Consider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the freestream pressure and temperature are 432.6 lb/ft2 and 390◦R, respectively. A one-fiftieth scale model of the 747 is tested in a wind tunnel where the temperature is 430◦R. In addition to the information given in above, for this airplane the zero-lift angle of attack is −2◦, the lift slope of the airfoil section is 0.1 per degree, the lift efficiency factor τ = 0.04, and the wing aspect ratio is 7.96. At the cruising condition treated given, calculate the angle of attack of the airplane.
Consider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the freestream pressure and temperature are 432.6 lb/ft2 and 390◦R, respectively. A one-fiftieth scale model of the 747 is tested in a wind tunnel where the temperature is 430◦R. In addition to the information given in above, for this airplane the zero-lift angle of attack is −2◦, the lift slope of the airfoil section is 0.1 per degree, the lift efficiency factor τ = 0.04, and the wing aspect ratio is 7.96. At the cruising condition treated given, calculate the angle of attack of the airplane.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Consider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the freestream pressure and temperature are 432.6 lb/ft2 and 390◦R, respectively. A one-fiftieth scale model of the 747 is tested in a wind tunnel where the temperature is 430◦R.
In addition to the information given in above, for this airplane the zero-lift angle of attack is −2◦, the lift slope of the airfoil section is 0.1 per degree, the lift efficiency factor τ = 0.04, and the wing aspect ratio is 7.96. At the cruising condition treated given, calculate the angle of attack of the airplane.
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