# ENGRMAE 158 Aircraft Performance (2013-2014)

#### ENGRMAE 158 Aircraft Performance

**ENGRMAE 158 Aircraft Performance (Credit Units: 4)** Flight theory applied to subsonic propeller and jet aircraft. Nature of aerodynamic forces, drag and lift of wing and fuselage, high-lift devices, level-flight performance, climb and glide performance, range, endurance, take-off and landing distances, static and dynamic stability and control.
Prerequisite: MAE130A. Aerospace Engineering and Mechanical Engineering majors have first consideration for enrollment. (Design units: 2)

Anderson, J.D. Introduction to Flight, 2nd Edition, McGraw Hill.

1. Ability to apply basic fluid mechanic equation such as continuity and momentum to problems (EAC a)

2. Ability to calculate the lift of an airplane given speed, weight, altitude, and airfoil configuration. (EAC a, EAC e, EAC k)

3. Ability to discern the state of the boundary layer and calculate their contribution to the overall drag of an aircraft (EAC a, EAC e, EAC k)

4. Ability to estimate the total drag of an airplane given flight condition and geometry of aircraft. (EAC a, EAC c, EAC e, EAC k)

5. Ability to predict the minimum drag and best climb performance of both jet and propeller driven aircraft. (EAC a, EAC c, EAC e, EAC k)

6. Ability to predict the range and endurance of both jet and propeller driven aircraft. (EAC a, EAC c, EAC e, EAC k)

7. Ability to estimate the minimum takeoff and landing field length required of an aircraft. (EAC a, EAC c, EAC e, EAC k)

8. Ability to deduce the stability of an aircraft given the geometry and C.G. location. (EAC a, EAC c, EAC e, EAC k)

9. Understand some basic operation of the aircraft manufacturing industry and airline industry; as well as some problems and ethical concern of both. (EAC f, EAC g, EAC h, EAC i, EAC j)

- Understanding of basic aerodynamics.
- Statics and dynamics

- Basic Fluid mechanics
- continuity & momentum
- compressibility, Mach number
- viscosity (- Reynolds number; - boundary layer)

- Lift and drag
- theory of lift
- viscous drag
- airfoil characteristics
- compressibility drag
- wing characteristics
- total airplane drag

- Airplane performance
- steady level flight (L=W, T=D)
- cl = >weight, size, altitude, speed
- thrust or power available versus thrust or power required
- airspeed constraints: maximum, minimum, optimum
- climb: rate, angle, efficiency
- range: propeller, turbojet
- endurance: propeller, turbojet
- energy-state method for time & fuel to climb
- takeoff
- landing

- Stability and control
- static & dynamic stability
- requirements of longitudinal static stability
- center-of-gravity, trim, neutral point
- comparison of conventional, canard and flying-wing

- Propulsion
- reciprocating engines & gas turbines
- propellers & momentum theory

Meets for 4 hours of lecture and 1 hour of discussion each week for 10 weeks.

Contributes toward the Engineering Topics courses and Major design experience for both Mechanical and Aerospace Engineering.

An airplane is a device that almost does not work. As a vehicle, it is unique in that it has a minimum as well as a maximum speed, and every piece of the airplane can be regarded as weight critical – particularly the structure. Development and application of the primary airplane performance equations provides a vivid illustration of the design trades in the creation of an airplane.

- Homework: 25%
- Midterm(s): 30%
- Final: 45%
- Total: 100%

Mathematics and Basic Science: 0.0 credit units

Computing: 0.0 credit units

Engineering Topics: 4.0 credit units

Engineering Science: 2.0 credit units

Engineering Design: 2.0 credit units