3-1 ques papers

Code No.:150479

III B.Tech. I-Semester Examinations December, 2006.

AEROSPACE PROPULSION-I (Aeronautical Engineering)Time:3 hours Max.Marks:80Answer any FIVE questionsAll questions carry equal Marks

1.a) Explain the construction details and different components of an aircraft engine?b) Explain the fuel consumption characteristics of an engine?

2.a) What are the ill effects of detonation? How to prevent detonation?b) Explain the method of balancing of an aircraft engine?

3. The following data refer to a simple turbojet engine: Compressor pressure ratio = 8;Turbine inlet temperature = 1200K;Isentropic efficiencies of compressor of compressor, turbine, propelling nozzle are 0.87, 0.90, 0.95 respectively. Combustion pressure loss = 4% compressor delivery pressure. If the cruis speed and altitude are M0.8 and 10000m, then calculate: specific thrust and specific fuel consumption.

4.a) Explain the effect of prewhirl related to centrifugal compressor?b) Discuss the procedure to estimate the work done of a centrifugal compressor along with velocity triangles?

5.a) Draw the T-s diagram for one stage of axial flow compressor and derive the equation for the pressure ratio?b) Briefly discuss the blade design of axial flow compressor?

6.a) Explain the dual fuel burner?b) What are the operational requirements of a combustion chamber?

7. An axial flow compressor stage has blade roof mean and tip velocities of 150, 200 and 250 m/s respectively. The state is to be designed for a stagnation temperature rise of 200C and an axial velocity of 150 m/s, both constant from roof to tip . Assume the work done factor is 0.93 and 50% reaction at mean radius. Calculate the stage air angle at roof, mean and tip and degree of reaction at roof and tip for a free vortex design?

8. Write short notes on;a) Stability limits(b)Flame stabilization (c) Constant nozzle angle designa) Blade cooling

Code No.:150479



1.a) Explain different components of an aircraft engine?b) Draw the performance characteristics of an aircraft engine?

2.a) Explain different stages of combustion process?b) What are different types of fuel injection systems ? and explain their advantages and disadvantages?

3.a) Define the terms momentum thrust and propulsive efficiency of a aircraft propulsion system. Derive their equations?b) What is the importance of a diffuser in a compressor?

4.a) What are different non-dimensional quantities for the explanation of characteristics of a centrifugal compressor.b) Explain the performance characteristics of the centrifugal compressor.

5.a) Draw the velocity triangles of an axial flow compressor and derive the equation for the estimation of work done required?b) Draw the performance characteristic curves of an axial flow compressor?

6.a) What are the important factors affecting the combustion chamber design?b) What are different methods of flame stabilization? Explain

7.a) Explain the fuel injection system in a combustion chamber?b) Discuss the theoretical approach to determine the blade profiles and pitch/chord ratio?

8. Write short notes on:a) Gas turbine blade coolingb) Turbine characteristic curvesc) Reaction blading of gas turbine

Code No.:150479



1.a) Explain different types of aircraft engines?b) What is supercharging of an engine? Discuss its importance?

2.a) Define and discuss about Knocking? How the detonation can be prevented?b) Explain the carburetian? What are different types of carburator? Explain any one?3.a) Explain the need of cooling and lubrication? And What are different types of lubrication systems?b) Explain the working principle of propelling nozzle system with a neat diagram?

4. The following data are suggested as a basis for the design of a single sided centrifugal compressor:Power input factor= 1.04; slip factor = 0.9Rotational speed = 290 rps; overall diameter of the Impeller = 0.5m; eye tip diameter = 0.3 m;Eye roof diameter=0.15m; mass flow rate of air = 9kg/sInlet stagnation temperature = 295 K;Inlet stagnation pressure = 1.1 barIsentropic efficiency = 0.78Calculate;(a) The pressure ratio of the compressor and the power required to drive it assuming that the velocity of the air at inlet is axial and (b)The inlet angle of the impeller vanes at the roof and tip radii of the eye, assuming that the axial inlet velocity is constant across the eye annulus

5.a) Define the term degree of reaction of an axial flow compressor? And derive its equation?b) Discuss the design procedure of an axial flow compressor?

6.a) What are different types of combustion chambers? Explain the can type combustor?b) Define the term combustion intensity? ? And explain its importance in design of combustion chamber?

