Helicopter Stage One

Front 1

Critical AOA

Back 1

Point where blade will start to stall. Approx 15 degrees.

Front 2

Air density

Back 2

Mass of air being encountered by the airfoil

Front 3

What two factors of the lift equation can the pilot control?

Back 3

Velocity (rotor rpm), and AOA (collective)

Front 4

3 types of drag

Back 4

Parasite, profile, and induced

Front 5

3 types of drag

Back 5

Parasite, profile, and induced

Front 6

Parasite drag

Back 6

Any body not producing lift

Front 7

3 types of drag

Back 7

Parasite, profile, and induced

Front 8

Parasite drag

Back 8

Any body not producing lift

Front 9

Profile drag

Back 9

The sum of form drag and skin friction.

Front 10

3 types of drag

Back 10

Parasite, profile, and induced

Front 11

Parasite drag

Back 11

Any body not producing lift

Front 12

Profile drag

Back 12

The sum of form drag and skin friction.

Front 13

Form drag

Back 13

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 14

3 types of drag

Back 14

Parasite, profile, and induced

Front 15

Parasite drag

Back 15

Any body not producing lift

Front 16

Profile drag

Back 16

The sum of form drag and skin friction.

Front 17

Form drag

Back 17

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 18

Skin frictiin

Back 18

The result of the slow down of the airflow in close proximity to the akin of the blades because of any surface roughness

Front 19

3 types of drag

Back 19

Parasite, profile, and induced

Front 20

Parasite drag

Back 20

Any body not producing lift

Front 21

Profile drag

Back 21

The sum of form drag and skin friction.

Front 22

Form drag

Back 22

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 23

Skin frictiin

Back 23

The result of the slow down of the airflow in close proximity to the akin of the blades because of any surface roughness

Front 24

Induced drag

Back 24

A by product of the creation of lift. Two sources. Down wash of air results from the downward reorientation of the airstream as it encounters the airfoil at any positive AOA. Pressure diff. between the upper and lower surfaces causes vortices at the wing tips.

Front 25

3 types of drag

Back 25

Parasite, profile, and induced

Front 26

Parasite drag

Back 26

Any body not producing lift

Front 27

Profile drag

Back 27

The sum of form drag and skin friction.

Front 28

Form drag

Back 28

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 29

Skin frictiin

Back 29

The result of the slow down of the airflow in close proximity to the akin of the blades because of any surface roughness

Front 30

Induced drag

Back 30

A by product of the creation of lift. Two sources. Down wash of air results from the downward reorientation of the airstream as it encounters the airfoil at any positive AOA. Pressure diff. between the upper and lower surfaces causes vortices at the wing tips.

Front 31

3 types of drag

Back 31

Parasite, profile, and induced

Front 32

Parasite drag

Back 32

Any body not producing lift

Front 33

Profile drag

Back 33

The sum of form drag and skin friction.

Front 34

Form drag

Back 34

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 35

Skin friction

Back 35

The result of the slow down of the airflow in close proximity to the akin of the blades because of any surface roughness

Front 36

Induced drag

Back 36

A by product of the creation of lift. Two sources. Down wash of air results from the downward reorientation of the airstream as it encounters the airfoil at any positive AOA. Pressure diff. between the upper and lower surfaces causes vortices at the wing tips.

Front 37

3 types of drag

Back 37

Parasite, profile, and induced

Front 38

Parasite drag

Back 38

Any body not producing lift

Front 39

Profile drag

Back 39

The sum of form drag and skin friction.

Front 40

Form drag

Back 40

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 41

Skin friction

Back 41

The result of the slow down of the airflow in close proximity to the akin of the blades because of any surface roughness

Front 42

Induced drag

Back 42

A by product of the creation of lift. Two sources. Down wash of air results from the downward reorientation of the airstream as it encounters the airfoil at any positive AOA. Pressure diff. between the upper and lower surfaces causes vortices at the wing tips.

Front 43

3 types of drag

Back 43

Parasite, profile, and induced

Front 44

Parasite drag

Back 44

Any body not producing lift

Front 45

Profile drag

Back 45

The sum of form drag and skin friction.

Front 46

Form drag

Back 46

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 47

Skin friction

Back 47

The result of the slow down of the airflow in close proximity to the akin of the blades because of any surface roughness

Front 48

Induced drag

Back 48

A by product of the creation of lift. Two sources. Down wash of air results from the downward reorientation of the airstream as it encounters the airfoil at any positive AOA. Pressure diff. between the upper and lower surfaces causes vortices at the wing tips.

Front 49

LD max

Back 49

Min drag max lift

Front 50

3 types of drag

Back 50

Parasite, profile, and induced

Front 51

Parasite drag

Back 51

Any body not producing lift

Front 52

Profile drag

Back 52

The sum of form drag and skin friction.

Front 53

Form drag

Back 53

Resistance caused by frontal impact of airflow on the airfoil as well as turbulence and suction occurring at the rear.

