Airliner Takeoff Speeds


By "average commercial airline plane," I assume you are referring to large passenger jetliners such as Boeing and Airbus products. The takeoff speed of such aircraft varies quite a bit, depending on the takeoff weight and the use of high-lift devices like flaps (2) and slats. However, a good average speed range is about 160 mph (260 km/h) to 180 mph (290 km/h). Some typical takeoff speeds for a variety of airliners are provided below.

Aircraft Takeoff Weight Takeoff Speed
Boeing 737 100,000 lb
45,360 kg
150 mph
250 km/h
130 kts
Boeing 757 240,000 lb
108,860 kg
160 mph
260 km/h
140 kts
Airbus A320 155,000 lb
70,305 kg
170 mph
275 km/h
150 kts
Airbus A340 571,000 lb
259,000 kg
180 mph
290 km/h
155 kts
Boeing 747 800,000 lb
362,870 kg
180 mph
290 km/h
155 kts
Concorde 400,000 lb
181,435 kg
225 mph
360 km/h
195 kts

But you might be wondering just how these speeds are determined. Commercial airliners are certified under the Federal Aviation Administration (FAA) Federal Aviation Regulation (FAR) Part 25 which specifies takeoff velocity requirements that must be observed by transport aircraft. The progression of takeoff speeds dictated by these regulations is illustrated in the following figure.

Takeoff velocities for a multiengine aicraft
Takeoff velocities for a multiengine aicraft

This diagram starts with the plane at rest, indicated by V=0. The first critical speed encountered during the takeoff run is the stall speed, Vs. The stall speed is an important quantity throughout aerodynamics as it dictates the slowest speed at which an aircraft can travel and generate just enough lift to remain or become airborne. This velocity is heavily dependent upon the configuration of the plane, primarily the state of flaps, slats and other lift-control devices. Determining the stall speed is relatively straightforward using our handy dandy friend, the lift equation:

In this case, we know that we need enough lift (L) to counteract the takeoff weight (W), we know the reference area, and we know the density at the takeoff altitude. The lift coefficient that concerns us here is the maximum lift coefficient in the takeoff configuration (typically flaps down at 5 or 10) represented by C L max. This last value is by far the most difficult to estimate, but some typical values are 2 to 2.5 for a traditional airliner layout and 1.6 to 1.8 for a supersonic design. Knowing these values, we can now solve for the stall speed using the following equation.

Even though the plane is capable of taking off as soon as the stall speed is reached, it is a very unstable condition. Even the slightest change in the orientation of the plane or the condition of its control surfaces will cause the wing to lose lift (i.e. the wing stalls, hence the name "stall" speed) and the aircraft will drop back onto the runway.

Due to the danger of trying to takeoff at stall speed, a number of additional speed requirements have been implemented for safety reasons. The first of these relates to multi-engined aircraft, which covers all commercial airliners. Should an engine fail during the takeoff run, there is usually a yawing moment since the engine(s) on one side of the plane produce more thrust than those on the other side. A yawing moment, which causes the nose to turn side-to-side, is countered by a deflection of the rudder, which produces a yaw moment in the opposite direction. The two moments will then cancel each other out and keep the plane headed straight down the runway. Below a certain speed, there simply is not enough aerodynamic force generated by the rudder to produce the correcting yaw. This velocity is called the minimum control speed, Vmc.

The next critical speed, which must be at least as fast as Vmc, is also related to the failure of an engine during the takeoff run. If the engine fails fairly far down the runway, the plane might have enough speed to continue the takeoff safely. Conversely, if the engine fails early in the takeoff, there ought to be enough runway left to abort the takeoff and come to a stop. But what if the engine fails somewhere in between? To provide the pilot with some definite criteria on which to make a decision, the FAR Part 25 specifies a critical engine-failure speed, V1. Below this speed, the pilot should abort and bring the plane to a stop if an engine fails. If the engine fails after the aircraft has exceeded V1, he should continue the takeoff using the remaining engines. The critical engine speed therefore defines the point on the runway at which the distance needed to stop is exactly the same as the that required to reach takeoff speed. The resulting total takeoff distance is correspondingly known as the balanced field length.

Definition of critical engine-failure speed and balanced field length
Definition of critical engine-failure speed and balanced field length

The next velocity of interest to us is that at which the aircraft can begin to rotate its nose into the air, conveniently called the rotation speed, Vr. While Vr must be at least 5% greater than Vmc, it need not be any greater than V1.

Next comes the minimum unstick speed, Vmu, which defines the point at which the aircraft could take off if the maximum possible rotation angle were reached. This maximum angle would occur if the tail of the plane were to actually scrape the ground.

Since such a takeoff would be damaging to the plane and most unnerving to passengers, the aircraft actually lifts off at a slightly greater velocity called the liftoff speed, Vlof. Liftoff speed must be at least 10% greater than Vmu when all engines are operating and 5% greater when one engine has failed.

Now that our happy little plane has finally become airborne, it accelerates into takeoff climb speed, V2, which must be reached at an altitude high enough to clear a given obstacle. For FAR 25 aircraft, the obstacle clearance height is 35 ft (10.7 m). The takeoff climb speed must be at least 20% greater than stall speed, Vs, and 10% greater than Vmc.

These speeds are summarized below.

Speed Description FAR 25
Requirement
Vs stall speed in takeoff configuration -
Vmc minimum control speed with one engine inoperative (OEI) -
V1 OEI decision speed = or > Vmc
Vr rotation speed 5% > Vmc
Vmu minimum unstick speed for safe flight = or > Vs
Vlof liftoff speed 10% > Vmu
5% > Vmu (OEI)
V2 takeoff climb speed at 35 ft 20% > Vs
10% > Vmc

- answer by Jeff Scott, 4 August 2002


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