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o-na [289]
3 years ago
10

What is the number for account receivable?​

Engineering
2 answers:
creativ13 [48]3 years ago
8 0

Answer:

113 or 1-1300

Explanation:

Account receivable => Current Assets (11)

For receivable => 3

So, the number for account receivable is 113

Mazyrski [523]3 years ago
3 0

Answer:

113

Maybe thats the answer for this question

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The following figures were obtained in a standard tensile test on a specimen of low carbon steel with a circular sectional area:
liq [111]

Answer:

See Explaination

Explanation:

1)here for given stress strain curve graph is given as follows

where for getting stress,S=F/A=4F/(pi*(50*10^-3)^2)

for strain=e=dl/l=dl*10^-3/100 mm/mm or m/m

2)so graph is as follows

3)for getting youngs modulus of elasticity we must know slope of graph stress verses strain and for straight line in elastic region upto 12 point we have elastic region and from that we get E as

E=slope of graph for first 12 points=S/e=14.5665*10^9/.812=17.9390*10^9 N/m2

4)for getting ultimate tensile stress at which specimen bears maximum load without failure so we get UTS as

UTS=maximum load/area=40*10^6/1.9634=20.3728*10^6 N/m2

5)percentage reduction in area is given by

percentage reduction in area=[original area-final area/original area]*100

Percent reduction=[5062-10^2]*100/50^2=96%

6)percentage elongation is given by

percent elongation=[final length-original length/original length]*100

final length at fractureis=14.56+100=114.56 mm

so we get percent elongation as=[114.56-100/100]*100=14.56%

7)true fracture stress is given by load at fracture devided by true area at fracture

Sf=load/(true area)=4*28*10^3/(pi*(10*10^-3)^2)=356.5070*10^6 N/m2

8 0
4 years ago
The pressure distribution over a section of a two-dimensional wing at 4 degrees of incidence may be approximated as follows: Upp
Aliun [14]

Answer:

The lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.

Explanation:

The Upper Surface Cp is given as

Cp_u=-0.8 *0.6 +0.1 \int\limits^1_{0.6} \, dx =-0.8*0.6+0.4*0.1

The Lower Surface Cp is given as

Cp_l=-0.4 *0.6 +0.1 \int\limits^1_{0.6} \, dx =-0.4*0.6+0.4*0.1

The difference of the Cp over the airfoil is given as

\Delta Cp=Cp_l-Cp_u\\\Delta Cp=-0.4*0.6+0.4*0.1-(-0.8*0.6-0.4*0.1)\\\Delta Cp=-0.4*0.6+0.4*0.1+0.8*0.6+0.4*0.1\\\Delta Cp=0.4*0.6+0.4*0.2\\\Delta Cp=0.32

Now the Lift Coefficient is given as

C_L=\Delta C_p cos(\alpha_i)\\C_L=0.32\times cos(4*\frac{\pi}{180})\\C_L=0.3192

Now the coefficient of moment about the leading edge is given as

C_M=-0.3*0.4*0.6-(0.6+\dfrac{0.4}{3})*0.2*0.4\\C_M=-0.1306

So the lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.

5 0
3 years ago
List 3 specific things you can do with a screw gun (not just screw in screws)
alexandr402 [8]

Answer:

1: Attaching a fork and wip eggs/batter/ ect.

2: You can entertain a cat by putting yarn on the gun/drill

3: If you get yarn everywere, you can spin the yarn up on the drill/gun

Explanation:

I hope this helps you out somehow

8 0
3 years ago
A book of the Law was found in the Temple, which was being repaired, during the___
grigory [225]

Answer:

2

Explanation:

5 0
3 years ago
Read 2 more answers
I really need some help here!
Virty [35]

Explanation:

<h3>1.*Frame Structure have joins which keep them together whereas Shell Structure have no joins.</h3><h3>*Shell Structure usually only support their own weight whereas Frame Structure support others weight as well as themselve.</h3>
7 0
3 years ago
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