7.a) Explain different methods too reduce pollution from gas turbine emissions?b) What are the limiting factors while designing a gas turbine?8.a) What is called vortex blading? Explain free vortex design?b) Name different methods of turbine blade cooling? Explain film cooling

Code No.:150479



1.a) Classify the air craft engines? Discuss the advantages and disadvantages of

different engines?b) Explain the supercharging of an aircraft engine?

2.a) Explain the effect of detonation on performance of an engine?b) What are different causes for detonation? And explain methods to prevent detonation?

3. Explain the methods to account for different component losses of a turboprop engine?

4.a) Explain the principle operation of a centrifugal compress with a neat sketch?b) Derive the equation for actual work done and the overall stagnation pressure ratio of a centrifugal compressor?

5.a) What are different factors effecting the pressure ratio of an axial flow compressors? Explain b) Compare the turbine rotor blades with a compressor rotor blades?

6.a) What are the important factors while assessing the combustion chamber performance? Explain.b) Explain flame tube cooling?

7.a) Draw the diagram of Duplex and spill burner for fuel injection system? Explainb) Discuss the performance characteristic curves of a gas turbine?

8. An axial flow gas turbine has a degree of reaction of 30%. The blade speed at the mean diameter is 300 m/s and the mass flow rate is 2.5 kg/s. The gas temperatures at turbine inlet and outlet are 5000C and 3000C respectively. The fixed blade outlet angle is 200. The axial velocity remains constant at 200 m/s. Draw the velocity diagrams and determine the power developed?

Code No: RR312103 Set No. 4III B.Tech I Semester Regular Examinations, November 2006AERODYNAMICS-II(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. For a 2D flow of incompressible air near the surface of a flat plate, the stream- wise(or x) components of velocity may be approximated by the relation U = a1yx-0.5-a2y3x-1.5a1 and a2 are constants Using the continuity equation, find the velocity componentv in the y direction? Evaluate the constant of integration by noting that v=0 aty=0. [16]2. Show that integral conservation form of the momentum equation can be used toestimate the drag over a 2D body? [16]

3. Consider a low speed steady flow around the thin airfoil . Weknow the velocity and altitude at which the vehicle is flying. Thus we know P1 andV1. We have obtained experimental values of the local static pressure at points 2through 6. At which of these points we can use Bernoulli’s equation to determinethe local velocity? If we cannot, why not? [16]Point 2: at the stagnation point of the airfoilPoint 3: at a point in the inviscid region just outside the laminar boundary layerPoint 4: at a point in the laminar boundary layerPoint 5: at point in the turbulent boundary layerPoint 6: at a point in the inviscid region just outside the turbulent boundary layer4. Derive the pressure and velocity distribution for flow about a rotating cylinder?Also calculate lift and drag forces? Draw the stream lines showing stagnationpoints? [16]5. (a) Define an airfoil? Draw a neat sketch?(b) Define Chord, Camber, Mean camber line, Leading edge radius and Thicknessof an airfoil? Draw a neat sketch of the airfoil by showing all these features?[16]6. Using thin airfoil theory show that for a cambered airfoil location of centre ofpressure Xcp= (C/4)[1 + (p/C1)(A1-A2)]7. Explain the following [16](a) Wing tip vortices, downwash(b) Induced AoA and Induced drag(c) Span wise lift distribution over a finite wing.8. Discuss and prove the statement that minimum induced drag of wing is associatedwith the elliptical loading? Plot the curve showing the induced drag coeficientagainst lift coeficient for wing of aspect ratio 7.63

Code No: RR312103 Set No. 3III B.Tech I Semester Regular Examinations, November 2006AERODYNAMICS-II(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. For a 2D flow of incompressible air near the surface of a flat plate, the stream- wise(or x) components of velocity may be approximated by the relation U = a1yx-0.5-a2y3x-1.5a1 and a2 are constants Using the continuity equation, find the velocity componentv in the y direction? Evaluate the constant of integration by noting that v=0 aty=0. [16]2. Show that integral conservation form of the momentum equation can be used toestimate the drag over a 2D body? [16]3. The velocity field is of 2D flow is given below. u = x2+y2v = 2xy2 Is the flowis incompressible? Is it a irrotational flow? If so calculate the velocity potentialfunction? [16]

4. A uniform flow is added to a doublet flow. Show that the resulting flow is flow overa circular cylinder of radius r = R = [k/2pV1]1/2Here k - strength of doubletV1 - velocity of uniform flow [16]5. Write a short note on development of NACA airfoils? In 4 digit, 5 digit and 6 digitairfoils, what does these digits means? [16]6. Explain the thin airfoil theory and its application to a cambered airfoil? [16]7. What is effective AoA? Why AoA changes at the local airfoil sections of a wing?Explain? What is induced drag? [16]8. The span wise distribution of circulation on an untwisted rectangular wing of aspectratio 5 can be written in the form of??(y) = 2bV1a[0.02340sin?+0.00268sin3? + 0.00072sin5?+0.00010sin7?]Calculate the lift and induced drag coefficients when the zero lift angle of attack is10 degrees.

