public final class Airspeeds
extends java.lang.Object
Modified by: Joseph A. Huwaldt
Constructor and Description |
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Airspeeds() |
Modifier and Type | Method and Description |
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static double |
a_a0_fn_theta(double theta)
Calculates the ratio of the speed of sound to the standard sea level speed of sound
as a function of the temperature ratio.
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static double |
a_fn_VT_M(double VT,
double Mach)
Calculates the speed of sound as a function of the true airspeed and Mach number.
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static double |
M_fn_delta_VC(double delta,
double VC_a0,
double gam)
Method that calculates Mach number as a function of pressure ratio, and calibrated
airspeed.
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static double |
M_fn_VT_a(double VT,
double a)
Calculates the Mach number as a function of the true airspeed and local speed of
sound.
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static double |
VC_a0_fn_delta_M(double delta,
double Mach,
double gam)
Method that calculates calibrated airspeed divided by sea level standard day speed
of sound.
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public static double a_a0_fn_theta(double theta)
theta
- Temperature ratio with altitude (T/T0, where T0 = sea level standard
temp).public static double a_fn_VT_M(double VT, double Mach)
VT
- True airspeed.Mach
- Mach numberpublic static double M_fn_VT_a(double VT, double a)
VT
- True airspeed (in same units as "a").a
- Local speed of sound (in same units as VT).public static double M_fn_delta_VC(double delta, double VC_a0, double gam)
delta
- Pressure ratio with altitude (P/P0).VC_a0
- Ratio of calibrated airspeed to standard sea level speed of sound.gam
- The specific heat ratio of the gas. For air, the value is 1.4.public static double VC_a0_fn_delta_M(double delta, double Mach, double gam)
delta
- Pressure ratio with altitude (P/P0).Mach
- Mach number.gam
- The specific heat ratio of the gas. For air, the value is 1.4.