In a standard atmosphere and at the sea level the calibrated airspeed CAS is ?
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The parameter that determines the relationship between EAS and TAS is ?
With CAS and pressure altitude we can deduce ?
Speed of sound proportional to The square root of absolute temperature, square root of tas, square of absolute temperature, square of tas. 
The total air temperature tat The temperature resulting from aircraft motion in air, static air temperature (sat) multiplied the recovery factor, impact air temperature measured the pitot probe, average temperature resulting from temperature measure of pitot tat probes. total air temperature tat the temperature that would be measured a temperature probe, if all of kinetic energy of air resulting from aircraft's motion was totally recovered. this can never be very accurately measured, because 100% recovery of kinetic energy impossible a number of reasons. 
During a climb if total pressure head rapidly clogged up ice sensed total pressure remains constant and The static pressure decreases, implying an increasing ias, static pressure decreases, implying a decreasing ias, ias remains also constant, static pressure increases, implying a decreasing ias. 'total pressure hea = pitot tube (it senses dynamic pressure + static pressure). while climbing, static pressure decreases. if total pressure head clogged up ice, airspeed indicator will then show an increasing speed. indicated airspeed = (dynamic pressure + static pressure) static pressure. since question states...the sensed total pressure remains constant... value '(dynamic pressure + static pressure)' does not change, only 'static pressure' reduces, consequence an increasing indicated airspeed. 
The static air temperature sat The ambient outside air temperature, temperature resulting from aircraft motion in air, outside air temperature measured the pitot probe, tat divided the recovery factor. in aviation terminology, outside air temperature (oat) or static air temperature (sat) refers to temperature of air around an aircraft, but unaffected the passage of aircraft through it. Question Measurement of Air Data Parameters 45 Answer 8
The limits of green scale of an airspeed indicator are Vsvno, vsvmo, vsvne, vsvne. Question Measurement of Air Data Parameters 45 Answer 9
Concerning pitot and static system static pressure error varies according to 1 altimeter setting2 speed3 angle of attackthe combination that regroups all of correct statements the static port will be affected speed (compressibility effect) by angle of attack (air flow aournd fuselage will change). altimeter setting irrelevant to pressure sensed at static port. Question Measurement of Air Data Parameters 45 Answer 10
The alternate static source used When static ports become blocked, when drain holes freeze, to compensate static pressure error, to compensate hysteresis of aneroid capsule. the alternate static vent of an unpressurised aircraft senses air pressure in flight deck/cockpit. in flight air outside flight deck accelerates over aircraft canopy (venturi effect) this causes a drop in static pressure. air will always flow from a high pressure to a low pressure, so air in flight deck flows outside. this flow to outside causes pressure in cabin to be lower than undisturbed static pressure around aircraft. Question Measurement of Air Data Parameters 45 Answer 11
The machmeter subject to position error this error varies according to 1 angle of attack2 oat3 tasthe combination that regroups all of correct statements position (pressure) error varies with angle of attack speed but not with temperature. Question Measurement of Air Data Parameters 45 Answer 12
The data output from adc are 1 barometric altitude2 mach number3 cas4 tas5 satthe combination that regroups all of correct statements , 2, 3, 4, 5,, 4, 2, 3, 4,, 3, 5. Question Measurement of Air Data Parameters 45 Answer 13
An aeroplane cruising at fl 60 with a tas of 100 kt in standard atmosphere in these conditions 1 tas approximately 10% higher than ias2 difference between eas and cas negligible3 speed displayed on airspeed indicator a cas if position error and instrument error are zerothe combination regrouping all of correct statements , 2, 3, 2, 3,, 2,, 3. tas = ias + 2% per 1000 ft altitude. eas cas corrected compressibility at low speed low altitude, compressibility negligeable. cas ias corrected position instrument errors. Question Measurement of Air Data Parameters 45 Answer 14
The tas obtained from cas correcting the following errors 1 instrument2 compressibility3 position4 densitythe combination that regroups all of correct statements 2, 4, 2, 4,, 2, 3, 4. Question Measurement of Air Data Parameters 45 Answer 15
The cas obtained from ias correcting the following errors 1 position2 compressibility3 instrument4 densitythe combination that regroups all of correct statements , 3, 3,, 3, 4, 2, 3, 4. Question Measurement of Air Data Parameters 45 Answer 16
The eas obtained from cas correcting the following errors 1 position2 compressibility3 instrument4 densitythe combination that regroups all of correct statements 2, 4, 2, 4,, 2, 3, 4. Question Measurement of Air Data Parameters 45 Answer 17
If static ports are completely clogged up ice during a climb vertical speed indicator shows Zero, a descent if outside static pressure less than pressure in instrument's gauge, a constant rate of climb, even if aircraft levelling out, an increasing rate of climb if ambient static pressure decreases. Question Measurement of Air Data Parameters 45 Answer 18
Eas equal to Cas corrected compressibility error, cas corrected density error, tas corrected compressibility error, tas corrected compressibility density errors. Question Measurement of Air Data Parameters 45 Answer 19
During a climb at a constant mach number below tropopause in standard atmosphere Cas tas decrease, cas increases tas decreases, cas decreases tas increases, cas tas increase. for those questions, use very simple 'ertm' diagram. the mach line vertical because question states climb at a constant mach number. ertm e as/r as(rectified air speed or cas)/t as/m ach. Question Measurement of Air Data Parameters 45 Answer 20
When climbing at a constant cas through an isothermal layer mach number Increases, decreases, remains constant, decreases if oat lower than standard temperature. for those questions, use very simple 'ertm' diagram. the cas line vertical because question states climbing at a constant cas. ertm e as/r as(rectified air speed or cas)/t as/m ach. tas will increase since density decreases with altitude. mach = tas / local speed of sound local speed of sound varies only with temperature, the question states 'isothermal layer' (temperature remains constant), thus lss increases. Question Measurement of Air Data Parameters 45 Answer 21
If pilot increases reference pressure using sub scale setting knob altitude indicated the altimeter Increases, decreases, decreases if qnh >3 hpa, decreases if qnh
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