= = At PHAA with (n = 3.9) and (CL CLmax = 1.70), the Triton SX3...

  

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= = At PHAA with (n = 3.9) and (CL CLmax = 1.70), the Triton SX3 aircraft has a documented distributed wing lift load (= 20.6 lb/inch), distributed wing drag load (d = 1.97 lb/inch), and distributed wing weight (w = 0.41 lb/inch). These three values were accurately determine at one location along the wing span (2*x/b = 0.30). Assume the aircraft flight path is horizontal (steady level flight) and the wing angle of attack is (a 18 degrees), calculate the distributed structural load that is parallel to the airfoil chord. Assume a positive load is pointed rearward (i.e. trying to bend the wing backwards). (Units: lb/inch) = = At PHAA with (n = 3.9) and (CL CLmax = 1.70), the Triton SX3 aircraft has a documented distributed wing lift load (= 20.6 lb/inch), distributed wing drag load (d = 1.97 lb/inch), and distributed wing weight (w = 0.41 lb/inch). These three values were accurately determine at one location along the wing span (2*x/b = 0.30). Assume the aircraft flight path is horizontal (steady level flight) and the wing angle of attack is (a 18 degrees), calculate the distributed structural load that is parallel to the airfoil chord. Assume a positive load is pointed rearward (i.e. trying to bend the wing backwards). (Units: lb/inch)