GT AE 1350 - AE 1350 Lecture #4 (21 pages)

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AE 1350 Lecture #4



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AE 1350 Lecture #4

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Pages:
21
School:
Georgia Institute of Technology
Course:
Ae 1350 - Intro to Aerospace Engr

Unformatted text preview:

AE 1350 Lecture 4 PREVIOUSLY COVERED TOPICS Preliminary Thoughts on Aerospace Design Specifications Specs and Standards System Integration Forces acting on an Aircraft The Nature of Aerodynamic Forces Lift and Drag Coefficients TOPICS TO BE COVERED Why should we study properties of atmosphere Ideal Gas Law Variation of Temperature with Altitude Variation of Pressure with Altitude Variation of Density with Altitude Tables of Standard Atmosphere Why should we study Atmospheric Properties Engineers design flight vehicles turbine engines and rockets that will operate at various altitudes They can not design these unless the atmospheric characteristics are not known L CL 1 For example from last lecture V 2 S 2 We can not design a vehicle that will operate satisfactorily and generate the required lift coefficient CL until we know the density of the atmosphere What is a standard atmosphere Weather conditions vary around the globe from day to day Taking all these variations into design is impractical A standard atmosphere is therefore defined that relates fight tests wind tunnel tests and general airplane design to a common reference This common reference is called a standard atmosphere International Standard Atmosphere Standard Sea Level Conditions Pressure 101325 Pa 2116 7 lbf ft2 Density 1 225 Kg m3 0 002378 slug ft3 Temperature 15 oC or 288 K 59 oF or 518 4 oR Ideal Gas Law or Equation of State Most gases satisfy the following relationship between density temperature and pressure p RT p Pressure in lb ft2 or N m2 Rho density in slugs ft3 or kg m3 T Temperature in Degrees R or degrees K R Gas Constant varies from one gas to another Equals 287 1 J Kg K or 1715 7 ft lbf slug oR for air Speed of Sound From thermodynamics and compressible flow theory you will study later in your career sound travels at the following speed a RT where a speed of Sound m s or ft s Ratio of Specific Heats 1 4 R Gas Constant T temperature in degrees K or degrees R Temperature vs Altitude 90 km 79



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