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Thursday, December 6, 2012

AE2032 EXPERIMENTAL AERODYNAMICS SYLLABUS | ANNA UNIVERSITY BE AERONAUTICAL ENGINEERING 8TH SEMESTER SYLLABUS REGULATION 2008 2011 2012-2013

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AE2032 EXPERIMENTAL AERODYNAMICS SYLLABUS | ANNA UNIVERSITY BE AERONAUTICAL ENGINEERING 8TH SEMESTER SYLLABUS REGULATION 2008 2011 2012-2013 BELOW IS THE ANNA UNIVERSITY 8TH SEMESTER B.E AERONAUTICAL ENGINEERING DEPARTMENT SYLLABUS, TEXTBOOKS, REFERENCE BOOKS,EXAM PORTIONS,QUESTION BANK,PREVIOUS YEAR QUESTION PAPERS,MODEL QUESTION PAPERS, CLASS NOTES, IMPORTANT 2 MARKS, 8 MARKS, 16 MARKS TOPICS. IT IS APPLICABLE FOR ALL STUDENTS ADMITTED IN THE YEAR 2011 2012-2013 (ANNA UNIVERSITY CHENNAI,TRICHY,MADURAI, TIRUNELVELI,COIMBATORE), 2008 REGULATION OF ANNA UNIVERSITY CHENNAI AND STUDENTS ADMITTED IN ANNA UNIVERSITY CHENNAI DURING 2009

AE2032 EXPERIMENTAL AERODYNAMICS L T P C
3 0 0 3
Objectives: To present the measurement techniques involved in aerodynamic testing.
UNIT I WIND TUNNEL TESTING 8
Low speed wind tunnels-estimation of energy ratio and power required supersonic win
tunnels-calculation of running time and storage tank requirements.
UNIT II EXPERIMENTS IN SUBSONIC WIND TUNNELS 10
Estimation of flow angularity and turbulence factor-calculation of CL and CD on aero foils
from pressure distribution- CD from wake survey-Test section average velocity using
traversing rakes-span wise load distribution for different taper ratios of wing
UNIT III EXPERIMENTS IN HIGH SPEED TUNNELS 10
Mach number estimation in test section by pressure measurement and using a wedge –
preliminary estimates of blowing and running pressures, nozzle area ratios, mass flow for
a given test section size and Mach number-starting problem and starting loads.
UNIT IV MEASUREMENT TECHNIQUES 9
Hot wire anemometer and laser Doppler anemometer for turbulence and velocity
measurements-Use of thermocouples and pyrometers for measurement of static and total
temperatures-Use of pressure transducers, Rotameters and ultrasonic flow meters.
UNIT V SPECIAL PROBLEMS 8
Pitot-static tube correction for subsonic and supersonic Mach numbers-boundary layer
velocity profile on a flat plate by momentum-integral method -Calculation of CD from wall
shear stress-Heating requirements in hypersonic wind tunnels-Re-entry problems.
TOTAL: 45 PERIODS
REFERENCES:
1. Rae W.H and Pope. A “Low speed wind tunnel testing” John Wiley Publication, 1984
2. Pope. A and Goin. L “High speed wind tunnel testing” John Wiley, 1985
3. Rathakrishnan. E “Instrumentation, Measurement and Experiments in Fluids”, CRC
Press, London, 2007

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