Code No: RR312103 Set No. 2III B.Tech I Semester Regular Examinations, November 2006AERODYNAMICS-II(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. Explain the Importance of aerodynamics in the design of aircraft? Also discussabout the some non-aeronautical applications of aerodynamics? [16]2. Show that integral conservation form of the momentum equation can be used toestimate the drag over a 2D body? [16]3. Mention the various applications of Bernoulli’s equation? Explain the functioningand applications of pitot-static probe with a neat sketch? [16]4. Derive the stream function and velocity potential function for a double flow? Sketchthe stream line pattern? [16]5. (a) Define an airfoil? Draw a neat sketch?(b) Define Chord, Camber, Mean camber line, Leading edge radius and Thicknessof an airfoil? Draw a neat sketch of the airfoil by showing all these features?[16]6. The camber line of a thin circular arc airfoil is given by Z/c =4c(x/c)[1-(x/c)]. Findthe lift coefficient and the moment at the quarter chord point by using thin airfoiltheory. [16]7. State the Helmholtz’s theorems? Explain the philosophy of the Prandtl’s liftingline theory? [16]8. Consider an airplane that weighs 14,700 N and cruises in level flight at 300 km/hat an altitude of 3000 m. the wing has a surface area of 17 square meters and anaspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angleof attack and aL = 0 = -1.2. If the load distribution is elliptic, calculate the valueof the circulation at the centre of the wing, the downwash, induced drag coefficient?

Take density value at 3000 m is 0.74225 kg/ m

Code No: RR312103 Set No. 1III B.Tech I Semester Regular Examinations, November 2006AERODYNAMICS-II(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. What is the physical principle behind the energy equation? Derive the energyequation by applying this principle to a fixed control volume in space? What is theform of this equation? [16]2. By considering the gradient of a scalar field, show that the velocity potential linesand stream lines are perpendicular to each other? [16]3. Mention the various applications of Bernoulli’s equation? Explain the functioningand applications of pitot-static probe with a neat sketch? [16]4. A sink of strength of 120 m2/s is situated 2 m downstream from a source of equalstrength in an irrotational uniform stream of 30 m/s. Find the fineness ratio of theoval formed by the stream line ?= 0. [16]5. Show that rotating circular cylinder in potential flow produces lift? [16]6. What are the assumptions in thin airfoil theory? By applying thin airfoil theory toa symmetrical airfoil show that Cl= 2pa.Here a is AoA. [16]7. What is elliptical lift distribution? Calculate the aerodynamic characteristics of afinite wing having elliptical lift distribution? [16]8. Consider an airplane that weighs 14,700 N and cruises in level flight at 300 km/hat an altitude of 3000 m. the wing has a surface area of 17 square meters and anaspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angleof attack and aL = 0 = -1.2. If the load distribution is elliptic, calculate the valueof the circulation at the centre of the wing, the downwash, induced drag coefficient?Take density value at 3000 m is 0.74225 kg/ m3

Code No: RR312105 Set No. 4III B.Tech I Semester Regular Examinations, November 2006AIRCRAFT STRUCTURES-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. A cantilever beam of span 5m is loaded with 50 KN at distance of 3 m from thefixed end and another load 20 KN at the free end. Find the deflection and slope atthe free end using double integration method.I = 16000 × 104mm4 E = 2 × 105N/mm2 [16]2. A cantilever beam of span 4 m is loaded with a u.d.l. of 4 KN/m over its entirespan and a point load of 50 KN at a distance of 2m from the fixed end. Determine

the maximum deflection and slope using superposition method.I = 20×107mm4 E = 2×105 N/mm2. [16]3. A propped cantilever of span L is propped at a distance L/4 from the free end andloaded at the free end by a load W. Find the prop reaction and draw the SFD andBMD. [16]4. (a) Derive the total strain energy stored in beam subjected to bending.(b) Calculate the total strain energy stored in a cantilever beam of span L sub-jected to concentrated load, P at the free end assuming uniform flexural rigid-ity EI. [16]5. AC= CB = 3m Compute the deflection at B and C using unit load method for thecantilever beam shown 5 I=2X108mm4 E=2X105N/mm26. Derive Euler critical load formula for a column with one end fixed, other end free.[16]7. An I section of length 3 m deflects by 6.35 mm under a central point load of 10.16KN, wen siple supported as a beam. Find the critical load when used as a columnwith both ends hinged. The section properties are Ixx = 468. 8×104 mm4 Iyy=58.6×104 mm4 . [16]8. (a) Define beam column(b) What are the various loadings for a beam column.

