Calculate the stall speed for the following:

An aircraft has the C_L curve shown below and thefollowing data applies:

Weight = 20,000 lb

Wing Area S = 340 ft²

Density Altitude = 10,000 ft with a ?(density ratio) = 0.7385

Transcribed Image Text:

easure of the effectiveness of the airfoil to produce lift. Values of C, have been be said to be "the ratio between the lift pressure and the dynamic pressure." tally for all airfoil sections and can be found in publications (see Reference L the curve passes through the 0-0 point, showing that no lift is developed at 0 1 shows a typical curve of C₁ plotted against AOA for a symmetrical airfoi e is essentially a straight line until it approaches its stall AOA. 1 AOA the airfoil gets its maximum lifting ability (CL(MAX)). Stall is discus q 1.4 1.2 1.0 0.8 0.6 0.4 0.2- CL(max) Straight Portion - 'S-T-A-L-L 0 2 4 6 8 10 12 14 16 18 ANGLE OF ATTACK STALL AOA Figure 4.1 C₁-a for a symmetrical airfoil. to understand that an airfoil always stalls at the 4141 some AQA easure of the effectiveness of the airfoil to produce lift. Values of C, have been be said to be "the ratio between the lift pressure and the dynamic pressure." tally for all airfoil sections and can be found in publications (see Reference L the curve passes through the 0-0 point, showing that no lift is developed at 0 1 shows a typical curve of C₁ plotted against AOA for a symmetrical airfoi e is essentially a straight line until it approaches its stall AOA. 1 AOA the airfoil gets its maximum lifting ability (CL(MAX)). Stall is discus q 1.4 1.2 1.0 0.8 0.6 0.4 0.2- CL(max) Straight Portion - 'S-T-A-L-L 0 2 4 6 8 10 12 14 16 18 ANGLE OF ATTACK STALL AOA Figure 4.1 C₁-a for a symmetrical airfoil. to understand that an airfoil always stalls at the 4141 some AQA

Answer rating: 100% (QA)

Hence solved it Given M20000 lb Wing Area S 340 ft Altitude 10000ft I s... View the full answer