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Consider a flying wing aircraft made using a NACA 2418 airfoil with a wing area of 22 m², wing span of 15 m, and a span efficiency factor of 0.85. The aircraft is flying at 4° angle of attack and a Reynolds number of around 6 x 106 at an altitude of 2000 m. a) What are CL and CD for the flying wing? b) If the aircraft is flying at V = 85 m/s, how much lift and drag is it experiencing? c) What is the lift to drag ratio of the aircraft? d) If the aircraft has a takeoff weight of 7500 kg and flying at the indicated angle of attack, what should be its flight speed if the compressibility effect is neglected? You can use the following relations: Cla 57.30 La 1+ ле АR Altitude (meters) 0 2,000 ; CLincomp=C₁₁ (α-α=0); C₁² = La CD=Ca + C₁² ne AR Lincomp √1-M² Table 1: Standard Atmospheric Conditions Density (kg/m³) 1.225 1.0066 Temperature Pressure (K) (Pa) 288.16 1.01325E+5 275.16 7.9501E+4 =;CD₁i C² ле АR Viscosity (N-s/m²) 1.79E-5 1.73E-5

Consider a flying wing aircraft made using a NACA 2418 airfoil with a wing area of 22 m², wing span of 15 m, and a span efficiency factor of 0.85. The aircraft is flying at 4° angle of attack and a Reynolds number of around 6 x 106 at an altitude of 2000 m. a) What are CL and CD for the flying wing? b) If the aircraft is flying at V = 85 m/s, how much lift and drag is it experiencing? c) What is the lift to drag ratio of the aircraft? d) If the aircraft has a takeoff weight of 7500 kg and flying at the indicated angle of attack, what should be its flight speed if the compressibility effect is neglected? You can use the following relations: Cla 57.30 La 1+ ле АR Altitude (meters) 0 2,000 ; CLincomp=C₁₁ (α-α=0); C₁² = La CD=Ca + C₁² ne AR Lincomp √1-M² Table 1: Standard Atmospheric Conditions Density (kg/m³) 1.225 1.0066 Temperature Pressure (K) (Pa) 288.16 1.01325E+5 275.16 7.9501E+4 =;CD₁i C² ле АR Viscosity (N-s/m²) 1.79E-5 1.73E-5

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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Consider a flying wing aircraft made using a NACA 2418 airfoil with a wing area of 22 m², wing span of 15 m, and a span efficiency factor of 0.85. The aircraft is flying at 4° angle of attack and a Reynolds number of around 6 x 106 at an altitude of 2000 m. a) What are C₁ and CD for the flying wing? b) If the aircraft is flying at V = 85 m/s, how much lift and drag is it experiencing? c) What is the lift to drag ratio of the aircraft? d) If the aircraft has a takeoff weight of 7500 kg and flying at the indicated angle of attack, what should be its flight speed if the compressibility effect is neglected? You can use the following relations: Cla 57.30 La 1+ ле АR Altitude (meters) 0 2,000 ; = Lincomp C₁₁ (α-αL=0); C₁: La Co=cat C₁² Te AR CLincomp √1-M² Table 1: Standard Atmospheric Conditions Density (kg/m³) 1.225 1.0066 Temperature Pressure (K) (Pa) 288.16 1.01325E+5 275.16 7.9501E+4 CDi C² ле АR Viscosity (N-s/m²) 1.79E-5 1.73E-5
Transcribed Image Text:Consider a flying wing aircraft made using a NACA 2418 airfoil with a wing area of 22 m², wing span of 15 m, and a span efficiency factor of 0.85. The aircraft is flying at 4° angle of attack and a Reynolds number of around 6 x 106 at an altitude of 2000 m. a) What are C₁ and CD for the flying wing? b) If the aircraft is flying at V = 85 m/s, how much lift and drag is it experiencing? c) What is the lift to drag ratio of the aircraft? d) If the aircraft has a takeoff weight of 7500 kg and flying at the indicated angle of attack, what should be its flight speed if the compressibility effect is neglected? You can use the following relations: Cla 57.30 La 1+ ле АR Altitude (meters) 0 2,000 ; = Lincomp C₁₁ (α-αL=0); C₁: La Co=cat C₁² Te AR CLincomp √1-M² Table 1: Standard Atmospheric Conditions Density (kg/m³) 1.225 1.0066 Temperature Pressure (K) (Pa) 288.16 1.01325E+5 275.16 7.9501E+4 CDi C² ле АR Viscosity (N-s/m²) 1.79E-5 1.73E-5
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Consider a flying wing aircraft made using a NACA 2418 airfoil with a wing area of 22 m², wing span of 15 m, and a span efficiency factor of 0.85. The aircraft is flying at 4° angle of attack and a Reynolds number of around 6 x 106 at an altitude of 2000 m. a) What are C₁ and CD for the flying wing? b) If the aircraft is flying at V = 85 m/s, how much lift and drag is it experiencing? c) What is the lift to drag ratio of the aircraft? d) If the aircraft has a takeoff weight of 7500 kg and flying at the indicated angle of attack, what should be its flight speed if the compressibility effect is neglected? You can use the following relations: Cla 57.30 La 1+ ле АR Altitude (meters) 0 2,000 ; = Lincomp C₁₁ (α-αL=0); C₁: La Co=cat C₁² Te AR CLincomp √1-M² Table 1: Standard Atmospheric Conditions Density (kg/m³) 1.225 1.0066 Temperature Pressure (K) (Pa) 288.16 1.01325E+5 275.16 7.9501E+4 CDi C² ле АR Viscosity (N-s/m²) 1.79E-5 1.73E-5
Transcribed Image Text:Consider a flying wing aircraft made using a NACA 2418 airfoil with a wing area of 22 m², wing span of 15 m, and a span efficiency factor of 0.85. The aircraft is flying at 4° angle of attack and a Reynolds number of around 6 x 106 at an altitude of 2000 m. a) What are C₁ and CD for the flying wing? b) If the aircraft is flying at V = 85 m/s, how much lift and drag is it experiencing? c) What is the lift to drag ratio of the aircraft? d) If the aircraft has a takeoff weight of 7500 kg and flying at the indicated angle of attack, what should be its flight speed if the compressibility effect is neglected? You can use the following relations: Cla 57.30 La 1+ ле АR Altitude (meters) 0 2,000 ; = Lincomp C₁₁ (α-αL=0); C₁: La Co=cat C₁² Te AR CLincomp √1-M² Table 1: Standard Atmospheric Conditions Density (kg/m³) 1.225 1.0066 Temperature Pressure (K) (Pa) 288.16 1.01325E+5 275.16 7.9501E+4 CDi C² ле АR Viscosity (N-s/m²) 1.79E-5 1.73E-5
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