Code No: RR312105 Set No. 3III B.Tech I Semester Regular Examinations, November 2006AIRCRAFT STRUCTURES-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. Two cantilevers AB, CD of equal span L are fixed to a wall at A, C in horizontalposition paralleling separating by span L. Another beam BD of span L is kept onthe cantilevers such that it is resting on the free end of the cantilevers. A load Pis applied at the center of BD. Find the net deflection under the load assuminguniform flexural rigidity, EI [16]2. A cantilever beam of span 6 m is subjected to a point load of 40 KN at a distance4 from the fixed end and a clock wise moment of 10 KN-m at the free end. Findthe slope and deflection at the free end using superposition method.EI = 3×1014Nmm2 [16]3. A continuous overhang beam is loaded with simple supports. .Find the reactions and moments using clapeyron?s theorem of three moments.]4. A is hinged, B roller support, AB=AC= BD= DE = L= 2 m Find the verticaldeflection for the structure , under a load of 20KN usingCastiglino‘s theorem L=2m,area of each member is 100mm2 E=2×105 N/mm25. A quarter ring of radius R fixed at A and loaded at free end B by point downwardload P as shown in figure5. Find the horizontal and vertical deflections at B usingunit load method. EI =constant.6. Compare the strength of solid circular column of diameter 200mm and hollow -

circular column of same cross-sectional area and thickness 30mm.The other para-meters are same for both the sections [16]7. Compare the crippling loads given by Rankine’s formula and Euler’s Formula for atubular strut having outer and inner diameters as 37.5 mm And 32.5 mm respec-tively loaded through pin joints at both ends. The critical stress is 32.5 KN/cm2.k1= 1/7500 E = 2× 105 N/mm2. [16]8. (a) Define beam column(b) What are the various loadings for a beam column.

Code No: RR312105 Set No. 2III B.Tech I Semester Regular Examinations, November 2006AIRCRAFT STRUCTURES-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. A simply supported beam of rectangular section having span 6m, is subjected toUDL ‘w’ over its whole length. The maximum bending stress is 9.6 N/ mm2. Findthe depth of the beam, if the maximum deflection is limited to 1/ 1500 of span. E= 0.15 N/mm2 [16]2. A simple supported flitched beam (composite) of span 2m carries a U.D.L of 10KN/m over its entire span. The beam is made of aluminum 100× 50mm2 reinforcedwith steel plates 50×10 mm2 . Determine the maximum deflection and slope forthe composite beam. Esteel = 3.5× Ewood. Esteel = 2×105 N/mm2. [16]3. A fixed beam of span L is subjected to a point load W at the center. Find the endreactions and moments. Draw the shear force and bending moment diagrams. [16]4. A cantilever beam AB is subjected to uniformly distributed load w per unit length.The length of cantilever is L and its flexural rigidity EI is constant the . Determine the deflection at a distance L/2 from the free end usingCastiglino‘s theorem.5. Find the deflection and slope using unit load method at the free end of a cantileverbeam loaded , assuming uniform flexural rigidity, EI.6. Determine the limiting length of a pin-ended column of section 60mm×100mm sothat the critical stress is 250 N/mm2AssumeE=2×105N/mm2 [16]7. Find the buckling load for a steel column 5 m long, made up of four equal L sectionsplaced each placed back to back . Assume both ends are fixed.The critical stress is 32.5 KN/cm2. k1= 1/75008. A beam column of span L, which is fixed at both ends is subjected to moment M,at a distance L/3 from right end, followed by axial compressive load P,(a) Write the beam column equations for buckling at a section(b) Give the boundary conditions.

