 4, the allowable stress in an AISI 1018 steel component can be calculated to be = / = 440/4 = 110 MPa, or = 110×10 6 N/m 2. Such allowable stresses are also known as "design stresses" or "working stresses".
In aerodynamics, the normal shock tables are a series of tabulated data listing the various properties before and after the occurrence of a normal shock wave. [1] With a given upstream Mach number, the post-shock Mach number can be calculated along with the pressure, density, temperature, and stagnation pressure ratios.