Fundamentals Aerodynamics

KINEMATICS OF VISCOSITY

IDEAL GAS LAW

UNIVERSAL GAS CONSTANT (R)

1. ENGLISH AND METRIC

STANDARD SEA LEVEL VALUES

1. PRESSURE

2. TEMPERATURE

3. DENSITY

4. COEFFICIENT OF DYNAMIC VISCOSITY

SEA LEVEL TO TROPAPAUSE (0KM - 11KM, 0FT - 36000FT)

1. TEMPERATURE VARIATION

2. PRESSURE VARIATION

3. DENSITY VARIATION

LAPSE RATE (a)

1. ENGLISH AND METRIC (m and km)

STRATOSPHERE (11KM - 25KM, 36000FT - 82000FT)

1. TEMPERATURE VARIATION

2. PRESSURE VARIATION

3. DENSITY VARIATION

CONTINUITY EQUATION / MASS FLOW (INCOMPRESSIBLE)

1. M IS < OR > 3?

2. FORMULA?

3. WHAT IS ITS DIFFERENTIAL FORM?

CONTINUITY EQUATION / MASS FLOW (INCOMPRESSIBLE)

1. M IS < OR > 3?

2. FORMULA?

3. WHAT IS ITS DIFFERENTIAL FORM?

INCOMPRESSIBLE BERNOULLI EQUATION

LOW SPEED SUBSONIC WIND TUNNEL (INCOMPRESSIBLE)

1. Q?

2. PRESSURE DIFFERENCE?

3. THROAT TO INLET RATIO?

4. CONTRACTION RATIO FORMULA?

SPECIFIC GRAVITY

1. FORMULA

2. WATER DENSITY?

3. MERCURY DENSITY?

COMPRESSIBLE BERNOULLI EQUATION

ISENTROPIC RELATION

1. PRESSURE

2. DENSITY

3. TEMPERATURE

4. SPECIFIC VOLUME

5. SPECIFIC WEIGHT

6. SPEED OF SOUND

ENERGY EQUATION

1. USING ENTHALPY AND CP FORMULA

SPEED OF SOUND

MACH NUMBER

CONVERSION

1. MPH TO FT/S

2. KNOTS TO FT/S

1. 22 / 15

2. 76 / 45

TOTAL PRESSURE ( INCOMPRESSIBLE)

AIRSPEED

1. TRUE AIRSPEED

2. EQUIVALENT AIRSPEED

REYNOLDS NUMBER

LAMINAR BOUNDARY LAYER

1. THICKNESS

2. LOCAL SKIN FRICTION COEFFICIENT (Cf)

3. SHEAR STRESS

4. TOTAL SKIN FRICTION COEFFICIENT (Cf)

5. SKIN FRICTION DRAG (Df)

TURBULENT BOUNDARY LAYER

1. THICKNESS

2. LOCAL SKIN FRICTION COEFFICIENT (Cf)

3. SHEAR STRESS

4. TOTAL SKIN FRICTION COEFFICIENT (Cf)

5. SKIN FRICTION DRAG (Df)

CRITICAL REYNOLDS NUMBER

TYPES OF FORCE

1. NORMAL

2. AXIAL

FORMULA (2D - AIRFOIL)

1. LIFT

2. DRAG

3. PITCHING MOMENT COEFFICIENT

FORMULA (3D - WING)

1. LIFT

2. DRAG

3. PITCHING MOMENT COEFFICIENT

STALL SPEED

LIFT CURVE SLOPE

AIRFOIL PRESSURE DISTRIBUTION (Cp)

1. NORMAL

2. LOWSPEED

PRANDTL GLAUERT RULE

CRITICAL VALUES

1. CRITICAL VELOCITY

2. CRITICAL PRESSURE

3. ÇRITICAL PRESSURE COEFFICIENT

KUTTA-JOUKOWSKI THEOREM (CYLINDER)

LIFT DUE TO CIRCULATION

FLAT PLATES PERPENDICULAR TO AIRSTREAM

CURVED DEFLECTING SURFACES

EFFECT OF CHANGE OF ENGINE

AVER4AGE ACCELERATION METHOD (STEPS)

1. COSINE LAW

2. CONVERT TO FT/S

3. DIVIDE TIME

4. DIVIDE GRAVITY