Code No: RR312105 Set No. 1III B.Tech I Semester Regular Examinations, November 2006

AIRCRAFT STRUCTURES-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. A steel shaft 300 mm diameter , 5m long is used a cantilever. The cantilevercarries a point load of 40 KN at its free end. Determine the slope and deflection ata distance 2 m from the free end. E = 2×105N/mm2 [16]2. (a) Explain Beams of constant strength(b) A cantilever beam of span L with point load at free end is of rectangular cross-section. Determine the cross-section and draw the beam of constant strength[16]3. A SSB of span L is carrying a UDL,‘w’ over its entire length and propped at thecenter. Find the prop reaction and draw the SFD and BMD. [16]4. The structure is supported simply at A and E as shown in (figure4).AB =BC=CD=DE=FB=GC=HD= 1m Area of each member is 100mm2E=2×105N/mm2.Determine the vertical deflection under the 100KN load using Castiglino’s theorem.[16]5. Find the horizontal deflection at C using unit load method for the frame when horizontal force P is applied at B. EI =constant.6. A slender column,3m long ,36mm in diameter transmits a longitudinal thrust Pacting at the center of the ends. The strut is initially slightly bent the initialcentral deflection is 5mm.Find the total max. deflection and the max.compressivestress induced in the section ,when P=9KN,E=210GN/ mm2 [16]7. A steel rolled joint ISMB300 is to be used as a column of 3m long with both endsfixed. Find safe axial load on the column using Rankine’s theory. Factor of safetyis 3. Crushing stress is 320N/mm2K=a=1/7500.Properties of the column sectionArea=5626mm2Ixx=8.603×107mm4Iyy=4.539×107mm4 [16]8. A beam-column of span L, which is hinged at one end and roller supported at theother end is subjected to axial compressive load P at the ends followed by clockwisemoment at the middle(a) Write the beam column equations considering buckling at section(b) Give the boundary conditions

Code No: RR312106 Set No. 4III B.Tech I Semester Regular Examinations, November 2006AERO SPACE PROPULSION-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?

1. Consider an air standard Brayton cycle, where the air enters the compressor at0.12 Mpa,25o C .It leaves the compressor at 0.5 Mpa. TIT is 1000o C. Determinepressure and temperature at each point in the cycle.Work out the efficiency of itscompressor,turbine and the overall engine. [16]2. A turbo-prop driven airplane is flying at 680 Km / h at an altitude where the ambi-ent conditions are 0.458 bar and -10oC. The compressor pressure ratio is 9.5:1 andthe turbine inlet temperature is 1250 K. The isentropic efficiencies of compressorand turbine are 0.85 and 0.90 respectively. Assuming that no thrust is generatedby the jet exhaust from the engine; calculate the specific power input available tothe propeller. [16]3. Consider a front air intake for a subsonic turbojet airplane as that for He-178 orF-86 Saber jet. Show the internal layout for the air to be swallowed by the engine.Explain its aerodynamics and thermodynamics in details when the airplane divesat higher angles in its flight. [16]4. Consider a supersonic airplane with Ear type air intakes ahead of the wing rootends on the fuselage. Describe its aerodynamics and thermodynamics at its designMach number at a small angle of yaw. [16]5. Enumerate the various factors affecting the performance of a combustion chamber.How ‘combustion efficiency’ and ‘combustion intensity’ affect the performance?[16]6. Find the dimensions and the values of Cfg, Fg and CV of an axisymmetric exhaust-nozzle with a mass flow rate of 75kg/s with the following given data:Pt8 = 350 kPa Tt8 = 1600KA9/A8 = 1.8 R = 0.287 kJ/kg.K ? = 1.33Pt9/Pt8 = 0.98 CD = 0.98 P0 = 40 kPa [16]7. (a) How do you classify centrifugal compressors? Explain how physically thepressure ratio is achieved in practice. What are the limitations of a centrifugalcompressor?(b) Define and differentiate between ‘slip factor’ and ‘power input factor’. [16]8. Explain the following with respect to axial flow compressor:(a) Cascade characteristics(b) Reynolds and Mach number effects.

Code No: RR312106 Set No. 3III B.Tech I Semester Regular Examinations, November 2006AERO SPACE PROPULSION-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. Consider an air standard Brayton cycle, where the air enters the compressor at0.1 Mpa, 18o C. It leaves the compressor at 0.5 Mpa. TIT is 900o C. Determinepressure and temperature at each point in the cycle. Work out the efficiency of itscompressor, turbine and the overall engine. [16]2. Explain with a lay out sketch the arrangement of a turbo-prop engine and itsthermodynamic cycle of operation. Describe the role of each component in an

