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101.	Calculate the ideal temperature rise when total temperature is 440K and temperature at that point is 369K.(a) 71(b) 70(c) 75(d) 78This question was posed to me in a national level competition.This intriguing question originated from Measurement of Air Temperature topic in division Atmosphere and Air Data Measurement of Aircraft Performance
Answer» RIGHT answer is (a) 71 For explanation: The answer is 71. GIVEN Tt=440K and T=369K. The IDEAL TEMPERATURE rise is measured by the formula, Tt-T. On substituting the values we GET the indicated temperature rise=440-369 The indicated temperature rise=71.

102.	Transducers are the pressure devices used to convert signal in one form of energy to another energy form.(a) True(b) FalseI got this question during an internship interview.This intriguing question originated from Air Data Computers topic in chapter Atmosphere and Air Data Measurement of Aircraft Performance
Answer» Right CHOICE is (a) True The BEST I can explain: Transducers are the PRESSURE devices used to CONVERT signal in one form of energy to another energy form. Pressure transducers can also be called as TRANSMITTERS, senders, indicators or piezometers.

103.	FSO stands for ____________(a) Full-scale output(b) Flight-scale output(c) Flight stimulation output(d) Full screen outputThe question was asked by my school teacher while I was bunking the class.Origin of the question is Air Data Computers topic in portion Atmosphere and Air Data Measurement of Aircraft Performance
Answer» CORRECT choice is (a) Full-scale output Easiest explanation: FSO STANDS for full-scale output. At a specific TEMPERATURE the variation in output signals as the transducer performs over a RANGE from MINIMUM to maximum pressure is known as full-scale output.

104.	Find the flow speed of air when the dynamic pressure is 70516 N/m^2 and density is 1.23kg/m^3.(a) 338.62 m/s(b) 340 m/s(c) 313.5 m/s(d) 321.5 m/sThis question was posed to me at a job interview.This intriguing question comes from Air Data Computers in portion Atmosphere and Air Data Measurement of Aircraft Performance
Answer» Correct ANSWER is (a) 338.62 m/s For explanation I WOULD say: The answer is 338.62 m/s. GIVEN dynamic pressure=70516 N/m^2 and density is 1.23kg/m^3. From the formula q=\(\frac{1}{2}\)ρV^2, substitute the given values. On solving we GET 70516=\(\frac{1}{2}\)1.23V^2 V=338.62 m/s.

105.	Dynamic pressure is the difference between stagnation pressure and static pressure.(a) True(b) FalseThe question was asked in quiz.My question is taken from Air Data Computers in portion Atmosphere and Air Data Measurement of Aircraft Performance
Answer» The correct choice is (a) True Explanation: DYNAMIC pressure is the difference between stagnation pressure and static pressure. In simpler way it is kinetic energy per unit volume of a FLUID particle. It is REPRESENTED by ‘q’. The formula for dynamic pressure is given by q=\(\frac{1}{2}\)γPM^2 where q=dynamic pressure, P is pressure of the fluid, M is mach NUMBER of that medium and γ is the ratio of SPECIFIC heat at constant pressure to that of specific heat at constant volume.

106.	Air data computer system measures airspeed, mach number, temperature and height.(a) True(b) FalseI had been asked this question in an internship interview.The origin of the question is Air Data Computers topic in portion Atmosphere and Air Data Measurement of Aircraft Performance
Answer» Correct ANSWER is (a) True To explain I would say: Air data COMPUTER SYSTEM MEASURES airspeed, mach number, temperature and height. Air data computer is an important avionic component present in an aircraft that measures airspeed, mach number, temperature and height with the help of pitot-static tube.

107.	Which of the following is the correct formula for dynamic pressure?(a) q=\(\frac{1}{2}\)γPM^2(b) q=\(\frac{1}{2}\)γρM^2(c) q=\(\frac{1}{2}\)γPV^2(d) q=\(\frac{1}{2}\)γρV^2This question was posed to me during an interview.This interesting question is from Air Data Computers in division Atmosphere and Air Data Measurement of Aircraft Performance
Answer» Right CHOICE is (a) q=\(\frac{1}{2}\)γPM^2 The best explanation: The correct formula for DYNAMIC pressure is q=\(\frac{1}{2}\)γPM^2 where q=dynamic pressure, P is pressure of the fluid, M is MACH number of that medium and γ is the ratio of specific heat at CONSTANT pressure to that of specific heat at constant volume.

108.	Dynamic pressure is directly proportional to the flow speed.(a) True(b) FalseThe question was posed to me during an internship interview.Origin of the question is Air Data Computers in section Atmosphere and Air Data Measurement of Aircraft Performance
Answer» Right answer is (a) True Easiest EXPLANATION: DYNAMIC pressure is directly proportional to the flow speed. The formula for dynamic pressure is q=\(\frac{1}{2}\)γPM^2 where q=dynamic pressure, P is pressure of the fluid, M is mach number of that medium and γ is the ratio of specific heat at constant pressure to that of specific heat at constant VOLUME.

109.	Calculate the dynamic pressure of aircraft in air when density and flow speed are 1.23 kg/m^3 and 340m/s.(a) 71094 N/m^2(b) 54128N/m^2(c) 65487 N/m^2(d) 65789 N/m^2This question was posed to me during an interview for a job.This interesting question is from Air Data Computers topic in portion Atmosphere and Air Data Measurement of Aircraft Performance
Answer» The CORRECT answer is (a) 71094 N/m^2 The BEST explanation: The answer is 71094 N/m^2. GIVEN speed=340m/s, ρ=1.23kg/m^3. On substituting the values in the formula q=\(\frac{1}{2}\)ρV^2. We GET q=\(\frac{1}{2}\)1.23340^2 On solving we get q=71094 N/m^2.

110.	Calculate the dynamic pressure of aircraft in air when mach number and pressure are 2 and 101325N/m^2.(a) 283710 N/m^2(b) 541278 N/m^2(c) 352769 N/m^2(d) 457815 N/m^2The question was posed to me in exam.My enquiry is from Air Data Computers in division Atmosphere and Air Data Measurement of Aircraft Performance
Answer» CORRECT option is (a) 283710 N/m^2 To elaborate: The answer is 283710. Given M=2, P=101325 N/m^2 and we know γ for air is 1.4. On substituting the values in the formula q=\(\FRAC{1}{2}\)γPM^2 We get q=\(\frac{1}{2}\)1.4101325*2^2 On solving we get q=283710 N/m^2.

111.	The Pitot-static system pressures are given to the air data computers to find CAS, density and temperature.(a) True(b) FalseThis question was posed to me during an online exam.My question is based upon Air Data Computers in section Atmosphere and Air Data Measurement of Aircraft Performance
Answer» Correct option is (b) False The best explanation: The Pitot-static system pressures are given to the AIR data computers to find CAS (calibrated air speed), PRESSURE height and Mach number. In addition we can find EAS (equivalent air speed) by scale-altitude correction APPLIED to CAS (calibrated air speed).

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