Consider an NACA 2412 airfoil (the meaning of the number designations for standard NACA airfoil shapes is discussed in Chapter 4). The following is a tabulation of the lift, drag, and moment coefficients about the quarter chord for this airfoil, as a function of angle of attack.
From this table, plot on graph paper the variation of
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- The figure shows two cables AB and AC. Using the tabulated values for the parameters, calculate the magnitude of the projection of FAC onto AB. Also, determine the angle 0 formed by BAC. NOTE: the magnitude of the projection may be positive or negative (or zero). Also, point C lies on the y axis. В L6 FAB A L2 FAC y L3 X 2021 Cathy Zupke parameter value units 3 m L2 L3 L4 3 m 3 m 1 m 3 L6 FAB 2 80 N FAC 100 The magnitude of the projection of FAC on AB is N The angle AB makes with AC is 0-arrow_forward10. What is the name of the mentioned airfoil parameter? y airfoil curve O airfoil thickness O chord linearrow_forwardThe drag polar equation of a light airplane in clean configuration can be written as Cp = 0.358 + 0.0405 C₁². It has a weight of 18,681 N. The wing area is 14.41 m². Calculate the minimum power required in watts. (Round off answer with no decimal places, No units, No commas) Answer given: 1461792 A 5,000 lbs. aircraft has an excess power of 75 hp at sea level. If the service ceiling is 3,657.6 m, determine the time to climb from sea level to absolute ceiling in minutes. (Round off answer with no decimal places. No units, No commas) Answer given: 17arrow_forward
- a)What is the impact of increasing Reynolds number on skin friction and pressure drags over an airfoil? What can be happened for separation in this case? b) What is an adverse pressure gradient and where does it occur on an airfoil (show that on a sketch)? c) Why lift-to-drag ratio is an important parameter for an aircraft? d)How can changing in altitude affect the aircraft power required, PR? Show thatmathematically and graphically?arrow_forwardanswer with FOUR decimal places on final answer, and in scientific notation for less than 1 values. Include the units on the answer. Question NACA 664-221 Chord c = 150 cm 1) What is the CL range to achieve the minimum coefficient of drag? 2) What is the thickness ratio of the airfoil?arrow_forward2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Y Fx = Yu 0 0.0952 0.0922 0.0588 0 (Pu dYu dx - Calculate the drag and lift force on the airfoil by numerically evaluating the integrals Fy (P₁-P₂)dx = √ ( P₁ - 1 Pi Y₁ 0 -0.0254 -0.0144 -0.0052 0 dv) Y = Yu (x) dx y = Ye (x) Pu 1.000 -1.640 -0.786 -0.212 0 x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.arrow_forward
- 4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil Eg. (4,57) C 2.0 - 1.e 1.2 Lift coefficient 0.8 0.4 -0.4 Eg. (4,64) -0.1 Moment coefficient -0.8 -0.2 -1.2 -0.3 Re - 3.1 X 10 O Re- 8.9 x 10 -0.4 16 a, degrees de; = ? daarrow_forwardEstimate the drag force on the fuselage shown below for a cruising speed of 210 m/s at 10,000m. Hint 1: To calculate the drag force split the fuselage into 4 parts: front hemisphere,cylindrical body, vertical stabilizer, back hemisphere. Model the front and back hemispheres as flow over a sphere. For simplicity treat the cylindrical body and vertical stabilizer as flat plates.Hint 2: Use Cd vs Reynolds number graphs for sphere and flat plate. If your Reynolds number is greater/smaller than the Cd vs Reynolds graph range, you can instead use the greatest/smallest number available on the graph.arrow_forwardEstimate the landing ground roll distance at sea level for the CJ-1. No thrust reversal is used; however, spoilers are employed such that L drag coefficient by 10 percent. The fuel tanks are essentially empty, so neglect the weight of any fuel caried by the airplane. The maximum lift coefficient, with flaps fully em- ployed at touchdown, is 2.5. 0. The spoilers increase the zero-lift,arrow_forward
- Type here to search X The large, newly planted tree shown in the figure below is kept from tipping over in a wind by use of a rope as shown. It is assumed that the sandy soil cannot support any moment about the center of the soil ball, point A. Estimate the tension T in the rope if the wind is 75 km/hr. See the figure for drag coefficient data. 4x F2 4, # O DI » $ F4 U=75 km/hr DII % F5 Rope * 45 F6 A Scale drawing ☀ F7 & 2.1m PrtScn F8 Home F9 End 28°F Cloudy F10 POUP FI PgDnarrow_forwardQustion. An aircraft is flying in level flight at a speed of 200 km/h through air (density, p = 1.2 kg/m³, and viscosity, μ = 1.6 x 10-5 N-s/m²). The lift coefficient at this speed is 0.4 and the drag coefficient is 0.0065. The mass of the aircraft is 800 kg. The effective lift area of the aircraft NOTE= Do not give wrong answer I will dislike , If not sure skip itarrow_forward(a) A luxury sports car has a frontal area of 23.1 ft and a 0.24 coefficient of drag at 80 mph. How much power must the engine produce just to overcome the air drag? (Express your answer using three significant figures.) P = hp (b) A sport-utility vehicle has Cp = 0.45 at 80 mph and a slightly larger frontal area of 28.3 ft. How much power must the engine produce just to overcome the air drag? (Express your answer using three significant figures.) P =[ hparrow_forward
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