integrated manner. [16]3. Consider a front air intake for a subsonic turbojet airplane as that for He-178 orF-86 Saber jet. Show the internal layout for the air to be swallowed by the engine.Explain its aerodynamics and thermodynamics in details when the airplane fliesnear its stalling angle in its flight. [16]4. Consider a conical spike type supersonic air inlet with fixed geometry for optimumperformance at one Mach number. Describe its aerodynamics and thermodynamicsat the design Mach number. What happens when the operating mach number isless than the design Mach number at a small angle of yaw ß = 2o ? [16]5. The overall pressure loss factor of a combustion chamber may be assumed to varywith the temperature ratio according to the law p0m2/21A2m= K1 + K2[(T02/T01) - 1]For a particular chamber having an inlet area of 0.0389m2 and a maximum cross-sectional area Am of 0.0975m2, cold loss tests show that K1 has the value of 19.When tested under design conditions, the following readings were obtained:Air mass flow, m = 9.0kg/sInlet stagnation temperature, T01 = 475KOutlet stagnation temperature, T02 = 1023KInlet static pressure, p1 = 4.47 barStagnation pressure loss = 0.27 barEstimate the pressure loss at a part load condition for which m is 7.4kg/s, T01is439K, T02 is 900K and p1 is 3.52 bar.Also for these two operating conditions, compare the values of the velocity at inletto the chamber and comment on the result. [16]6. (a) Sketch various types of exhaust nozzles for a turbojet engine. What are theiradvantages and disadvantages?(b) Explain the theory of flow in isentropic nozzles.7. Following data pertains to a centrifugal compressor:Mass flow rate = 8kg/s Pt1 =101.3kPaPressure ratio = 4.0 Tt1 = 288.16KPolytropic efficiency = 0.85 Slip factor = 0.9Inlet root diameter = 15cm V3 = 90m/sOutlet diameter of impeller = 50cm w2 = u1Inlet tip diameter = 30cmFind(a) rotational speed and r.p.m. of the rotor.(b) rotor inlet Mach number, velocity and relative flow angles at the root and tip.(c) Rotor exit velocity, Mach number, total temperature, total pressure and di-rection.(d) depth of rotor exit.(e) diffuser exit Mach number, area, total temperature and pressure. [16]8. Explain the following with respect to axial flow compressor:

(a) Cascade characteristics(b) Reynolds and Mach number effects.

Code No: RR312106 Set No. 2III B.Tech I Semester Regular Examinations, November 2006AERO SPACE PROPULSION-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. Consider an actual gas turbine engine. How does each of its parts function toaccomplish the work of the engine? Illustrate with sketches and plots. Show thevariation of various parameters across the engine. [16]2. A turbo-prop driven airplane is flying at 680 Km / h at an altitude where the ambi-ent conditions are 0.458 bar and -10oC. The compressor pressure ratio is 9.5:1 andthe turbine inlet temperature is 1250 K. The isentropic efficiencies of compressorand turbine are 0.85 and 0.90 respectively. Assuming that no thrust is generatedby the jet exhaust from the engine; calculate the specific power input available tothe propeller. [16]3. Consider Ear type air intakes for a subsonic airplane as that for Gnat / Ajit fighterplane. Show the internal layout for the swallowed air to reach the engine. Explainits aerodynamics and thermodynamics in details when the airplane takes a turn ofabout 10 in its yaw plane. [16]4. Consider a conical spike type supersonic air inlet with fixed geometry for optimumperformance at one Mach number. Describe its aerodynamics and thermodynamicsat the design Mach number. What happens when the operating mach number ishigher than the design Mach number at a small angle of attack a = 2o ? [16]5. Describe various types of combustion chambers with the help of sketches? Listdown their relative merits and demerits. [16]6. What do you understand by propelling nozzles? Differentiate between convergentand convergent-divergent nozzles. Which type is suitable for aircraft gas turbineengine and why? [16]7. A single-sided centrifugal compressor has to be designed with the following givendata:Power input factor = 1.04Slip factor = 0.9Rotational speed = 290rev/sOverall diameter of impeller = 0.5mEye tip diameter = 0.3mEye root diameter = 0.15mInlet stagnation temperature = 295KInlet stagnation pressure = 1.1barAir mass flow = 9kg/sIsentropic efficiency = 0.78(a) Determine the pressure ratio of the compressor and the power required to

drive it assuming that the air at inlet is axial.(b) Calculate the inlet angle of the impeller vane at the root and tip radii of theeye assuming that the axial inlet velocity is constant across the eye annulus.[16]8. Write notes on the following:(a) Axial compressor characteristics.(b) Compressibility effects in axial flow compressors.

