Aviation Legislation

Basic Aerodynamics

Intro to Aernautical Science

Possible_Final_questions.docx.docx-Define the four components, or pillars,

Page 1 of 3 Exercise 4: Drag and Applications Part 1: Drag Givens (Questions 1 – 6): Weight (W) 15,000 lb C DP 0.021 Wing Area (S) 230 ft 2 C Lmax at Stall 1.5 Aspect Ratio (AR) 5.3 Note : Assume the drag polar is a parabola Span Efficiency (e) 0.85 Temperature Standard Altitude Sea Level Complete the following table for this particular typical transport jet. Start the table at stall speed, V S . Then answer the questions at the end using the values from the table. You can use an excel spreadsheet to create the answers for the table. V (KTAS) q (psf) C L C D C L / C D D P (lb) D I (lb) D T (lb) V S= 113.3 43.51 1.5 .159 9.43 210.15 1591.16 1801.31 120 48.81 1.34 .147 9.088 235.75 1414.51 1650.26 140 66.44 .982 .089 10.7 320.91 1039.12 1360.03 160 86.78 .752 .061 12.33 419.15 798.38 1217.53 180 109.83 .594 .046 12.91 530.48 631.52 1162 190 122.37 .533 .041 13 591.1 562.90 1154 200 135.59 .481 .037 13 654.9 498.97 1153.87 220 164.01 .398 .031 12.84 792.12 377.22 1169.34 240 195.25 .334 .0289 11.56 943.06 354.77 1297.83 260 229.15 .285 .0267 10.67 1106.8 300.42 1407.22 This document was developed for online learning in ASCI 309. File name: Ex_4_Drag Updated: 8/13/2014 Page 2 of 3 Equations for Table: q = σV k 2 295 C L = W qS C Di =[1/ (πeAR)] C L 2 C D = C DP + C Di C D = C DP + [1/ ( π e AR)] C L 2 Dp = C Dp q S Di = C Di q S = [1/ ( π e AR)] C L 2 q S Dt = Di + Dp = C D q S 1. Determine V STALL (Stall speed in KTAS) 113.3 KTAS 2. Determine D MIN (Minimum total drag in pounds) 1153.8 lbs. 3. Determine V DMIN (Speed in KTAS at minimum drag) 200 KTAS 4. Determine the parasitic drag at D MIN (pounds) 654.9 lbs. 5. Determine the induced drag at D MIN (pounds) 498.97 lbs. 6. Find Glide Ratio at V DMIN 13 This document was developed for online learning in ASCI 309. File name: Ex_4_Drag Updated: 8/13/2014 Page 3 of 3 Part 2: Applications of Lift and Drag Givens (Questions 7-11): Weight (W) = 15,000 lb Wing Area (S) = 230 ft 2 Altitude = Sea Level Temperature Standard (The Given Figure below is not exactly the same aircraft as above, but close) Figure 1.13 from Aerodynamics for Naval Aviators (1965). 7. What is the Angle of Attack at Stall for the aircraft in Figure 1.13? AOA stall angle is 20 degrees. 8. What is the airspeed associated with initial onset of stall? (KEAS) 122 KEAS 9. If the gross weight is increased by 10%, how would the stall speed change? 122(1.05) = 128 KEAS 10. What Angle of Attack is associated with Best L/D? 6 degrees AOA 11. What would be the best Glide Ratio for this aircraft? (L/D) MAX = 12.5 This document was developed for online learning in ASCI 309. File name: Ex_4_Drag Updated: 8/13/2014

