Consider a positively cambered airfoil with a zero-lift angle of −3◦. The lift slope is 0.1 per degree. Now imagine the same airfoil turned upside-down, but at the same 5° angle of attack as part (a). Calculate the lift coefficient. (Round the final answer to one decimal place. You must provide an answer before moving on to the next part.) The lift coefficient is ............ At what angle of attack must the upside-down airfoil be set to generate the same lift as that when it is right-side-up at a 5° angle of attack? (Round the final answer to the nearest whole number.) The angle is ...........

Consider a positively cambered airfoil with a zero-lift angle of −3◦. The lift slope is 0.1 per degree. Now imagine the same airfoil turned upside-down, but at the same 5° angle of attack as part (a). Calculate the lift coefficient. (Round the final answer to one decimal place. You must provide an answer before moving on to the next part.) The lift coefficient is ............ At what angle of attack must the upside-down airfoil be set to generate the same lift as that when it is right-side-up at a 5° angle of attack? (Round the final answer to the nearest whole number.) The angle is ...........

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.55P

See similar textbooks

Similar questions

A given symmetrical airfoil has a lift curve slope of 6 per radian. What is the angle of attack (in degrees) corresponding to a lift coefficient of 0.4? Round off answer to the nearest tenths. (for symmetrical airfoils zero-lift angle of attack is 0°)
A given airfoil develops a lift of 120 lb/ft at a given velocity of 120 mph under standard sea level conditions. Calculate the lift coefficient when the chord length is 9 ft. Round off answer to the nearest hundredths.
Consider a finite wing with an aspect ratio of 3. Assume an elliptical liftdistribution. The lift slope for the airfoil section is 0.1/degree. Calculateand compare the lift slopes for (a) a straight wing, and (b) a swept wing,with a half-chord line sweep of 45 degrees.
The Antonov An-225 is the heaviest aircraft ever built, with a maximum takeoff weight of 640 metric tonnes. It also has the largest wingspan of any aircraft in operational service. Sea level standard day (sls) conditions for calculations are 15°C; 101.3kPa Rotate speed (Vr) at takeoff (sls): Vr = 154 kts = 1.2×Vmin (1 kt = 0.514 m/s) Cruise Engine Thrust : a) Calculate the lift coefficient for a standard day takeoff b) Calculate the drag coefficient at cruis Fcruise = 0.85 Fmax Engine maximum thrust: Factual,max = Fsls,max×δ θ½ δ = Pactual/Pref; and θ = Tref/Tactual
An airfoil has a lift curve slope at 7/rad and angle at zero lift of -3deg. At what angle of attack will the airfoil develop a lift of 120 lbs/ft at 110 mph under SSLC? Assume c = 10ft.
Consider an airfoil at 12◦ angle of attack. The normal and axial forcecoefficients are 1.2 and 0.03, respectively. Calculate the lift and dragcoefficients.
For the airfoil given, calculate cm,c/4 and xcp/c when α = 3◦.
answer 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?
Explain the effect of aerodynamic drag and lift on aerofoils.
A B-2A is flying at 42,500 ft in standard day conditions at 420 KTAS. The mean chord length is 39.6ft.A) Find the overall or total Reynolds number for the aircraft.
Describe the downwash angle of a finite span wing and induced drag coefficient!
A small, fast boat has a specific resistance ratio of 0.06 (see Table 17.2) and displaces 125 long tons. Compute the total ship resistance and the power required to overcome drag when it is moving at 50 ft/s in seawater at 77°F.