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What is the thrust to weight ratio of earth?
The thrust-to-weight ratio is a measure typically used in the context of vehicles, particularly aircraft and rockets, to determine their ability to accelerate. For Earth as a planet, this concept isn't directly applicable since Earth does not produce thrust like a vehicle. However, if we consider the gravitational force (weight) acting on Earth itself, the concept doesn't yield meaningful values, as "thrust" is not a relevant factor in the context of a planet's mass and gravity. Instead, Earth is primarily characterized by its mass (approximately 5.97 x 10^24 kg) and gravitational acceleration (about 9.81 m/s² at its surface).
How much thrust is required to propel 5kg RC plane?
A thrust to weight ratio of 1:1 is good on RC planes so I'd recommend 5KG of thrust
If thrust is 45 pounds how much weight can that lift?
If the thrust is directed straight down and torque is counteracted, the weight it can lift is less than 45 pounds. It requires at least 45 pounds of thrust just to make 45pounds of vtol aircraft hover . It takes more than that to make it climb vertically up. To climb implies an acceleration against gravity and it takes at least 45 pounds thrust just to balance gravity's pull against a 45pound mass. With a winged aircraft the thrust can be less than the total weight of the aircraft and it can still fly and climb with less thrust than the mass of the plane. A high lift to drag ratio of the wing and effective wing area means that the thrust of the plane overcomes the drag of the plane. The wing's passage through the air creates the lift. The drag caused by the creation of 45pounds of lift is less than 45 pounds for an efficient wing.
How can aircraft easily achieve much higher speeds than ships?
Less friction. (ships continuously have to push their way through water, and planes only have to push through air) Planes have a better thrust to weight ratio.
Do heavier airplanes fly faster?
Not necessarily. The aircraft with better power to weight ratio will fly fastest.
What is power-to-weight ratio of steam turbine and gas turbine?
there is a mathematical formula to figure the actual power measured in Inchpounds of torque for both types of turbine engines. due to the light weight of the engine and the very high speeds in which they operate they are very efficient compared to other type of power plants generally the rough power to weight ratio of a typical aircraft turbine engine is around 85 to 95% output power compared to the actual weight of the type engine used.the exception to this would be a turbo-fan engine used on high speed aircraft which the power output is measured in footpounds of thrust
Why is duralumin use in aircraft?
duralumin is low density alloy, it has a high strength to weight ratio making it ideal to use in aircrafts.
How much horsepower does an F 15 Eagle have?
The F-15 Eagle is powered by two Pratt & Whitney F100-PW-100 or F100-PW-220 engines, each producing approximately 25,000 pounds of thrust. When converted to horsepower, this equates to around 50,000 to 60,000 horsepower combined, depending on the engine variant and specific performance conditions. The aircraft's thrust-to-weight ratio allows it to achieve impressive speed and maneuverability.
What important property of aluminium make it great demands in industry?
It's weight to strength ratio which makes it an ideal metal for aircraft and the automotive industries .
What is the importance of lift to drag ratio?
In aircraft aerodynamics, the lift-to-drag ratio, or L/D ratio, is the amount of lift generated by an aerofoil, divided by the drag it creates by moving through the air. A higher or more favourable L/D ratio is typically one of the major goals in aircraft design; since a particular aircraft's required lift is set by its weight, delivering that lift with lower drag leads directly to better fuel economy, climb performance, and glide ratio.
Why does glide ratio not change with aircraft weight?
"Who said it doesn't? Of course it changes. The Lift force has to equal the weight of the aircraft. The amount of lift generated is a function of airspeed and angle of attack. Lift does not increase just because the aircraft weighs more. So, if two aircraft are identical other than weight, the lighter one glides further."Incorrect ! Absolutely wrong!Glide ratio (L over D or L/D) is NOT affected by aircraft weight. The glide ratio is a factor of the physical form of the aircraft; the drag produced by the aircraft shape & profile and the lift produced by the wings.Those factors do not change and we are speaking of aircraft best glide ratio, so, by definition, while producing the least drag which means landing gear retracted & flaps up, referred to as "clean".Aircraft manuals (POH- pilot operating handbook) that list glide ratio & often the speed at which to fly to achieve best glide ratio (greatest distance the aircraft will fly) always refer to aircraft maximum gross weight. If the aircraft weighs less, the best glide speed will be lower.A rule of thumb; for every 10% (1%) below gross weight, reduce speed by 5% (.5%) to achieve best glide speed.A Cessna 172 empty weight is about 69% of maximum gross weight. W/ min. fuel and 150lb pilot the plane weighs about 76% of gross, so 24% less weight = 12% reduction in speed to arrive at best glide, reducing best glide from 65 kts at gross weight to 57kts at minimal weight.This can be significant and determine if the plane reaches the planned touchdown point.Conclusion is, a heavier aircraft will glide the same distance as a lighter aircraft (of identical make/model) but it will need to be flown at a higher speed to do so.Yes, the lift produced is a function of airspeed & angle of attackas best glide ratio is a function of angle of attack (AoA). So a specific AoA must be achieved to insure best glide / longest distance over the ground.The most perceived difference between lighter and heavier aircraft is, the heavier aircraft arrives in the same spot, faster.The same effects are in play with air density and higher altitude.Air is thinner, less lift and less drag, but Lift over Drag (L/D) is still a factor of the physical structure, shape/ profile and the lift produced by the wings.This does not change when the air is thinner.I do not have information as to how to adjust the speed for best glide ratioas altitude increases and air density decreases.It is amazing how many pilots and aviation professionals do not understand this.
What are the advantages of solid fueled rocket engines?
Solid fueled rocket engines are relatively simple in design, have a high thrust-to-weight ratio, and are easy to store and transport. Additionally, they can provide a lot of thrust in a short amount of time, making them ideal for quick acceleration needs.