Code No: RR312106 Set No. 1III B.Tech I Semester Regular Examinations, November 2006AERO SPACE PROPULSION-I(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. Consider an air standard Brayton cycle, where the air enters the compressor at0.12 Mpa, 18oC. It leaves the compressor at 0.65 Mpa. TIT is 950o C. Determinepressure and temperature at each point in the cycle. Work out the efficiency of itscompressor, turbine and the overall engine. [16]2. Making use of first principle, develop an expression for thrust developed by a jetengine with inlet area of 0.55 sq. m .A turbojet engine is under static testing ona test bed. It develops a jet speed of 550 m /s at a pressure of 1 atm at 750 K atexit of the nozzle. Considering the location at sea level, calculate the static thrustin this case. [16]3. Consider Ear type air intakes for a subsonic airplane as that for Gnat/Ajit fighterplane. Show the internal layout for the swallowed air to reach the engine. Explainits aerodynamics and thermodynamics in details when the airplane is in its flightat its maximum level speed. [16]4. Consider a conical spike type supersonic air inlet with fixed geometry for optimumperformance at one Mach number. Describe its aerodynamics and thermodynamicsat the design Mach number. What happens when the operating mach number ishigher than the design Mach number? [16]5. A gas turbine combustion chamber is supplied with liquid fuel at 325K and air at450K. The fuel approximates to C10H12 and five times the quantity of air requiredfor stoichiometric combustion is supplied. Calculate the fuel air ratio and estimatethe fuel products temperature assuming the combustion to be adiabatic and com-plete. approximate value of the products temperature.In addition to following data assume suitable value of CpC10H12(liq)+13O2 ! 10CO2+6H2O(liq), H298K = -42500kJ/kg C10H12For water at 298K, hfg = 2442 kJ/kgFor the liquid fuel, mean Cp= 1.945 kJ/kg.KComposition of air by volume = 0.79 N2, 0.21O26. Find the dimensions of an axisymmetric nozzle and the values of Cfg, Fg and CVwith the following given data:Pt8 = 30 psia Tt8 = 20000R ? = 1.33

A9/A8 = 2 R = 53.34 ft.lbf/lbm.0RPt9/Pt8 = 0.98 CD = 0.98 P0 = 5 psia(massflow)8 = 200 lbm/s. [16]7. (a) What is pre-whirl? Sketch velocity triangles with and without pre-whirl. Whatare its effects on pressure ratio developed by the compressor?(b) A compressor of a turbojet engine operates in standard sea level air with apressure ratio of 5 and an air consumption of 35kg/s at an isentropic efficiencyof 86%. Calculate the work per kg, the horsepower required to drive thecompressor and the total temperature at the compressor discharge. [16]8. Write notes on the following:(a) Axial compressor characteristics.(b) Compressibility effects in axial flow compressors.

Code No: RR312103 Set No.4III B.Tech. I Semester Regular Examinations, November -2005AERODYNAMICS-II(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks1. Explain the Importance of aerodynamics in the design of aircraft? Also discussabout the some non-aeronautical applications of aerodynamics? [16]2. The velocity components of a 2D inviscid incompressible flow are given byU = 2y - y/(x2+y2)1/2v = -2x - x/(x2+y2)1/2Find the stream function and the vorticity and sketch the stream lines. [16]3. Show that the Bernoulli’s equation is a statement of Newton’s second law for asteady, inviscid, incompressible flow with no body force? [16]4. Derive the pressure and velocity distribution for flow about a rotating cylinder?Also calculate lift and drag forces? Draw the stream lines showing stagnationpoints? [16]5. (a) What is laminar flow airfoil? Explain?(b) Write a brief note about airfoil characteristics such as lift variation and dragvariation with AoA. [16]6. What are the assumptions in thin airfoil theory? By applying thin airfoil theory toa symmetrical airfoil show that Cl= 2.Here is AoA. [16]7. Derive the fundamental equation of the Prandtl’s lifting line theory? [16]8. What is the induced drag? Explain the effect of aspect ratio on the induced drag?Consider elliptical, modified elliptical, general lift distribution for your explanation?

