Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane Calculator

✖Total Stress is defined as the force acting on the unit area of a material. The effect of stress on a body is named strain.ⓘ Total Stress [σ_total]			+10% -10%
✖Axial Load is defined as applying a force on a structure directly along an axis of the structure.ⓘ Axial Load [P]			+10% -10%
✖Cross-Sectional Area is the area of a two-dimensional shape that is obtained when a three-dimensional shape is sliced perpendicular to some specified axis at a point.ⓘ Cross-Sectional Area [A_cs]			+10% -10%
✖Eccentricity with respect to Principal Axis YY can be defined as the locus of points whose distances to a point (the focus) and a line (the directrix) are in a constant ratio.ⓘ Eccentricity with respect to Principal Axis YY [e_x]			+10% -10%
✖Distance from YY to Outermost Fiber is defined as the distance in between the Neutral Axis and Outermost Fiber.ⓘ Distance from YY to Outermost Fiber [c_x]			+10% -10%
✖Moment of Inertia about Y-Axis is defined as the moment of inertia of cross-section about YY.ⓘ Moment of Inertia about Y-Axis [I_y]			+10% -10%
✖Moment of Inertia about X-Axis is defined as the moment of inertia of cross-section about XX.ⓘ Moment of Inertia about X-Axis [I_x]			+10% -10%
✖Eccentricity with respect to Principal Axis XX can be defined as the locus of points whose distances to a point (the focus) and a line (the directrix) are in a constant ratio.ⓘ Eccentricity with respect to Principal Axis XX [e_y]			+10% -10%

✖Distance from XX to Outermost Fiber is defined as the distance in between the Neutral Axis and Outermost Fiber.ⓘ Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane [c_y]

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Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane Solution

STEP 0: Pre-Calculation Summary

Formula Used

Distance from XX to Outermost Fiber = ((Total Stress-(Axial Load/Cross-Sectional Area)-((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis)))*Moment of Inertia about X-Axis)/(Axial Load*Eccentricity with respect to Principal Axis XX)
c_y = ((σ_total-(P/A_cs)-((e_x*P*c_x)/(I_y)))*I_x)/(P*e_y)
This formula uses 9 Variables

Variables Used

Distance from XX to Outermost Fiber - (Measured in Millimeter) - Distance from XX to Outermost Fiber is defined as the distance in between the Neutral Axis and Outermost Fiber.
Total Stress - (Measured in Pascal) - Total Stress is defined as the force acting on the unit area of a material. The effect of stress on a body is named strain.
Axial Load - (Measured in Kilonewton) - Axial Load is defined as applying a force on a structure directly along an axis of the structure.
Cross-Sectional Area - (Measured in Square Meter) - Cross-Sectional Area is the area of a two-dimensional shape that is obtained when a three-dimensional shape is sliced perpendicular to some specified axis at a point.
Eccentricity with respect to Principal Axis YY - Eccentricity with respect to Principal Axis YY can be defined as the locus of points whose distances to a point (the focus) and a line (the directrix) are in a constant ratio.
Distance from YY to Outermost Fiber - (Measured in Millimeter) - Distance from YY to Outermost Fiber is defined as the distance in between the Neutral Axis and Outermost Fiber.
Moment of Inertia about Y-Axis - (Measured in Kilogram Square Meter) - Moment of Inertia about Y-Axis is defined as the moment of inertia of cross-section about YY.
Moment of Inertia about X-Axis - (Measured in Kilogram Square Meter) - Moment of Inertia about X-Axis is defined as the moment of inertia of cross-section about XX.
Eccentricity with respect to Principal Axis XX - Eccentricity with respect to Principal Axis XX can be defined as the locus of points whose distances to a point (the focus) and a line (the directrix) are in a constant ratio.

STEP 1: Convert Input(s) to Base Unit

Total Stress: 14.8 Pascal --> 14.8 Pascal No Conversion Required
Axial Load: 9.99 Kilonewton --> 9.99 Kilonewton No Conversion Required
Cross-Sectional Area: 13 Square Meter --> 13 Square Meter No Conversion Required
Eccentricity with respect to Principal Axis YY: 4 --> No Conversion Required
Distance from YY to Outermost Fiber: 15 Millimeter --> 15 Millimeter No Conversion Required
Moment of Inertia about Y-Axis: 50 Kilogram Square Meter --> 50 Kilogram Square Meter No Conversion Required
Moment of Inertia about X-Axis: 51 Kilogram Square Meter --> 51 Kilogram Square Meter No Conversion Required
Eccentricity with respect to Principal Axis XX: 0.75 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c_y = ((σ_total-(P/A_cs)-((e_x*P*c_x)/(I_y)))*I_x)/(P*e_y) --> ((14.8-(9.99/13)-((4*9.99*15)/(50)))*51)/(9.99*0.75)

Evaluating ... ...

c_y = 13.9099715099715

STEP 3: Convert Result to Output's Unit

0.0139099715099715 Meter -->13.9099715099715 Millimeter (Check conversion here)

FINAL ANSWER

13.9099715099715 ≈ 13.90997 Millimeter <-- Distance from XX to Outermost Fiber

(Calculation completed in 00.004 seconds)

