To provide an outlook on some of the aspects of the next module's unaccelerated performance, select a jet aircraft of your choice, choosethree(3)of the following items of performance, and instructional presentation (utilizing a presentation tool of your choice - see resources in the Online Tools section) that explains in-depth how to find these different items of performance for a jet aircraft. This will be a standalone presentation and will not be attached to your comprehensive presentation project. Available choices:

• maximum forward speed in level flight
• absolute ceiling
• best angle of climb airspeed
• angle of climb
• best rate of climb airspeed
• rate of climb
• maximum endurance airspeed
• maximum range airspeed
• influence of weight on performance
• influence of altitude on performance
• influence of configuration on performance

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Change or add more details as required to fix what is wrong

Slide 4- did not read and follow instructions. You are not to post the Max Speed from the POH or any other source- Read the Mod 4 Core lectures that define Max forward speed. Slide 5- Same as above only for Best rate of climb airspeed and how to derive it. Slide 6- same as above only for Max range airspeed. Did not read and follow instructions.

Since all of your example aircraft are propeller-driven, it makes sense to divert your attention for a moment to introduce some of the application of performance principles in jetaircraft. maximum forward speed in level flight, absolute ceiling, best angle of climb airspeed, angle of climb, best rate of climb airspeed, rate of climb, maximum endurance airspeed, maximum range airspeed, influence of weight on performance, influence of altitude on performance, influence of configuration on performance

Choose a jet aircraft to use as your example for this activity. It should not be an exotic jet aircraft, as you will need to find data online for the aircraft. If you choose a military aircraft, make sure you are not using classified data to support your work. Only use data that is available to all on the internet. You will then use the data you gathered for this particular aircraft to show examples of your performance problems and how you derived them.

To provide an outlook to some of the aspects of next module's unaccelerated performance and apply them to jet aircraft, select a jet aircraft of your choice, choosethree(3)of the following items of performance, and an instructional presentation that explainsin-depthhow to find these different items of performance for a jet aircraft. This will be a standalone presentation and will not be attached to your comprehensive presentation project. Available choices:

maximum forward speed in level flight (Not what is in the POH-Look up the definition)

-absolute ceiling (this is NOT the Service Ceiling as stated in the POH-Look up the definition)

-best angle of climb airspeed

-angle of climb

-best rate of climb airspeed

-rate of climb

-maximum endurance airspeed

-maximum range airspeed

-influence of weight on performance

-influence of altitude on performance

-influence of configuration on performance

In the textbook we have an example of a T-38 Thrust required vs Thrust Available chart (Do not use this aircraft for your choice).

Total Drag is the same as Total Thrust Required-So just add another column on your table for 'Thrust Required' (equals Total Drag).

Then the last column you can have "Excess Thrust"

The F15E has a max speed of Mach 2.5 1,650 mph or 2,655 kmfh at high altitude roughly 50000 ft at the speed of Mach 2.3 Mach 1.2., 800 km, 921 mph or 1.482 kin/h sea level Fuel flow rate is roughly 60,000 lb/hr at Mach 2.3 around 50,000 ft With 0.17 miles per gallon the F-15 can travel 590 miles in 23 minutes. Standard F- 1 5E cruise speed is Mach 0.90 with a max speed of Mach 2.5 The max optimal speed is Mach 1.6, due to the added weight and drag it consumes roughly 70% of its fuel if its to y in Mach 2.5 by Unknown Author is licensed under 207.30 SECONDS 30,000 METER (90.425 m 321325; TIME TO CLIMB PROFILE 'Takeoff Gross Weight 31,908 Lb Thrust-to-Weight Ratio 1.4+ Best rate of climb airspeed 3,000 meters (9,843 Feet] 27.57 seconds 151 SECONDS 37,000 FT ' 6,000 meters (19,685 feet) 39.33 seconds ' 9,000 meters (29,685 feet) 43.85 seconds 2.2 MACH 56 SECONDS - 12,000 meters {39,370feet) 59.33 seconds 32,000 FT 1.1 MACH ' 15,000 meters [49,212 feet} 77.02 seconds \\_4G PULL ' 20,000 meters [65,617 feet} 122.94 seconds 60 To ' 25,000 meters [82,021 feet} 161.02 seconds ' 30,000 meters [98,425 feet} 207.80 seconds 21!? G 'IMMELMANN a?\" ACCELERATE TO 0.65 MACH m m Maximum range airspeed + Influence of weight on performance internal weight variances are 13,123 lbs to 13,455 lbs Conformal Fuel Tanks weight is roughly 21,645 lbs Up to 3 External Fuel Tanks can be installed ' 1830 gallons at 6.79 lbs per gallon with a grand total of 12425.7 lbs Total weight of 47193.7 to 475 25.7 lbs of fuel load. ' Aircraft Weight Empty weight 28,000 lbs or 12,701 kg ' Gross Weight 44,500 lbs or 20,185 kg - Max takeoff weight 68,000 or 30,377 kg ' At optimal cruise speedsfaltitude ' The F15-E as a rated range between 24,000 miles with a consumption of .45 miles per gallon to 3,500 miles or 5600 km when flown with Conformal Fuel Tanks and 3 external fuel tanks