A Boeing 747 has a wing span of 195.7 feet and a 6.95 aspect ratio. It...

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A Boeing 747 has a wing span of 195.7 feet and a 6.95 aspect ratio. It cruises at 500 mph at a weight of 550,000 pounds at 35,000 feet (density of 0.000737 slug/ft³). Assume that the Reynolds number can be approximated using: R₁ =9324 x V x c where V is the average speed in mph, e the average chord in feet. Assuming that the wing sweep and twist combine to give an essentially elliptical spanwise circulation distribution find: 1. From the given data, show that the span area is 5511 ft². 2. From the given data, show that the average elliptic chord is 35.85 ft. 3. From the given data, show that the Reynolds number is 1.67 × 10%. 4. Show that the cruise speed is 733 ft/s. 5. Show that the coefficient of lift is 0.50. 6. Show that I = 6.6 x 10³ ft²/s. 7. Show that downwash velocity is w = -16.9 ft/s. 8. Show that the coefficient of induced drag is 116 counts. 9. Show that the induced Drag has a value of 12.7 x 10³ lb. 10. Show that the induced angle of attack is approximately 1.32⁰. 11. Show that the coefficient of profile drag is c = 0.0088. Assume you can use the value for a flat plate with a correction factor of 1.75. 12. Show that the coefficient of proof drag at cruise is c = 0.0250. (See chart, next page) 13. Show the total coefficient of drag is 0.0455. (proof + profile + induced). 0.8 0.6 0.4 0.2 -0.2 Cruise Drag Polar, M=.84, Alt-35 kft D.O.C. 0.02 0.03 D04 Со 0.05 0.06 0:07 0.08 Nominal Cruise Point, 636kips A Boeing 747 has a wing span of 195.7 feet and a 6.95 aspect ratio. It cruises at 500 mph at a weight of 550,000 pounds at 35,000 feet (density of 0.000737 slug/ft³). Assume that the Reynolds number can be approximated using: R₁ =9324 x V x c where V is the average speed in mph, e the average chord in feet. Assuming that the wing sweep and twist combine to give an essentially elliptical spanwise circulation distribution find: 1. From the given data, show that the span area is 5511 ft². 2. From the given data, show that the average elliptic chord is 35.85 ft. 3. From the given data, show that the Reynolds number is 1.67 × 10%. 4. Show that the cruise speed is 733 ft/s. 5. Show that the coefficient of lift is 0.50. 6. Show that I = 6.6 x 10³ ft²/s. 7. Show that downwash velocity is w = -16.9 ft/s. 8. Show that the coefficient of induced drag is 116 counts. 9. Show that the induced Drag has a value of 12.7 x 10³ lb. 10. Show that the induced angle of attack is approximately 1.32⁰. 11. Show that the coefficient of profile drag is c = 0.0088. Assume you can use the value for a flat plate with a correction factor of 1.75. 12. Show that the coefficient of proof drag at cruise is c = 0.0250. (See chart, next page) 13. Show the total coefficient of drag is 0.0455. (proof + profile + induced). 0.8 0.6 0.4 0.2 -0.2 Cruise Drag Polar, M=.84, Alt-35 kft D.O.C. 0.02 0.03 D04 Со 0.05 0.06 0:07 0.08 Nominal Cruise Point, 636kips

Answer rating: 100% (QA)

Given data Speeds500mph Wing spanWs1957ft WeightW550000 pounds Heighth35000ft Re 9324 V c DensityD00... View the full answer