Supersonic Aerodynamics 01:00:00 Welcome, You are about to take up the Supersonic Aerodynamics. 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 15 items multiple choice type of question. 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. What happens to the pressure across the shockwave? a. increaseb. decreasec. remains the samed. none of the above A B C D None 2. The aircraft is said to be trimmed if a. The moment at aerodynamic center is zerob. The rotation at center of pressure is zeroc. The rotation at center of gravity is zerod. The rotation at geometric center is zero A B C D None 3. It is the angle between the chord line and the longitudinal axis of the aircraft a. Sweep angleb. Angle of Attackc. Angle of Incidenced. Dihedral Angle A B C D None 4. Which of the following statements is true about maximum L/D ratio? a. can be found where Cl is at maximumb. can be found where Cd is minimumc. located where both Cl and Cd is minimumd. None of the Above A B C D None 5. What happens to the value of lift as velocity is doubled? a. lift is doubledb. lift is tripledc. lift is quadrupledd. lift is reduced by half A B C D None 6. a. 54,000b. 44,000c. 62, 000d. 32,000 A B C D None 7. a. 12 kmb. 13 kmc. 14 kmd. 15 km A B C D None 8. a. 91 ft/sb. 81 ft/sc. 131 ft/sd. 241 ft/s A B C D None 9. a. 308.22 ft/sb. 542.0 ft/sc. 238.33 ft/sd. 448.6 ft/s A B C D None 10. Air enters a converging-diverging nozzle at 0.5 MPa with a negligible velocity. Assuming the flow to be isentropic, determine the pressure that will result in an exit Mach number of 1.8. a. 0.07b. 0.08c. 0.09d. 0.10 A B C D None 11. An airfoil is in a freestream where P = 0.61 atm, ρ = 0.819 kg/m^3, and V = 300 m/ s. At a point on the airfoil surface, the pressure is 0.5 atm. Assuming isentropic flow, calculate the velocity at that point. a. 2132b. 1132c. 932d. 832 A B C D None 12. Consider a normal shock wave in air where the upstream flow properties are V = 680 m/s, T = 288 K, and P = 1 atm. Calculate the pressure downstream of the shock. a. 4.5b. 3.5c. 2.5d. 1.5 A B C D None 13. Consider the isentropic supersonic flow through a convergent-divergent nozzle with an exit-to-throat area ratio of 10.25. The reservoir pressure and temperature are 5 atm and 600 R, respectively. Calculate the temperature at the nozzle exit. a. 240 Kb. 283 Kc. 162 Kd. 146 K A B C D None 14. A slender missile is flying at Mach 1.5 at low altitude. Assume the wave generated by the nose of the missile is a Mach wave. This wave intersects the ground 559 ft behind the nose. At what altitude is the missile flying? a. 173b. 273c. 373d. 473 A B C D None 15. a. 1b. 2c. 3d. 4 A B C D None 1 out of 2 Previous0 %NextNext
