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Erstellt / Aktualisiert 22.06.2016 / 22.06.2016
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0 Exakte Antworten 3 Text Antworten 56 Multiple Choice Antworten
Fenster schliessen
  1. When air passes through an oblique shock wave,

total pressure and Mach number both decrease

total pressure and Mach number both increase

total pressure decreases while Mach number increases

total pressure increases while Mach number decreases

Fenster schliessen
  1. Flow separation on an airfoil is caused by

turbulence in the boundary layer

surface roughness

adverse pressure gradients

boundary layer transition

none

Fenster schliessen
  1. The critical Mach number for a wing increases when

its thickness increases

its sweep angle increases

its lift coecient increases

its lift coecient decreases

Fenster schliessen
  1. In straight and level flight, if the airspeed is doubled the induced drag

doubles

halves

becomes four times higher

becomes four times smaller

Fenster schliessen

In general, when the wing trailing edge flaps are deflected

the stall angle of attack may decrease but the maximum lift coefficiet increases

the stall angle of attack and the maximum lift coefficient both increase

the lift coefficient increases at all angles of attack up to the stall

Fenster schliessen

The airspeed for minimum power required

corresponds to the maximum L/D ratio

is higher than the airspeed for maximum L/D ratio

is lower than the airspeed for maximum L/D ratio

is the slowest speed at which the airplane can fly

Fenster schliessen

The static margin is defined as the distance between

the tail aerodynamic center and the airplane center of gravity

the wing-body aerodynamic and the airplane center of gravity

the wing-body aerodynamic center and the neutral point

the neutral point and the airplane center of gravity

Fenster schliessen

In a coordinated turn with 60 bank, the stalling speed is approximately

the same as in level flight

40% higher than in level flight

60% higher than in level flight

twice as high as in level flight