Problem 1.80352010121624Time (hours)Load Duration CurveLoad DurationOther data are as follows:CF= 43.76%PC= 100 MWFind:A. Total energyB. Average loadC. Load FactorD. Reserve over peak(MIO peoT

(A) The total energy is the area under the curve.

Answered: Other data are as follows: CF= 43.76%…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

Determine the components of the reactions at A and E, (a) if a 760-N load is applied as shown at C, (b) if the load is moved along its line of action and is applied at point D. B 300 mm- Σ Fx = 0: o Σ Μ Α = 0: Ey = O 600 mm- o Ex = C Solution: 1. Free body: Entire assembly. This analysis is valid for both a) and b), since position of the load on its line of action is immaterial. o FBD: in total, there are o Hence Ax = D -300 mm N; Σ F, = 0: Ay = 2. If the load is acting on C, we choose the free body: member BE o Member BE has forces acting on it. (number of forces) E N; 200 mm N; forces/reactions (number of forces) acting on the entire assembly. Ex Ey • Thus the force acting on E should be directed along EB, hence N; 3. If the load is acting on D, we choose the free body: member AC o Member AC has forces acting on it. (number of forces) =
A copper wire, caliber 16 AWG (diameter of 0.1019 in.) 4 ft in length, is stretched with a force of 500 lb. It lengthens 0.21 in. and its diameter is reduced 0.10175 in. Determine the modulus of elasticity, from its response in 10^3 ksi.
For the cantilever steel beam [E = 220 GPa; /= 120 × 106 mm4], use the double-integration method to determine the deflection VÀ at A. Assume L = 2.9 m, P = 40 kN, and w = 27 kN/m. Answer: VA = i L mm. B
A1
BRAJ - TECH Manufacturing company requested AAA Power Plant to provide 1.08 MW as the maximum load dernand, If the total: connected load is 21.42% less of that maximum load, what is the demand factor? 3.127 2.12 © 1.27 1.01
and y vs. y (phase plot) 4. Consider the deflection v of the beam to the right. The beam is supported at each end and sags due to its own weight (a distributed load q = 50 kN/m). The equation describing the deflection is d'u qx (x- L) dx 2EI where L=5.0 m, I = 0.0052 m* and E = 1.0x1010 Pa. Use the method of your choosing (shooting or finite differences) to solve for: 1) the slope at each end of the beam; 2) the maximum deflection; and 3) the location of maximum deflection.
DZIA Oe Le 9:09 • Asiacell Iı. こ EE A docs.google.com 70 N D 120 N 45 50 N/m 300 N.m 30 1.5m 1.5m 3m 2 m 2 m blä 3 the concentrated load which replaced by distributed load is equal to A
For the cantilever steel beam [E = 180 GPa; / = 102 x 106 mm4], use the double- integration method to determine the deflection vg at B. Assume L = 3.8 m, Mo = 68 kN-m, and w = 17 kN/m. Answer: VB i mm. W Save for Later L eTextbook and Media Attempto unlimit Mo
Radius of mohr circle
HW #3 04/12/2020 due date. wednesden Tx=/25 MPa T2=? uncler Novolume cheye! do 10cm 20=0 ( For novalmachaye Sscm Socm N: 0.4 E= 10 k 125-10040z=0 102= -25 MPa Fz=? Az 0.2m X0.3m %3D Q: Ex=? final dianeter. F2 -25M x (200 mx 300) t2= -1500000N~/500KN
Find the min. supportable uniformly distributed load.
Q. 2: Method Planform Design You are to design candidate wings for a sport RC electric aircraft to the following requirements: density: p= 1.2 kg/m³ speed: lift: V. = 13.4 mph = 6 m/s L = 11 oz = 3.0N span: b = 63 in = 1.6 m Assume an elliptic load distribution I(y) = ToV1- (2y/b)² for each of the design cases below. Assume de /da = 2ñ for the wing airfoils. Assume the wing reference line (e.g. fuselage axis) is aligned with the flight direction, so that a = 0°. 2.1) Baseline elliptical wing: Assume a spanwise-constant c = 0.8. a) (Elliptic) Determine the chord distribution c(y) and sketch the planform. b) (Elliptic) Determine agero(y). c) (Elliptic) What will ageom (y) look like if the same cambered airfoil is used all across the span? d) (Elliptic) Determine the induced drag for this wing? What is the lift-to-drag ratio?

SEE MORE QUESTIONS

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS

Other data are as follows: CF= 43.76% PC= 100 MW Find: A. Total energy B. Average load C. Load Factor D. Reserve over peak