An increase in wing loading will…
Wing loading is directly proportional to weight, and as we have seen above, an increase in weight, increases stall speed since the wings need to fly at a higher angle of attack to generate enough lift for a given airspeed.
- Wing Loading = Weight / Wing Area
Any airplane, within the limits of its structure and the strength of the pilot, can be stalled at any airspeed.
VS = √(2W ÷ p S CLMAX)
The equation above well defines the factors affecting the stall speed, in summary; aircraft weight, air density, maximum lift coefficient, and the load factor.
AIRCRAFT WEIGHT. Stall speed is proportional with the aircraft weight. Stall speed increases, as the weight increases; and decreases as the weight decreases. |
AIR DENSITY. Aircraft stall speeds are usually given in terms of CAS or IAS as an aircraft limitations. However, as seen in the equation above, it is actually a true airspeed which is inversely proportional with the density. Therefore, although it is constant in terms of CAS/IAS, it increases with the altitude because of the density variation. |
MAXIMUM LIFT COEFFICIENT. Maximum lift coefficient may be varied by high lift devices such as flaps and slats. Higher maximum lift coefficients will result in slower stall speeds. Lowest maximum lift coefficient is obtained when flaps are retracted (airplane in clean configuration), thus highest stall speed occurs in clean configuration. |
LOAD FACTOR. Stall speed is proportional with the load factor. It increases as the load factor increases. If VSS is the stall speed of an aircraft in steady level flight, then stall speed during maneuvers will be: Or during a turn maneuver: |
Your Notes (not visible to others)
This question has appeared on the real examination, you can find the related countries below.
-
Austro Control2
-
Azerbaijan2
-
Italy1
-
Kazakhstan1
-
Liechtenstein1
-
United Kingdom1
Use Keyboard Shortcuts
