An airplane, weighing 10 kN (including cargo and passengers) has an area (chord x span) of 20 m². What is the stall speed, in kph? The wing characteristics follows the shape of NACA 2412 with lift properties shown in the graph. Assume that the density air is 1.2 kg/m³. 2.00 NACA 2412 section CL 1.50 1.00 0.50 NACA 0012 section -0.50 5 10 15 Angle of attack, a, degrees -5 0 20

An airplane, weighing 10 kN (including cargo and passengers) has an area (chord x span) of 20 m². What is the stall speed, in kph? The wing characteristics follows the shape of NACA 2412 with lift properties shown in the graph. Assume that the density air is 1.2 kg/m³. 2.00 NACA 2412 section CL 1.50 1.00 0.50 NACA 0012 section -0.50 5 10 15 Angle of attack, a, degrees -5 0 20

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

See similar textbooks

Similar questions

Pls help ASAP. Pls show all work annd circle the final answer.
Long flights at midlatitudes in the Northern Hemisphere encounter the jet stream, an eastward airflow that can affect a plane's speed relative to Earth's surface. If a pilot maintains a certain speed relative to the air (the plane's airspeed), the speed relative to the surface (the plane's ground speed) is more when the flight is in the direction of the jet stream and less when the flight is opposite the jet stream. Suppose a round-trip flight is scheduled between two cities separated by 3200 km, with the outgoing flight in the direction of the jet stream and the return flight opposite it. The airline computer advises an airspeed of 810 km/h, for which the difference in flight times for the outgoing and return flights is 72 min. What jet-stream speed is the computer using?
The lift curve for the 4 digit NACA 2421 airfoil is shown in the Figure. Consider a wing with AR = 8, sweep ? = 15 ???, and airplane flies at the Mach number equal to 0.3. The Oswald efficiency span number ?1 = 0.95 Calculate the lift slope for the finite wing. Clearly show the formula and explanations in the solution.
Using the information given in Table 10.4, determine the ratio of local pressure and density to sea-level values. Estimate the value of air density at the cruising altitude of most commercial airliners.
Answer this ole
Discuss and comment on the effect of drag polar for Re 5003352.
Do fast or Skip and allow others to work.
A stationary object in a flow of speed 27 m/s produces a drag force of 13 N. The flow speed is then changed to 25 m/s. What will be the drag force if the Drag Coefficient and density are assumed constant? Give your answer in Newtons to 2 decimal places.
A conventional low speed aircraft had the following aerodynamic characteristics: CDo=0.020. e=1.0 (Oswald efficiency). The aircraft was flown to maintain a steady level flight and for minimum thrust required, at a lift coefficient of Cz=0.8. The numerical value of the aspect ratio of the wing is three decimal places). (in
Calculate the Road load power for the case Toyota Prius (fronatal area =0.8m2 sliding over a street has coefficient of rolling resistance CR= 0.015, drag coefficient CD=0.26 air density=1.2 kg/m3 the mass of the car 1500 kg. O a. 3.48 kW O b. 2.15 kW O . 9.72 kW
If the pressure difference in the wind tunnel experiment is 50 mmH,O, the density of air is 1.2 3 kg/m in wind tunnel experiment, and the airfoil span is 204 mm, and the cord length is 98 mm, what is the lift coefficient if the lift force is L=28.9 N Select one: a. 2.94715 b. 11.61715 c. 5.83715 d. 14.50715 e. 8.72715