Total No. of Questions : 09
B.Tech.(ANE) (Sem.-5)
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Total No. of Pages : 02
AIRCRAFT PERFORMANCE
Subject Code : ANE-315
M.Code : 60524
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Time : 3 Hrs.
Max. Marks : 60
INSTRUCTIONS TO CANDIDATES :
SECTION-A is COMPULSORY consisting of TEN questions carrying TWO marks each.
SECTION-B contains FIVE questions carrying FIVE marks each and students have to attempt any FOUR questions.
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SECTION-C contains THREE questions carrying TEN marks each and students have to attempt any TWO questions.
SECTION-A
Q.1 Distinguish between the following :
(a) ‘Low Wing loading’ and ‘High wing loading’:
(b) ‘Range’ and ‘Endurance’.
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(c) ‘Aerodynamic Center’ and ‘Center of Gravity’.
(d) ‘Geometric altitude’ and ‘Geopotential altitude’.
(e) ‘Troposphere' and ‘Stratosphere’.
(f) ‘Washin’ and ‘Washout’.
(g) ‘Camber’ and ‘Camber line’.
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(h) ‘Dihedral angle’ and ‘Anhedral angle’.
(i) ‘Mach Number’ and ‘Critical Mach number’.
(j) ‘Skin friction drag’ and ‘Pressure drag’.
Q.2 Calculate the standard atmospheric values of T, p and ? at a geo-potential altitude of 30 km. The values of T, p and ? at 12 km altitude are 216.66K, 19399Nm™ and 0.31194 kg-m’ respectively. Assume Lapse rate of + 2.8 K/km above 25km altitude.
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Q.3 Explain ‘Delta Wing Aerodynamics’ at Low Speed with the help of labelled illustration/plots.
Q.4 Derive the expression for lift coefficient, drag coefficient and speed for minimum drag condition.
Q.5 Define and explain various high lift devices. Show their effect on lift curve slopes.
Q.6 Explain the nomenclature of ‘4-digit” and ‘5-digit” NACA series airfoils.
SECTION-C
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Q.7 Gulfstream-1V twin turbofan executive transport with weight of 200000N, planform area of 80 m² and drag polar as Cp = 0.015 + 0.08CL² is flying at an altitude of 10 km (?=0.413 kg/m³). Calculate :
(a) Lift coefficient corresponding to (CL²/CD)max, (CL/CD)max, and (CL³/CD)max conditions.
(b) (CL²/CD)max, (CL/CD)max and (CL³/CD)max values and their ratio.
(c) Velocities at which (CL²/CD)max, (CL/CD)max, and (CL³/CD)max occur.
Q.8 Write notes on the following :
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(a) Drag, Drag polar, Drag bucket
(b) V/STOL vehicles
Q.9 Calculate the total take-off distance at sea level of an aircraft weighing 200000N and also compare it with the value obtained from approximate relation with the help of following data (Use calculations at VLOF = 0.7VS): (Assume CD,G = 0.1 during ground roll)
CD=0.014+0.07CL² k1=0.02 Ky =4.5x10-8 b=20m
T = 65000N h=2.5m S = 90m² µ =0.035
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CLmax= 1.5 N=3 e=0.9 hos = 12m
NOTE : Disclosure of Identity by writing Mobile No. or Making of passing request on any page of Answer Sheet will lead to UMC against the Student.
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