ASCI | 309 | Basic Aerodynamics | lab | Page 1 of 3 Exercise 4: Drag a

1 Exercise 1: Rectilinear Motion Uniformly Accelerated Rectilinear Motion and Newton’s Law of Momentum Equations to use (remember to keep track of units): F = ma m = W/g T-D-f = ma V F 2 = V I 2 + 2 a s V F = V I 2 + a t Takeoff distance (s) = V F 2 /2a KE = ½ mV 2 PE = Wh HP= T*V kts /325 sin(γ) = (ROC kts )/(V kts ) 1 kt = 1.69 ft/sec g = 32.2 ft/sec 2 Givens : (Questions 1 to 8) Gross Weight = 100,000 pounds Average Drag = 5,000 pounds Average Friction Force = 1,000 pounds Average Thrust = 34,000 pounds Lift Off Speed = 150 Knots True Airspeed 1. Compute the acceleration on the aircraft during the takeoff roll (ft / sec 2 ). m = W/g m = 100,000/32.2 m = 3105.6 lb-sec 2 /ft or Slugs T – D – f = 3105.6 (a) 34,000 – 5000 – 1000 = ma 28000/3105.6 = 9.01 ft / sec 2 2. What would be the length of the takeoff run (ft)? Knots to ft/sec = 150x1.69 = 253.5 ft/sec Takeoff distance (s) = VF 2 /2a S = 253.5 2 /2(9.01) S = 64262.3/18.02 S = 3566.1 ft 3. How long would it take until liftoff once the takeoff roll is started (sec)? V F = VI 2 + a t 253.5 = 0 2 + 9(t) T = 253.5/9 T = 28.11 sec 4. Given the information shown above, determine how fast this airplane should be going when it passes the 2000-foot runway marker (2000 feet from the start of the takeoff roll)? Please express your answer in knots . This document was developed for online learning in ASCI 309. File name: Ex_1_ Reclinear_Moon Updated: 05/30/2014 2 VF 2 = VI 2 + 2 a s VF 2 = 0 2 + 2(9.01)(2000) VF 2 = 36040 VF 2 = √36040 VF = 189.8 ft/ sec VF = 189.8/1.69 = 112.3 Knots 5. What is the power (HP) of the aircraft engines after takeoff at Average Thrust at 250KTAS? After takeoff, so friction is now gone. HP= T*V kts /325 HP = 34,000 x 250 / 325 HP = 26,154 HP 6. What is the Kinetic Energy (ft-lb) of the aircraft after climbing out at 250 KTAS with the new weight at 95,000 lb? m = W/g m = 95000/32.2 m = 2950.3 Kg 250 Knots = 250 x 1.69 = 422.5 ft/Sec KE = ½ mV 2 KE = ½(2950.3)(422.5 2 ) KE = 263 323 494.7 ft-lb 7. What is the Potential Energy (ft-lb) of the aircraft after climbing out to 10,000 ft above sea level with the new weight at 95,000 lb? PE = Wh PE = 95000 x 10000 PE = 950 000 000 ft-lb 8. What is the Angle of Climb (deg) for airplane at 250 KTAS with a climb rate of 4,000 ft/min? Sin γ = O/H Sin γ = 39.4/250 γ = Sin-1(39.4/250) γ = 9.06° This document was developed for online learning in ASCI 309. File name: Ex_1_ Reclinear_Moon Updated: 05/30/2014 250 KTAS 4000 fpm γ = ? Change to Knots!! 4000 fpm = 66.6 fps = 39.4 Knots O H

ASCI | 309 | Basic Aerodynamics | assessment | 1 Exercise 1: Rectilinear Moti

a. the Aeronauc Society of New York 13. The AEA a. disbanded in 1909. 14. Fighter aircraﬅ such as the SE5 and Sopwith Camel were developed by the a. Brish. 15. The Curss Aeroplane and Motor Company a. Produced 10,000 planes by 1918. 16. During the post-World War I period, a. All of the above 17. All of the following severely hampered the early airmail service, except: a. Lack of pilots. 18. Which of the following statements is not true? a. Pra & Whitney developed the "whirlwind" engine in 1929. 19. The original transconnental airmail route was between a. New York and San Francisco. 20. During the early years of airmail service, a. All of the above 21. What was the disagreement that Curss had with the Wright brothers? a. The Wrights were under the impression that Curss and the AEA had infringed on their wing controlling patent, through the use of "ailerons". Curss dismissed the claim and went on to win a healthy amount of prize money, a few records and a lot of publicity. Aﬅer the results of the San Diego Internaonal Air Meet, the Wrights ﬁled a patent infringement lawsuit against Curss. 22. What was the purpose of the Naonal Advisory Commiee on Aeronaucs (NACA)? a. Be on the cung edge of aeronaucal research. Their job is to direct and conduct research and experimentaon in aeronaucs with a view to their praccal soluon.