Front 54

Skin friction

Back 54

The result of the slow down of the airflow in close proximity to the akin of the blades because of any surface roughness

Front 55

Induced drag

Back 55

A by product of the creation of lift. Two sources. Down wash of air results from the downward reorientation of the airstream as it encounters the airfoil at any positive AOA. Pressure diff. between the upper and lower surfaces causes vortices at the wing tips.

Front 56

LD max

Back 56

Min drag max lift

Front 57

Three axes

Back 57

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 58

Three axes

Back 58

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 59

Torque

Back 59

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 60

Three axes

Back 60

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 61

Torque

Back 61

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 62

R44 landing gear

Back 62

Spring and yield skid type landing gear

Front 63

Three axes

Back 63

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 64

Torque

Back 64

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 65

R44 landing gear

Back 65

Spring and yield skid type landing gear

Front 66

When can you test an ELT.

Back 66

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 67

Three axes

Back 67

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 68

Torque

Back 68

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 69

R44 landing gear

Back 69

Spring and yield skid type landing gear

Front 70

When can you test an ELT?

Back 70

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 71

Three axes

Back 71

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 72

Torque

Back 72

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 73

R44 landing gear

Back 73

Spring and yield skid type landing gear

Front 74

When can you test an ELT?

Back 74

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 75

Axis of rotation

Back 75

Front 76

Three axes

Back 76

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 77

Torque

Back 77

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 78

R44 landing gear

Back 78

Spring and yield skid type landing gear

Front 79

When can you test an ELT?

Back 79

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 80

Axis of rotation

Back 80

Front 81

Translating tendency

Back 81

Tendency of the helicopter to move in the direction of the tail rotor thrust.

Front 82

Three axes

Back 82

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 83

Torque

Back 83

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 84

R44 landing gear

Back 84

Spring and yield skid type landing gear

Front 85

When can you test an ELT?

Back 85

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 86

Axis of rotation

Back 86

Front 87

Translating tendency

Back 87

Tendency of the helicopter to move in the direction of the tail rotor thrust.

Front 88

Pendular action

Back 88

Ability of the helicopter to oscillate 360 degrees in a pendulum like manner due to it's considerable mass being suspended from a singular point

Front 89

Three axes

Back 89

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 90

Torque

Back 90

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 91

R44 landing gear

Back 91

Spring and yield skid type landing gear

Front 92

When can you test an ELT?

Back 92

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 93

Axis of rotation

Back 93

Front 94

Translating tendency

Back 94

Tendency of the helicopter to move in the direction of the tail rotor thrust.

Front 95

Pendular action

Back 95

Ability of the helicopter to oscillate 360 degrees in a pendulum like manner due to it's considerable mass being suspended from a singular point

Front 96

Dynamic rollover

Back 96

When the helicopter has a pivot point other than the CG and a rolling moment begins. If the roll passes 15 degrees, the helicopter will roll over.

Front 97

Three axes

Back 97

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 98

Torque

Back 98

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 99

R44 landing gear

Back 99

Spring and yield skid type landing gear

Front 100

When can you test an ELT?

Back 100

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 101

Axis of rotation

Back 101

Front 102

Translating tendency

Back 102

Tendency of the helicopter to move in the direction of the tail rotor thrust.

Front 103

Pendular action

Back 103

Ability of the helicopter to oscillate 360 degrees in a pendulum like manner due to it's considerable mass being suspended from a singular point

Front 104

Dynamic rollover

Back 104

When the helicopter has a pivot point other than the CG and a rolling moment begins. If the roll passes 15 degrees, the helicopter will roll over.

Front 105

3 req for dynamic rollover

Back 105

Rolling moment, pivot point, thrust greater than weight

Front 106

Three axes

Back 106

Pitch or lateral, roll or longitudinal, and yaw or vertical

Front 107

Torque

Back 107

Rotation is clockwise (for us) and tail rotor counteracts rotation.

Front 108

R44 landing gear

Back 108

Spring and yield skid type landing gear

Front 109

When can you test an ELT?

Back 109

During the first 5 minutes after every hour. Freqs are 121.5 and 243.0.

Front 110

Axis of rotation

Back 110

Front 111

Translating tendency

Back 111

Tendency of the helicopter to move in the direction of the tail rotor thrust.

Front 112

Pendular action

Back 112

Ability of the helicopter to oscillate 360 degrees in a pendulum like manner due to it's considerable mass being suspended from a singular point

Front 113

Dynamic rollover

Back 113

When the helicopter has a pivot point other than the CG and a rolling moment begins. If the roll passes 15 degrees, the helicopter will roll over.

Front 114

3 req for dynamic rollover

Back 114

Rolling moment, pivot point, thrust greater than weight

Front 115

Coning

Back 115

Upper deflection of the blades due to the fact that the rotors are suspending the weight. Causes by lift and centrifugal force

Front 116

Takeoff profile

Front 117

Takeoff profile

Front 118

R44 coriolis