POF T2
pof
pof
Fichier Détails
| Cartes-fiches | 336 |
|---|---|
| Langue | Deutsch |
| Catégorie | Physique |
| Niveau | Autres |
| Crée / Actualisé | 16.05.2015 / 22.07.2020 |
| Lien de web |
https://card2brain.ch/box/pof_t2
|
| Intégrer |
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Spinn, was ist das und wann?
auto-rotation which develops after an aggravated stall => asymmetrisch Staal ( Auftrieb an einem Flügel leicht nach vorne, andere leicht nach hinten) ==> Kippt über eine Seite weg
Unterschied Flat Spinn and Steil spinn?
Flat Spinn schlimmer => kl. als 45% => Flat spinn ==> Schlimmer weil Seitenruder wird kaum noch von vorne angeströmt
Spin recovery
1. Deflected rudder in opposite direction of spin 2. Elevator down, aileron neutral
Spiral Dive
Speed descending turn in which airplane is in an excessive nose down attitude => rapidly increasing speed, Excessive Angle of Bank; Rapidly increasing ROD
Unterschied Spinn and Spiral Dive
Spinn ist die v constant + Sinkrate => Spiral Dive nimmt die v und Sinkrate excessive zu
Slip
The wind doesn't meet the aircraft parallel to its centerline = >Lowering one wing and use opposite rudder to prevent a turn developing ==> Crosswinglandung
Looping?
AOA constant => Def. als Angle zur anströmenden Luft (kleiner als 8 Grad) ==> Pitch ändert im Looping
ABsolute Ceiling
Kann sie nie ganz erreichen => best rate of climb is zero
Service Ceiling Jet and Prop
ROC for Jet: mind. 500 ft/min => 300 ft/min for OEI
ROC for Prop: Mind. 100 ft/min => 50 ft/min OEI
=> ROC for Jet must be higher, weil sie viel schneller unterwegs sind => Müssen schneller reagieren
Max. Altitude
The pressure alt. up to which a specific speed can be maintained in horizontal flight without exceeding a given limitation of the thrust
Max. Operating Altitude
allowes for normal operations
VA
Design Maneuvering speed => max speed at which application of full deflection of rudder, aileron + rudder ==> Muss auf einem Kleber im Cockpit stehen
VFO
Flaps operation => V wo ich die Flaps ein und raus fahren darf
VFE
Mit der Speed, mit der ich mit ausgefahren Flaps fliegen darf
VS1
Steal speed at specific configuration
VS0
Stall speed at landing configuration
forward C.G.
Flare ist schwerer (Viel Kraft für Flare); Nose gear den ; Tail can't take the structural loads
aftward C.G.
Spin recovery, balked landing (springt weg) nose down trim, stick forces,
CP Wanderung bei Stall bzw. hohen AOA ?
vgl. wings
Strömungsabriss bei Elliptical, rectangular amd high taper and sweepback wings ?
vgl Bild
VS New ?
Vs old x\( { \sqrt{New W\over Old W }}\)
Doppler effet?
Apparent increase of a frequency =
Apparent descrease of a frequency =
rel. motion between the transmitter and the receiver of a radio wave, a change in frequency occurs
Apparent increase of a frequency = transmitter is moving towards the receiver
Apparent descrease of a frequency = transmitter is moving away from teh receiver
the AOA of an airfoil profile is defoned as the angle between
undisturbed airflow and the chord line
an aeroplane's wing angle of incident is definied as the angle between the:
Wing loading is teh ratio of:
aircraft weight to wing area
teh thickness to chord ratio of an aerofoil is:
the ratio of the max. thickness of an aerofoil section to its chord
Taper ratio?
Taper ratio is the tip chord divided by the the root chord ==> a tapered wing will have a smaller chord at the tip than at the root
In which direction acts static pressure
in all direction, is caused by the weight of air above
the angle between teh aeroplane longitudinal axis and the wing root chord line is the:
:angle of incidence
a wing would be said to e swept back if:
wing sweep angle is the angle between?
Relationship between pressure p, desnity and Temperature
p / (rho x T) = constant
The construction feature of a wing called wash out (wing twist) is:
Geometric washout (wing twist) means that:
1. Assuming no flow separation and no compressibility effects the location of teh C.P. of a positevely cambered aerofoil section: AOA decreases
2. Assuming no flow separation and no compressibility effects teh lpcation of the C.P. od a symmetrical aerofoil section: AOA decreases
3. !!! Assuming no flow separation and no compressibility effects the location of the aerodynamic centre of an aerofoil section: AOA decreases
1. moves backwards when the AOA decreases
2. is independent of AOA
3. is independent of AOA
==> genau schauen was für ein Profil!!
In a stationary susbonic streamline flow pattern, if the streamlines converge, in this part of teh pattern, the sttaic pressure willl........ and the velocity will........
decrease; increase
With a decrease in AOA ==> wohin bewegt sich der seperation point?
the separation point moves backwards
total drag of an aerofoil?
1. Form drag, Profil drag or pressure drag 2. skin friction drag
Wer (upper or lower surface) produzieren mehr lift über alle speeds hinweg?
the upper surface produces the greater proportion at all speeds
Aerodynamic centre of an aerofoil section?
=> Independent of AOA ==> approximately 25% chord IRRESPECTIVE of AOA ===> Where pitching moment coefficient does not vary with AOA
