Subsonic Aerodynamics Assessment Welcome, You are about to take up the Subsonic Aerodynamics Assessment. Please take note of the following before you take the assessment. This assessment is timed for 60 Mins and auto submit. Scores and correct answer will be displayed after taking up the assessment. You can only take the assessment twice so make sure you have a strong internet connection. All questions are required to have an answer. This assessment is composed of 10 items multiple choice type of question. Note to examinees: The passing score for this exam is 15 points. If the score you’ve acquired is less than 15, retake the assessment until you acquire the passing mark. Always remember: THINK, CHECK AND SUBMIT. If you have any concern, please feel free to contact us. E-mail Address: assessment@flightwingsaviation.com Facebook Page: www.facebook.com/flightwingsaviation GOODLUCK! Email Adress LMS USERNAME FULL NAME CLASS SECTION/SCHEDULE (FRI-AM, FRI-PM, SAT-AM, SAT-PM, SUN-AM, SUN-PM, ONLINE) 1. Where is most of the water vapor in the atmosphere can be found? a. Tropopauseb. Stratospherec. Troposphered. Stratopause A B C D None 2. The properties of Earth’s atmosphere which influence aircraft performance are a. humidity and Oxygenb. humidity, temperature and pressurec. humidity, temperature, pressure and densityd. Nitrogen, Oxygen, temperature and pressure A B C D None 3. It is the linear altitude corrected for gravitational effects. a. geometric altitudeb. absolute altitudec. pressure altituded. geopotential altitude A B C D None 4. An airplane indicates a pressure of 95 kPa at takeoff, where the airport elevation is 1 km, and the temperature is 10°C. If the standard lapse rate of -5.87°C/km is assumed, at what elevation is the plane when a pressure of 75 kPa is read? a. 1.5 kmb. 3 kmc. 19 kmd. 20 km A B C D None 5. a. 16 psf/sb. 0.3 psf/sc. 9 psf/sd. 0.02 psf/s A B C D None 6. At a certain altitude, a standard altimeter reads 10,000 ft. If the density altitude is 8,000 ft., find the true temperature at that altitude. a. 500 Rb. 490 Rc. 483 Rd. 454 R A B C D None 7. a. 1082 ft.b. 1135 ft.c. 17,574 ft.d. 9, 900 ft. A B C D None 8. The difference between IAS and TAS will a. decrease at high speedsb. increase with increasing air densityc. increase with temperature decreased. decrease with decreasing altitude A B C D None 9. Assuming ISA conditions and all other conditions are constant, if an airplane flies at the same angle of attack in straight and level flight at two different altitudes then the TAS will be a. lower at the higher altitudeb. higher at the higher altitudec. impossible to determined. the same at both altitudes A B C D None 10. An open circuit wind tunnel draws in sea-level standard air and accelerates it through a contraction into a 1 m by 1 m test section. A differential transducer mounted in the test section wall measures a pressure difference of 45 mm of water between the inside and outside. Find the velocity in the test section. a. 553 kphb. 186 kphc. 40 kphd. 97 kph A B C D None 11. a. 487 kPab. 137 kPac. 103 kPad. 507 kPa A B C D None 12. A certain aircraft flies at the same Mach number at all altitudes. If it flies at a speed that is 120 kph slower at an altitude of 12,000 m than it does at sea level, find the Mach number at which it flies. Assume standard atmospheric conditions. a. 0.7b. 3.6c. 5.5d. 0.4 A B C D None 13. An airplane is flying at a standard altitude of 16000 ft. with a velocity of 270 m/s. At a point on the wing of the airplane, the velocity is 330 m/s. Calculate the pressure at this point. a. 82 kPab. 48 kPac. 35 kPad. 79 kPa A B C D None 14. The critical angle of attack a. alters with an increase of gross massb. decreases as the CG moves aftc. remains the same for all massesd. increases as the CG moves forward A B C D None 15. Induced drag is decreased by a. Wing strutb. Wing filletc. Wing camberd. Wing fence A B C D None 16. A gas initially at a subsonic velocity enters an adiabatic diverging duct. What will happen to the velocity? a. remains the sameb. decreasec. increased. none of the choices given A B C D None 17. If the sum of the moments of an airplane in flight is not zero, then the airplane will rotate about the a. ACb. CGc. CPd. Neutral point A B C D None 18. In a test on an airfoil section the moment coefficient about the leading edge was found to be -0.005 at zero lift. At 6° angle of attack the moment coefficient about the leading edge was -0.240, and the lift and drag coefficients were 0.90 and 0.045 respectively. Find the position of the aerodynamic center of this airfoil section in percent of chord. a. 0.4cb. 0.5cc. 0.6cd. none of the choices given A B C D None 19. A car windshield is 42 inches wide by 12 inches high. What horsepower is used up by the windshield at 50 miles per hour? a. 4b. 3.33c. 5.27d. 9 A B C D None 20. A wing with an aspect ratio of 6 and span efficiency factor of 1 has a slope of lift curve at 0.076/degree. What is the lift coefficient at an angle of attack of 4° when the aspect ratio is 8.5? Angle of zero lift is at -2°. a. 0.15b. 0.38c. 0.49d. 0.22 A B C D None 1 out of 2