ASCI | 254 | Aviation Legislation | homework | a. the Aeronauc Society of Ne

Module 1 Learning Objectives Upon successful completion of this module, you will be able to: 1. Explain the qualifications, attributes, ethics, and responsibilities of aviation professionals. 2. Analyze the financial and educational requirements of aviation careers. 3. Describe the qualifications, privileges, and limitations of all classes of certification to include pilot, maintenance, avionics, dispatch, and air traffic control. Answers: Refer to PDF links Module 2 Learning Objectives Upon successful completion of this module, you should be able to: 1. Explain how the atmosphere affects the density of air and aircraft flight characteristics. 2. Demonstrate Newton’s Laws of Motion and Force and Bernoulli’s Principle of Pressure. 3. Discuss the aerodynamic forces that influence aircraft stability and flight maneuvers. 4. Discuss how load factors transform the structure of an aircraft and the effects of weight on flight performance. 5. Define aircraft performance in terms of information available in the Airplane Flight Manual/Pilot’s Operating Handbook (AFM/POH). 6. Interpret performance speeds and performance specifications for various aircraft. Answers 1.  Reduced atmospheric pressure alters the production of lift. Reduced density means lesser  molecules of air flowing around the airplane’s wings to generate lift. The aircraft’s lifting capability is decreased.  Reduced atmospheric pressure alters the fuel/air ratio. Reduced density, in this case, is responsible for less  number of molecules of air entering the cylinder. This upsets the optimum ratio required between aircraft fuel and air molecules, to maintain efficient flight. 2.  Newton’s Second Law: force causes a change in velocity which in turn generates another force.  Newton’s Third Law: net flow of air is turned down resulting in an ‘equal and opposite’ upward force.  Newton’s Third Law states that for every action there is an equal and opposite reaction.  Bernoulli’s Principle states that, as air speeds up, its pressure goes down.  Bernoulli’s Theory in Action: Air speeds up in the constricted space between the car & truck creating a low-pressure area. Higher pressure on the other outside pushes them together.  Bernoulli's Principle: slower moving air below the wing creates greater pressure and pushes up.  Bernoulli’s Principle: Air moving over the wing moves faster than the air below. Faster-moving air above exerts less pressure on the wing than the slower-moving air below. The result is an upward push on the wing--lift!  A wing creates lift due to a combination of Bernoulli’s Principal & Newton’s Third Law 3.  Forces that act on the airplane in flight and also work against each other: Thrust, weight, lift, drag  Roll, yaw, pitch, 4.  Ratio between the lift generated by the wings at any given time divided by the total weight of the airplane.  A heavily loaded plane stalls at a higher speed than a lightly loaded airplane.  •It needs a higher angle of attack to generate required lift at any given speed than when lightly loaded. 5. The various items of aircraft performance result from the combination of aircraft and powerplant characteristics. The aerodynamic characteristics of the aircraft generally define the power and thrust requirements at various conditions of flight, while powerplant characteristics generally define the power and thrust available at various conditions of flight. The matching of the aerodynamic configuration with the powerplant is accomplished by the manufacturer to provide maximum performance at the specific design condition (e.g., range, endurance, and climb). Module 3 Learning Objectives Upon successful completion of this module, you will be able to: 1. Define the operating principles of reciprocating and turbine engines.

All courses in ASCI

Popular Documents