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1. Consider an airplane similar to the Beechcraft Bonanza V-tail, single engine, light-weight private airplane. The characteristics of the airplane (shown above on the left) are: Aspect ratio = 6.2 Wing area = 181 ft² Oswald efficiency factor = 0.91 Maximum gross weight = 3,400 lb Zero-lift drag coefficient = 0.027 The specific fuel consumption is 0.42 lb of fuel per HP per hour. Fuel capacity is 44 gallons. The airplane is powered by a single piston engine of 345 HP maximum at sea level. Assume that the power of the engine is proportional to the freestream density. The two-blade propeller has an efficiency of 0.83. Calculate the following: • Power required at sea level. . Maximum velocity at sea level. ● N1/330 ● Power required at 12,000 ft. of altitude. Maximum velocity at 12,2000 ft. of altitude. Range at sea level. Endurance at sea level. Estimate how much "extra" range and endurance can be achieved by adding the wig-tip fuel tanks shown above on the right.

1. Consider an airplane similar to the Beechcraft Bonanza V-tail, single engine, light-weight private airplane. The characteristics of the airplane (shown above on the left) are: Aspect ratio = 6.2 Wing area = 181 ft² Oswald efficiency factor = 0.91 Maximum gross weight = 3,400 lb Zero-lift drag coefficient = 0.027 The specific fuel consumption is 0.42 lb of fuel per HP per hour. Fuel capacity is 44 gallons. The airplane is powered by a single piston engine of 345 HP maximum at sea level. Assume that the power of the engine is proportional to the freestream density. The two-blade propeller has an efficiency of 0.83. Calculate the following: • Power required at sea level. . Maximum velocity at sea level. ● N1/330 ● Power required at 12,000 ft. of altitude. Maximum velocity at 12,2000 ft. of altitude. Range at sea level. Endurance at sea level. Estimate how much "extra" range and endurance can be achieved by adding the wig-tip fuel tanks shown above on the right.

Elements Of Electromagnetics
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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1. Consider an airplane similar to the Beechcraft Bonanza V-tail, single engine, light-weight private airplane. The characteristics of the airplane (shown above on the left) are: Aspect ratio = 6.2 Wing area = 181 ft² Oswald efficiency factor = 0.91 Maximum gross weight = 3,400 lb Zero-lift drag coefficient = 0.027 N1/330 ● 100 OPA The specific fuel consumption is 0.42 lb of fuel per HP per hour. Fuel capacity is 44 gallons. The airplane is powered by a single piston engine of 345 HP maximum at sea level. Assume that the power of the engine is proportional to the freestream density. The two-blade propeller has an efficiency of 0.83. Calculate the following: Power required at sea level. Maximum velocity at sea level. Power required at 12,000 ft. of altitude. Maximum velocity at 12,2000 ft. of altitude. Range at sea level. Endurance at sea level. Estimate how much "extra" range and endurance can be achieved by adding the wig-tip fuel tanks shown above on the right.
Transcribed Image Text:1. Consider an airplane similar to the Beechcraft Bonanza V-tail, single engine, light-weight private airplane. The characteristics of the airplane (shown above on the left) are: Aspect ratio = 6.2 Wing area = 181 ft² Oswald efficiency factor = 0.91 Maximum gross weight = 3,400 lb Zero-lift drag coefficient = 0.027 N1/330 ● 100 OPA The specific fuel consumption is 0.42 lb of fuel per HP per hour. Fuel capacity is 44 gallons. The airplane is powered by a single piston engine of 345 HP maximum at sea level. Assume that the power of the engine is proportional to the freestream density. The two-blade propeller has an efficiency of 0.83. Calculate the following: Power required at sea level. Maximum velocity at sea level. Power required at 12,000 ft. of altitude. Maximum velocity at 12,2000 ft. of altitude. Range at sea level. Endurance at sea level. Estimate how much "extra" range and endurance can be achieved by adding the wig-tip fuel tanks shown above on the right.
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