Code No: RR312103 Set No.3III B.Tech. I Semester Regular Examinations, November -2005AERODYNAMICS-II(Aeronautical Engineering)

Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. What are the non-dimensional numbers used in Aerodynamics. Explain their im-portance? [16]2. Show that integral conservation form of the momentum equation can be used toestimate the drag over a 2D body? [16]3. Consider a steady, inviscid, incompressible flow in a convergent divergent nozzle.Area of the nozzle and other flow properties are varying as A = A(x), V = V(x), P =P(x). Derive the continuity and momentum equations for this flow? What is themomentum equation called? [16]4. Consider the potential flow over a non-rotating circular cylinder, show that pressuredistribution is symmetrical on top, bottom surfaces and front, rear surfaces of thecylinder. [16]5. Show that rotating circular cylinder in potential flow produces lift? [16]6. Explain the thin airfoil theory and its application to a cambered airfoil? [16]7. Show that for an elliptical loading on a finite wing, the downwash induced alongits span is constant? [16]8. A monoplane weighing 73.6 KN has elliptic wings of 15.23 m in span. For a speedof 90 m/s in steady and level flight at low altitudes find(a) Induced drag(b) Circulation at the section of a distance of 3 m from the tips.

Code No: RR312103 Set No.2III B.Tech. I Semester Regular Examinations, November -2005AERODYNAMICS-II(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks1. (a) Explain the physical meaning of gradient of a scalar field. Also write themathematical expression for gradient of pressure in Cartesian coordinate sys-tem.(b) Define the divergence and curl of velocity field? Write down the mathematicalExpressions for the same? [16]2. The velocity field for a 2D flow is given as u=y / (x2+y2) and v = -x / (x2+y2)Calculate the circulation around a circular path of radius 5? Assume the S.I unitsystem. [HINT: in polar coordinate system V.dS = Vrdr+rVd] [16]3. The velocity field is of 2D flow is given below. u = x2+y2v = 2xy2 Is the flowis incompressible? Is it a irrotational flow? If so calculate the velocity potentialfunction? [16]4. Consider the potential flow over a non-rotating circular cylinder, show that pressuredistribution is symmetrical on top, bottom surfaces and front, rear surfaces of thecylinder. [16]5. Write a short note on development of NACA airfoils? In 4 digit, 5 digit and 6 digit

airfoils, what does these digits means? [16]6. Explain the thin airfoil theory and its application to a cambered airfoil? [16]7. What is effective AoA? Why AoA changes at the local airfoil sections of a wing?Explain? What is induced drag? [16]8. Explain the difference between the symmetrical and unsymmetrical loading? Whenwe can have unsymmetrical loading on the finite wings? By considering the generallift distribution derive the expression for downwash of unsymmetrical loading?

Code No: RR312103 Set No.1III B.Tech. I Semester Regular Examinations, November -2005AERODYNAMICS-II(Aeronautical Engineering)Time: 3 hours Max Marks: 80Answer any FIVE QuestionsAll Questions carry equal marks? ? ? ? ?1. What is the physical principle behind the continuity equation? Consider an un-steady viscous 3D flow, apply the above physical principle to a fixed control volumein space and derive the continuity equation? What is the form of this equation?[16]2. What is a stream function? What are the assumptions involved in defining it? Howthe mass flow between two stream lines is related to stream function? [16]3. Consider a low speed steady flow around the thin airfoil shown below Figure-1. Weknow the velocity and altitude at which the vehicle is flying. Thus we know P1 andV1. We have obtained experimental values of the local static pressure at points 2through 6. At which of these points we can use Bernoulli’s equation to determinethe local velocity? If we cannot, why not? [16]Point 2: at the stagnation point of the airfoilPoint 3: at a point in the inviscid region just outside the laminar boundary layerPoint 4: at a point in the laminar boundary layerPoint 5: at point in the turbulent boundary layerPoint 6: at a point in the inviscid region just outside the turbulent boundary layer4. Derive the pressure and velocity distribution for flow about a rotating cylinder?Also calculate lift and drag forces? Draw the stream lines showing stagnationpoints? [16]5. By considering the potential flow over a rotating circular cylinder, derive the equa-tion of Cp in terms of radius of the cylinder R, Circulation around the cylinder ?? ,and free stream velocity V1? Show that this expression reduces to Cp = 1-4sin2.[16]6. The NACA 4412 airfoil has a mean camber line given by (Z/C) = 0.25[0.8(x/c) - (x/c)2], using thin airfoil theory(a) L=0(b) Cl when

= 30 [16]7. Show that for an elliptical wing, downwash is constant along its span? [16]8. Explain the difference between the symmetrical and unsymmetrical loading? Whenwe can have unsymmetrical loading on the finite wings? By considering the generallift distribution derive the expression for downwash of unsymmetrical loading?

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