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ATMCALC.DOC
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1988-03-26
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Atmosphere Calculator Documentation
HyperStuffWare - Copyright (c) 1988
ATMCALC has been developed to perform most of the routine atmospheric
calculations used in aviation and aeronautical engineering. The program
contains extensive error checking and has the following options.
[A] User input of pressure altitude (Hc) in feet. After input, the program
updates all other altitude dependant variables such as Mach number but does
not change the calibrated airspeed (Vc) which is independent of Hc.
[B] User input of calibrated airspeed (Vc). After input, the program
updates all airspeed dependant variables at the existing altitude.
[C] User input of true airspeed (Vt). After input, the program calculates a
new Vc at the existing altitude and updates all airspeed dependant
variables.
[D] User input of equivalent airspeed (Ve). After input, the program
calculates a new Vc at the existing altitude and updates all airspeed
dependant variables.
[E] User input of the local speed of sound (a). After input, the program
calculates a new Vc at the existing altitude and updates all airspeed
dependant variables.
[F] User input of the ambient pressure (Pa). After input, the program
calculates a new altitude and updates all other variables while maintaining
the same Vc.
[G] User input of the dynamic pressure (q) which is the velocity component
of the impact pressure (Qc). After input, the program calculates a new Vc
at the existing altitude and updates all airspeed dependant variables.
[H] User input of the impact pressure (Qc) which is the sum of the ambient
pressure and dynamic pressure components. After input, the program
calculates a new Vc at the existing altitude and updates all airspeed
dependant variables.
[I] User input of the static temperature (TAS). After input, the program
calculates a new altitude and updates all other variables while maintaining
the same Vc.
[J] User input of the total temperature (TAT). After input, the program
calculates a new Vc at the existing altitude and updates all airspeed
dependant variables.
[K] User input of the ambient pressure ratio (delta). After input, the
program calculates a new altitude and updates all other variables while
maintaining the same Vc.
[L] User input of the ambient density ratio (sigma). After input, the
program calculates a new altitude and updates all other variables while
maintaining the same Vc.
[M] User input of the static temperature ratio (theta). After input, the
program calculates a new altitude and updates all other variables while
maintaining the same Vc.
[N] User input of the Mach number. After input, the program calculates a
new Vc at the existing altitude and updates all airspeed dependant
variables.
[O] User input of the air density. After input, the program calculates a
new altitude and updates all other variables while maintaining the same Vc.
[P] User input of the ram air temperature recovery factor. This value is
typically 0.80 for aircraft pitot-static systems. It is used in the
relationship between static and total air temperature calculations. After
input, the program uses the existing Vc and Hc to update all other
variables.
[R] User input of Ve and Mach to calculate the altitude at which they are
equal. After input, the program calculates a new Hc and Vc then updates all
other variables.
[S] User input of a temperature differential from the standard atmosphere.
After input, the program calculates a new static temperature then updates
the remaining variables at the existing Vc and Hc.
[Q] Quit AtmCalc.
[Z] User input to reinitialize AtmCalc to zero conditions.