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Temperature Conversion
Altitude Correction for Pressure Altitude
Pressure Altitude
Density Altitude
True Altitude
True Airspeed
Temperature Rise
Mach Number
Equivalent Airspeed
1976 Standard Atmosphere
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   Altimetry
 
 

Temperature
Conversion

 
Temperature
     [oF]  [oC]    [oR]    [K]

     Enter a number in any box and get all the remaining box's results            

     Click here for more help and sample problems on this calculator

 

Altitude Correction for
Pressure Altitude

 
Altimeter Setting
    [InHg]    [HPa] or [mbar] 
Altitude Correction
   [ft]  [m] 

     Enter the altimeter setting or altitude correction  

 

Pressure
Altitude

 
Calibrated Altitude
    [ft]
  [m]
Altimeter Setting (QNH)
    [InHg]
  [HPa] or [mbar]
Pressure Altitude
    [ft]  [m]

    Enter any two fields (i.e. Altitude, Altimeter Setting or Pressure Altitude)
    then press "Eval" on any remaining field for that field's result

    QNH is a term not commonly used in the United States but used in many other countries. It is the altimeter setting setting
    such that the altimeter reads altitude above mean sea level at the airport level. In the U.S. this is referred to as the altimeter
    setting and is usually given by ATC (Air Traffic Control) or the airport ATIS (Airport Terminal Information Service)
    among other sources.

    Note that it does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other two rows when the Eval button of that row is pressed.


   Click here for more help and sample problems on this calculator

 

QNH

 
Airport Altitude
    [ft]   [m]
Pressure Altitude at Airport
    [ft]   [m]
Altimeter Setting (QNH)
    [InHg]  [HPa] or [mbar]

    QNH is a term not commonly used in the United States but used in many other countries. It is the altimeter setting setting
    such that the altimeter reads altitude above mean sea level at the airport level. In the U.S. this is referred to as the altimeter
    setting and is usually given by ATC (Air Traffic Control) or the airport ATIS (Airport Terminal Information Service) among
    other sources.
 Pressure Altitude is the altitude the altimeter reads when set to the QNE setting 1013.25 hPa or
    approximately 29.92 InHg. QNE is also a term used more internationally but denotes the altimeter setting to obtain the
    pressure altitude reading.


    Note that it does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other two rows when the Eval button of that row is pressed.
 

QFE

 
Pressure Altitude at Airport
    [ft]   [m] 
QFE Setting
    [InHg]  [HPa] or [mbar] 

    QFE is a term also not commonly used in the United States but referred to in many other countries. In practice it is not used
    very much but it is useful to know of it's existence. It is the altimeter setting such that the altimeter reads zero height at the
    airport level. Pressure altitude is the altitude the altimeter reads when set to the QNE setting 1013.25 hPa or approximately
    29.92 InHg. QNE is also a term used more internationally but denotes the altimeter setting to obtain the pressure altitude
    reading.

 

Density
Altitude

 
Pressure Altitude
  [ft]
[m]
Temperature
  [oF]
[oC] 
Density Altitude
    [ft] [m]

    Enter any two fields (i.e. Pressure Altitude, Temperature or Density Altitude) then press "Eval" on any remaining field
    for that field's result

    Note that it does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other two rows when the Eval button of that row is pressed.

    RELATED WEBSITES:
     Wahiduddin's Website (Interesting website with a very thorough explanation of density altitude)
           Link to a very complete density altitude calculator and discussion of the effects of humidity

 

True
Altitude

 
Pressure Altitude (PA)
    [ft]   [m]
True Air Temperature (Tt)
    [oF]   [oC]
Calibrated Altitude (CA)
    [ft]   [m]
Station Altitude
    [ft]   [m]
True Altitude (TA)
    [ft]   [m]
          or  
Pressure Altitude (PA)
    [ft]   [m]
True Air Temperature (Tt)
    [oF]   [oC]
Altimeter Setting (QNH)
    [InHg]  [HPa] or [mbar]
Station Altitude
    [ft]   [m]
True Altitude (TA)
    [ft]   [m]
          or  
Calibrated Altitude (CA)
    [ft]   [m]
True Air Temperature (Tt)
    [oF]   [oC]
Altimeter Setting (QNH)
    [InHg]  [HPa] or [mbar]
Station Altitude
    [ft]   [m]
True Altitude (TA)
    [ft]   [m]

    Enter any four fields then press "Eval" on any remaining field for that field's result. True Altitude computations are
    inherently imprecise, please be cautious, particularly when extrapolating beyond typical conditions.

    Note 1: If you don't have the Station Altitude set it to zero

    Note 2: It does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other rows when the Eval button of that row is pressed.

 

True
A
irspeed

 
Pressure Altitude (PA)     [ft]   [m]
Recovery Coefficient (CT)    
Calibrated Air Temperature (Tc)    [oF]   [oC]
Calibrated Airspeed (CAS)    [knots]  [Km/h]
True Airspeed (TAS)    [knots]  [Km/h]

                            or

Pressure Altitude (PA)    [ft]   [m]
Calibrated Airspeed (CAS)    [knots]  [Km/h]
True Air Temperature (Tt)    [oF]   [oC]
True Airspeed (TAS)    [knots]  [Km/h]

    Enter any four fields on the upper portion orthree fields on the lower portion then press "Eval" on that portion for any
    remaining
field for that field's result. True Airspeed computations are somewhat imprecise, please be cautious, particularly
    when extrapolating beyond typical conditions. When calculating the Recovery Coefficient there is a vary narrow range of
    solutions. The model used takes into consideration compressibility and may be used for speeds beyond Mach 1.

    Note 1: If you don't know the recovery coefficient set it to 1.0.


    Note 2: It does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other rows when the Eval button of that row is pressed.

 

Temperature
Rise

 
True Airspeed (TAS)    [knots]  [Km/h]
Recovery Coefficient (CT)    
Temperature Rise (ΔT=Tc-Tt)      [oF]   [oC]

    Enter any two fields then press "Eval" on any remaining field for that field's result. When calculating the Recovery Coefficient
    there is a vary narrow range of solutions. The model used takes into consideration compressibility and may be used for speeds
    beyond Mach 1. To calculate True Air Temperature (Tt) use Tt=
Tc-ΔT. Where Tc is the Calibrated Air Temperature and ΔT is
    the Temperature Rise.


    Note 1: If you don't know the recovery coefficient set it to 1.0.


    Note 2: It does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other two rows when the Eval button of that row is pressed.

 

Mach
Number

 
Pressure Altitude (PA)    [ft]   [m]
Calibrated Airspeed (CAS)    [knots]  [Km/h]
Mach Number (M)     

                            or

True Airspeed (TAS)    [knots]  [Km/h]
Recovery Coefficient (CT)   
Calibrated Air Temperature (Tc)    [oF]   [oC]
Mach Number (M)   

    Enter any two fields on the upper portion orthree fields on the lower portion then press "Eval" on that portion for any
    remaining
field for that field's result.

    Note 1: If you don't know the recovery coefficient set it to 1.0.


    Note 2: It does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other rows when the Eval button of that row is pressed.

 

Equivalent
Airspeed

 
Pressure Altitude (PA)    [ft]   [m]
True Air Temperature (Tt)    [oF]   [oC]
True Airspeed (TAS)    [knots]   [Km/h]
Equivalent Airspeed (EAS)    [knots]   [Km/h]

     Enter any three fields then press "Eval" on any remaining field for that field's result 

    Note 2: It does not matter the order that you enter the rows. The remaining row (field) will be
    calculated based on the values of the other rows when the Eval button of that row is pressed.


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