A sailplane with a wing loading of 250 N m -2 has a best gliding angle...
A sailplane with a wing loading of 250 N m -2 has a best gliding
angle of 1.5 ° at 25 m s .Determine the coefficients a and b in the
equation for the drag coefficient Co = a + bC 2.
Also determine the minimum sinking speed and the glide angle at
which it is achieved
assuming standard sea-level conditions.
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A sailplane with a wing loading of 250 N m -2 has a best gliding
angle...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the dens...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
Consider a gliding seed similar to that of Alsomitra macrocarpa (Fig. 12.11a, also p. 261). The...
Consider a gliding seed similar to that of Alsomitra macrocarpa (Fig. 12.11a, also p. 261). The seed has a mass of 250 mg., a functional lift-to-drag ratio of 4.0, a lift coefficient under the same conditions of 0.3, and a wing area of 5000 mm^2. The seed is released 15 m above the ground and reaches its final velocity essentially immediately. a. In still air, what is the greatest horizontal distance it can go from the point of release? b....
2. A recreational airplane has a rectangular wing of constant chord c 1.0m and spanb 10m...
2. A recreational airplane has a rectangular wing of constant chord c 1.0m and spanb 10m which uses the same airfoil section from tip to tip. The lift curve slope of this airfoil is shown in the figure below. It is flying at the cruising speed of 50m/s through SSL ISA conditions. Assuming no 3D (finite span) effects (we will cover these in subsequent weeks), compute the following: (a) Cruising at sea level the angle of attack of the wing...
Please solve this with proper solution Q9 (2 Marks) A small aircraft has a wing area...
Please solve this with proper solution
Q9 (2 Marks) A small aircraft has a wing area of 50m2, a lift coefficient of 0.65 at takeoff settings, and a total mass of 5800 kg. The takeoff speed of the aircraft and the wing loading are respectively (Hint: pressure at sea level and standard atmospheric conditions) Pa)",-1.204 kg a) 209.3 km/hr and 915.6 N/m2 b) 58.13 m/s and 0.9156 kN/m2 c) 185 m/s and 1137.96 N/m2 d) 53.927 m/s and 1137.96 N/m2...
Problem 1 (20 points) An airplane weighs 180 kN and has a wing area of 160...
Problem 1 (20 points) An airplane weighs 180 kN and has a wing area of 160 m². (a) If it cruises at 112 m/s at 3000 m standard altitude, calculate the lift coefficient. (b) If the drag coefficient is 0.02, calculate the drag force and lift-to-drag ratio at cruise. (c) The plane is designed to land at velocity Vo= 1.2 Vstall with its flaps at -10°, as in Fig. 4.54 of the book. Using the sea-level density, find the landing...
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N...
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N aspect ratio=7.0 span efficiency factor= 0.85 Parasit drag coefficient = 0.03 Each Jet Engine produces 4000on of Thrust at sea level airplane is taking off at full gross weight and the runway has paved surface. Given that the maximum lift coefficient during ground roll is 2.5 and the pair of wings are 2-m above the ground. At sea-level conditions, a) (10 pts) determine the...
Question 5 (14 marks) The following are the characteristics of a single-engine light aircraft 9.8 m...
Question 5 (14 marks) The following are the characteristics of a single-engine light aircraft 9.8 m Wing span Wing area 15.2 m2 Height of wing 1.20 m All up weight 19.2 kN Power plant: 150 kW (sea-level) Propeller efficiency: 85% Maximum lift coefficient: 1.32 Parasite drag coefficient: 0.022 Oswald's efficiency factor: 0.88 Using the above data calculate the: a. stalling speed in km/h, (39.53 m/s, 142.3 km/h) aspect ratio, induced drag coefficient and hence total drag at Lift-off Stalling Speed...
use a Reynolds number of 2.6x10^5 to find using graphs 2. Consider an NACA 23015 airfoil...
use a Reynolds number of 2.6x10^5 to find using
graphs
2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
2. A recreational airplane has a rectangular wing of constant chord c 1.0m and spanb 10m which uses the same airfoil section from tip to tip. The lift curve slope of this airfoil is shown in the figure below. It is flying at the cruising speed of 50m/s through SSL ISA conditions. Assuming no 3D (finite span) effects (we will cover these in subsequent weeks), compute the following: (a) Cruising at sea level the angle of attack of the wing...
Please solve this with proper solution
Q9 (2 Marks) A small aircraft has a wing area of 50m2, a lift coefficient of 0.65 at takeoff settings, and a total mass of 5800 kg. The takeoff speed of the aircraft and the wing loading are respectively (Hint: pressure at sea level and standard atmospheric conditions) Pa)",-1.204 kg a) 209.3 km/hr and 915.6 N/m2 b) 58.13 m/s and 0.9156 kN/m2 c) 185 m/s and 1137.96 N/m2 d) 53.927 m/s and 1137.96 N/m2...
Problem 1 (20 points) An airplane weighs 180 kN and has a wing area of 160 m². (a) If it cruises at 112 m/s at 3000 m standard altitude, calculate the lift coefficient. (b) If the drag coefficient is 0.02, calculate the drag force and lift-to-drag ratio at cruise. (c) The plane is designed to land at velocity Vo= 1.2 Vstall with its flaps at -10°, as in Fig. 4.54 of the book. Using the sea-level density, find the landing...
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N aspect ratio=7.0 span efficiency factor= 0.85 Parasit drag coefficient = 0.03 Each Jet Engine produces 4000on of Thrust at sea level airplane is taking off at full gross weight and the runway has paved surface. Given that the maximum lift coefficient during ground roll is 2.5 and the pair of wings are 2-m above the ground. At sea-level conditions, a) (10 pts) determine the...
Question 5 (14 marks) The following are the characteristics of a single-engine light aircraft 9.8 m Wing span Wing area 15.2 m2 Height of wing 1.20 m All up weight 19.2 kN Power plant: 150 kW (sea-level) Propeller efficiency: 85% Maximum lift coefficient: 1.32 Parasite drag coefficient: 0.022 Oswald's efficiency factor: 0.88 Using the above data calculate the: a. stalling speed in km/h, (39.53 m/s, 142.3 km/h) aspect ratio, induced drag coefficient and hence total drag at Lift-off Stalling Speed...
use a Reynolds number of 2.6x10^5 to find using
graphs
2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24...
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