Daniel Munoz M5 Unaccelerated Flight

docx

School

Embry-Riddle Aeronautical University *

*We aren’t endorsed by this school

Course

ASCI 309

Subject

Mechanical Engineering

Date

Feb 20, 2024

Type

docx

Pages

Uploaded by ProfessorBravery7268

1 Module 5.1 Unaccelerated Flight and Flight Operations Embry-Riddle Aeronautical University ASCI 309: Aerodynamics Unaccelerated Flight and Flight Operations One important factor of aviation is aircraft performance in flight, which is essential for sustaining operations that are both safe and effective. This also allows pilots to make

2 smart choices during various points of flight, pilots, which are crucial for aircraft performance. For this assignment I will focus on two topics, Maximum Range Airspeed and Best Angle of Climb. I will explore how the practical application of thrust-to-power relationships and weight influences performance airspeeds. Maximum Range Airspeed The ideal speed at which a plane may travel the most distance horizontally while using the least amount of fuel is represented by Maximum Range Airspeed. According to the FAA, planning long-distance flights requires having an adequate grasp of the Maximum Range Airspeed. This data is used by pilots and operators to design routes that optimize endurance and reduce refueling stops. Operators may increase fuel economy and save operating expenses by carefully organizing their fuel stops and controlling cruise airspeed (FAA, n.d.). Effective flight planning requires an understanding of Maximum Range Airspeed. Best Angle of Climb For a safe takeoff, particularly when there are impediments to overcome soon after departure, knowing the Best Angle of Climb and its accompanying airspeed is crucial. The angle at which a plane may climb most sharply for every unit of horizontal distance traveled is referred to as the angle of climb. This becomes especially important while flying over mountains or taking off from small runways (FAA, 2018). Thrust-to-Power Relationship The Relationship between airspeed that aircraft’s thrust and power produced is a key idea in understanding aircraft performance This connection illustrates how the power required to maintain a certain airspeed connects with the thrust produced by an aircraft's engines. For engine efficiency and fuel consumption to be optimized, understanding this association is crucial. Engines with greater TPRs are able to generate more thrust with less

3 power, which improves overall performance and fuel economy. This connection is used by engineers and pilots to choose the most effective engine settings during various flying stages (FAA, n.d.). Taking the Formula into consideration, Thrust-to-Power Ratio (TPR) = Thrust / Power and consider an airplane with a thrust of 20,000 pounds and a power requirement of 10,000 horsepower to maintain a certain airspeed. The TPR in this case would be 2:0. This implies that twice as much thrust is produced by the engines than is needed to maintain the requisite power level. Weight Change Influence on Performance Airspeeds When it comes to Higher air speeds they are often required when an aircraft's weight increases in order to maintain performance levels. Knowing how performance airspeeds vary as a result of weight is essential for maintaining safe and effective flight operations (Badick, 2017). For example, considering that the plane is 10,000 lbs. in weight and travels at 150 knots as its reference airspeed. The performance airspeed of the aircraft may be determined using the formula below if the aircraft weight is 10,000 pounds: Performance Airspeed = 150 kts x (12,000 /9.8 lbs) x 1.2 x 150 kts x 1.095 x 164 kts. This demonstrates how weight gain impacts performance airspeed, which results in a greater air speed required for different flying maneuvers. Relationships between ROC and AOC The rate of ascension reduces as the angle at which an aircraft rises increases. Angle of Climb and Rate of Climb have an antagonistic connection. Formula: Ground Speed = ROC x tan. The aircraft's ground speed affects the link between the angle of climb and the rate of climb which will be demonstrated on the total drag table equation below. The ground speed drops, resulting in a slower rate of climb, when the AOC is steep, indicating a significant angle. Conversely, the ground speed rises, and the rate of ascent quickens when the AOC is shallow, suggesting a smaller angle (Badick, 2017).

Your preview ends here

Eager to read complete document? Join bartleby learn and gain access to the full version

Access to all documents
Unlimited textbook solutions
24/7 expert homework help

4 Assuming the powerplant produces a constant power output I will use the following parameters to determine total drag. 10,000 and best glide speed is 160 kts. I got the following numbers. V2 (v2/v1) Dp=dmin ( (V1/V2)2 Dt =dmin (v1/v2) Dt = Di + Dp (lb) 125 1.10 323.40 1.66 872.32 1195.72 150 0.72 425.69 1.01 598.07 1023.76 172 1.02 589.78 72.0 470.07 1059.85 200 1.50 801.90 0.59 350.07 1151.97 300 3.17 1706.25 .21 128.24 1834.49

5 References: FAA, n.d. Aviation Handbooks & Manuals. Aviation Handbooks & Manuals | Federal Aviation Administration. (n.d.). Chatper 5 and 11. https://www.faa.gov/regulations_policies/handbooks_manuals/aviation Badick, JR., Johnson, B.A. (2002) Flight Theory and Aerodynamics (fourth edition, p. 98) John Wiley and Sons. FAA. (2018). Best Glide Speed and Distance. Retrieved July 25, 2021, https://www.faa. gov/news/safety_briefing/2018/media/SE_Topic_18-05.pdf