# In a free-stream and at a specific angle of attack, a particular airfoil with a chord length of… 1 answer below »

1. In a free-stream and at a specific angle of attack, a particular airfoil with a chord length of 6.2 ft generates 265 lb/ft of lift per unit span acting through a center of pressure at 0.36c, with no moment about the center of pressure. Neglecting drag, what would the equivalent force and moment system be if the lift were placed at the quarter chord point? 2. Consider an airplane in straight, level flight. If no changes are made other than burning fuel, what will eventually happen to the altitude of the airplane? 3. Using the G550 data: a. For the G550, determine the maximum value of L/D b. if one of the RR BR700 Engines is placed on a test stand and operated at maximum thrust, how long will it take to burn 1,500 gallons of fuel (6.7 lb/gal)? c. If the G550 if flying at sea level at sea level and 950 ft/s, estimate the propulsive efficiency d. Determine the low-speed lift coefficient of the Gulfstream G550 from the data given when the airplane is at 2.5-degree angle of attack. Assume a lifting slope of 0.105 per degree and a zero-lift angle of attack of -2.2 degrees e. If the G550 is flying at 41,000 ft, at what velocity does L/D max occur? f. Determine the maximum velocity of the G550 at 41,000 ft. g. Determine the maximum rate of climb for the G550 at 41,000 ft h. Regarding the G550, if it is at its maximum rate of climb at 41,000 ft, what is its velocity? i. What is the maximum climb angle of the G550 at 30,000 ft? j. What is the maximum velocity of the G550 when it is at its maximum climb angle at 30,000 ft? k. Estimate the Maximum Endurance of the G550. l. What is the maximum range of the G550 at 41,000 ft? m. What is the maximum turn rate for the G550 at 30,000 ft? n. If the G550 is flying at 560 mi/hr at 30,000 ft, calculate its energy height

Attachments: