Wave drag coefficient for a hypersonic flat plate is a dimensionless quantity that measures the ratio of the wave drag force to the dynamic pressure times the reference area of the plate. Wave drag is the drag due to shock waves that form on the surface of the plate when it moves at speeds higher […]
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The total drag coefficient is the sum of the wave-drag coefficient cd,w and the friction-drag coefficient cd,0. This is a statement that describes the total drag or resistance of a body moving at supersonic or hypersonic speeds in a fluid environment, such as air or water. The wave-drag coefficient cd,w is the drag due to
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The total drag coefficient for a flat plate is a dimensionless quantity that measures the total drag or resistance of a flat plate in a fluid environment, such as air or water. It is composed of Zero lift drag coefficient (cd,0). Total drag coefficient (cd) Zero lift drag coefficient (cd,0)
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The thrust-to-weight ratio (T/W) is a critical parameter in aircraft design and performance analysis. It represents the ratio of an aircraft’s engine thrust (T) to its total weight (W). This ratio provides valuable information about an aircraft’s ability to accelerate, climb, and perform various flight maneuvers. The formula for calculating thrust-to-weight ratio is straightforward: T/W
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The drag polar is a graphical representation of an aircraft’s drag characteristics at various angles of attack and airspeeds. It typically consists of a curve that shows how the aircraft’s drag coefficient (CD​) changes with changes in angle of attack (α) or airspeed. The formula for the drag coefficient (CD​) itself is not a simple
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The term “(L/D)max” refers to the maximum lift-to-drag ratio that an aircraft can achieve. It is a crucial parameter in aircraft design and performance analysis because it indicates the point at which the aircraft is operating most efficiently in terms of generating lift for a given amount of drag. Pilots and engineers use this ratio
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The fuel fraction during a loiter phase of flight, often referred to as “FFL” (Fuel for Loiter) or “Loiter Fuel Fraction,” represents the proportion of an aircraft’s total fuel consumption that is typically consumed during a loitering or holding pattern phase. Loitering occurs when an aircraft circles or remains in a holding pattern before proceeding
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The fuel fraction during the cruise phase of a flight, often referred to as “FFC” (Fuel for Cruise) or “Cruise Fuel Fraction,” represents the proportion of an aircraft’s total fuel consumption that is typically consumed during the cruise phase of a flight. This fraction is used to estimate the fuel required for maintaining level flight
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The fuel fraction for the climb phase of a flight, often referred to as “FC” (Fuel for Climb) or “Climb Fuel Fraction,” represents the proportion of an aircraft’s total fuel consumption that is typically consumed during the climb phase of a flight. This fraction is used to estimate the fuel required to ascend from takeoff
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The fuel fraction for warm-up, taxiing, and take-off, often referred to as “WTT” (Warm-up, Taxi, and Take-off) fuel fraction, is a parameter used in aircraft design and performance analysis. It represents the proportion of an aircraft’s total fuel consumption that is typically consumed during the warm-up, taxiing, and take-off phases of a flight. This fraction
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