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- 220 200 180 160 140 120 Stress, ksi 100 80 Question O: Data for an extension spring is shown in the table below. Use only this table for this question! Also shown is an abridged version of Table 18-2 and figure 18. Spring Material ASTM A228 Music wire Max Operating Load: F₁ = 57 Type of Service Average Estimated Wahl Factor: K= 1.200 Required Mean Diameter: D = 0.850 Design Stress in Wire: 1 = 115,000 psi TABLE 18-2 Wire Gages and Diameters for Springs 0.0181 27 0.0175 Gage no. U.S. steel wire gage (in) Music wire gage² (in) 0063 0.067 28 0.0162 0.071 29 0.0150 0.075 30 00140 0.080 31 0.0132 0085 32 00128 0.090 33 00118 0096 34 0.0104 0.100 35 0.0095 36 0.0090 1.8 Wire diameter, mm 0.106 0.112 5.4 5.8 6.2 1515 Compression and extension springs, Music Wire, ASTM A228. 1380 Light service 1240 Average service 1100 965 Severe service 825 690 P10100 OSO 0 0.150 0.170 061'0 0.210 0.230 F 0.250 550 Stress, MPa Wire diameter, in FIGURE 18-9 Design shear stresses for ASTM A228 steel wire (music…arrow_forwardPlease see attachment.arrow_forwardPlease see attachment.arrow_forward
- P3: A differential band brake shown in the figure below uses a woven lining having a design value of the friction coefficient f=0.20. Dimensions are b=80 mm, r=250 mm, c=700 mm, a = 150 mm, s=35 mm, and 0=240°. Find 1) the brake torque if the maximum lining pressure is 0.5 MPa, 2) the corresponding actuating force F, and 3) the values of dimensions that would cause the brake to be self-locking. (25%) -240° F-250 mm Band width, b-80 mm Rotation Friction coefficient, -0.20 Maximum lining pressure, P-0.5 MPa 3-35 mm la-150 mm e-700 mm-arrow_forwardInclude a grapharrow_forwardA particular furnace is shaped like a section of a cone. The top surface of the furnace is uniformly heated by a resistance heater. During operation, the top surface is measured to be 800 K and the power supplied to the resistance heater is 1750 W/m². The sidewall of the furnace is perfectly insulated with ε = 0.2. If the emissivity of the top and bottom surfaces are ε = 0.5 and > = 0.7, respectively, determine the temperatures of the sidewall and the bottom surface of the furnace. A1 D₂ = 20 mm A₂ L = 50 mm D₁ = 40 mmarrow_forward
- You are designing an industrial furnace to keep pieces of sheet metal at a fixed temperature. You decide a long, hemispherical furnace will be the best choice. The hemispherical portion is built from insulating brick to reflect the radiation from a ceramic plate onto the sheet metal and the ceramic plate is heated by gas burners from below. An insulating wall prevents direct transmission of radiative energy from the ceramic plate to the sheet metal. The radius of the hemisphere is 1 m and the rest of the system properties can be found in the table below. You may neglect convection during your analysis. Temperature Emissivity Ceramic Plate 1600 K ε = 0.85 Sheet Metal 500 K Insulating Brick unknown € = 1 ε = 0.6 a) Calculate the required heat input, in W, per unit length of the furnace (out of the page) that must be supplied by the gas burners to maintain the specified temperatures. b) What is the temperature of the insulating brick surface? Metal products (2) T₂ = 500 K, &- 1 -…arrow_forwardDerive common expressions for the radiative heat transfer rate between two surfaces below. Aσ (T-T) a) Infinite parallel plates: A1, T1 E1 912 = 1 1 + ε1 E2 1 A2, T2, E2 b) Infinitely long concentric cylinders: 912 c) Concentric spheres: 912 182 A₁σ (T-T) 1-82 (11) = 1 + ε1 E2 = A₁σ (T-T) 1 1-82 રંતુ + E2 2arrow_forwardFollowing page contains formulas.arrow_forward
- 1) The assembly is made of the slender rods that have a mass per unit length of 3 kg/m. Determine the mass moment of inertia of the assembly about an axis perpendicular to the page and passing through point O. 0.4 m 0.8 m 0.4 marrow_forwardanswer asaparrow_forwardA radio controlled aircraft is instrumented with an airspeed sensor and a power module, which measures the airspeed V [m/s] with an uncertainty of ± 0.8 [m/s], the battery voltage E [V] with an uncertainty of ± 0.8 [V] and the current draw i with an uncertainty of ± 0.8 [A]. These sensors are used to estimate the coefficient of drag CD of the aircraft. For this purpose, the aircraft was flown under cruise condition at a constant speed, maintaining a constant altitude and the airspeed was recorded as V=10 [m/s]. A battery voltage of E=11.1 [V] and current draw i= 1[A] was also recorded. Prior to take off the weight of the aircraft was recorded using a scale as 0.8 [N] ± 0.03 [N], and the planform area S of the aircraft was found using a CAD model as 0.35 [m^2]. The air density p relevant to flight conditions was found to be p =1.225 [kg/m^3] and the propulsion efficiency was found to be 0.4. The coefficient of drag CD for cruise flight is governed by the following equation. Provide the…arrow_forward
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