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Osmania University (OU), Hyderabad

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< Eccentric Loading Calculators

Moment of Inertia of Cross-Section given Total Unit Stress in Eccentric Loading

LaTeX Go Moment of Inertia about Neutral Axis = (Axial Load*Outermost Fiber Distance*Distance from Load applied)/(Total Unit Stress-(Axial Load/Cross-Sectional Area))

Cross-Sectional Area given Total Unit Stress in Eccentric Loading

LaTeX Go Cross-Sectional Area = Axial Load/(Total Unit Stress-((Axial Load*Outermost Fiber Distance*Distance from Load applied/Moment of Inertia about Neutral Axis)))

Total Unit Stress in Eccentric Loading

LaTeX Go Total Unit Stress = (Axial Load/Cross-Sectional Area)+(Axial Load*Outermost Fiber Distance*Distance from Load applied/Moment of Inertia about Neutral Axis)

Radius of Gyration in Eccentric Loading

LaTeX Go Radius of Gyration = sqrt(Moment of Inertia/Cross-Sectional Area)

Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane Formula

LaTeX Go

Define Stress

In physics, stress is the force acting on the unit area of a material. The effect of stress on a body is named as strain. Stress can deform the body. How much force material experience can be measured using stress units. Stress can be categorized into three categories depending upon the direction of the deforming forces acting on the body.

How to Calculate Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane?

Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane calculator uses Distance from XX to Outermost Fiber = ((Total Stress-(Axial Load/Cross-Sectional Area)-((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis)))*Moment of Inertia about X-Axis)/(Axial Load*Eccentricity with respect to Principal Axis XX) to calculate the Distance from XX to Outermost Fiber, The Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane formula is defined as the distance between the x-axis and the outermost fiber. Distance from XX to Outermost Fiber is denoted by c_y symbol.

How to calculate Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane using this online calculator? To use this online calculator for Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane, enter Total Stress (σ_total), Axial Load (P), Cross-Sectional Area (A_cs), Eccentricity with respect to Principal Axis YY (e_x), Distance from YY to Outermost Fiber (c_x), Moment of Inertia about Y-Axis (I_y), Moment of Inertia about X-Axis (I_x) & Eccentricity with respect to Principal Axis XX (e_y) and hit the calculate button. Here is how the Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane calculation can be explained with given input values -> 294350.4 = ((14.8-(9990/13)-((4*9990*0.015)/(50)))*51)/(9990*0.75).

FAQ

What is Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane?

The Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane formula is defined as the distance between the x-axis and the outermost fiber and is represented as c_y = ((σ_total-(P/A_cs)-((e_x*P*c_x)/(I_y)))*I_x)/(P*e_y) or Distance from XX to Outermost Fiber = ((Total Stress-(Axial Load/Cross-Sectional Area)-((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis)))*Moment of Inertia about X-Axis)/(Axial Load*Eccentricity with respect to Principal Axis XX). Total Stress is defined as the force acting on the unit area of a material. The effect of stress on a body is named strain, Axial Load is defined as applying a force on a structure directly along an axis of the structure, Cross-Sectional Area is the area of a two-dimensional shape that is obtained when a three-dimensional shape is sliced perpendicular to some specified axis at a point, Eccentricity with respect to Principal Axis YY can be defined as the locus of points whose distances to a point (the focus) and a line (the directrix) are in a constant ratio, Distance from YY to Outermost Fiber is defined as the distance in between the Neutral Axis and Outermost Fiber, Moment of Inertia about Y-Axis is defined as the moment of inertia of cross-section about YY, Moment of Inertia about X-Axis is defined as the moment of inertia of cross-section about XX & Eccentricity with respect to Principal Axis XX can be defined as the locus of points whose distances to a point (the focus) and a line (the directrix) are in a constant ratio.

How to calculate Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane?

The Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane formula is defined as the distance between the x-axis and the outermost fiber is calculated using Distance from XX to Outermost Fiber = ((Total Stress-(Axial Load/Cross-Sectional Area)-((Eccentricity with respect to Principal Axis YY*Axial Load*Distance from YY to Outermost Fiber)/(Moment of Inertia about Y-Axis)))*Moment of Inertia about X-Axis)/(Axial Load*Eccentricity with respect to Principal Axis XX). To calculate Distance from XX to outermost fiber given Total Stress where Load doesn't lie on Plane, you need Total Stress (σ_total), Axial Load (P), Cross-Sectional Area (A_cs), Eccentricity with respect to Principal Axis YY (e_x), Distance from YY to Outermost Fiber (c_x), Moment of Inertia about Y-Axis (I_y), Moment of Inertia about X-Axis (I_x) & Eccentricity with respect to Principal Axis XX (e_y). With our tool, you need to enter the respective value for Total Stress, Axial Load, Cross-Sectional Area, Eccentricity with respect to Principal Axis YY, Distance from YY to Outermost Fiber, Moment of Inertia about Y-Axis, Moment of Inertia about X-Axis & Eccentricity with respect to Principal Axis XX and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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