I need this in java, and please pay attention to the bolded sentences. Such as needing the result of the wind correction angle in degrees and not radians, etc.

E6B Flight Computer ?Java Class

The E6B flight computer is a type of slide rule that pilots and navigators traditionally use for performing a variety of calculations. In our E6B, we want to perform the calculations to compute the following:

Density altitude. The following is from the Wikipedia:

Density altitude is the altitude relative to the standard atmosphere conditions (ISA) at which the air density would be equal to the indicated air density at the place of observation. In other words, density altitude is air density given as a height above mean sea level. "Density altitude" can also be considered to be the pressure altitude adjusted for non-standard temperature.

Both an increase in temperature, decrease in atmospheric pressure, and, to a much lesser degree, increase in humidity will cause an increase in density altitude. In hot and humid conditions, the density altitude at a particular location may be significantly higher than the true altitude.

In aviation, the density altitude is used to assess the aircraft's aerodynamic performance under certain weather conditions. The lift generated by the aircraft's airfoils and the relation between indicated and true airspeed are also subject to air density changes. Furthermore, the power delivered by the aircraft's engine is affected by the air density and air composition.

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Calculating Density Altitude

The National Weather Service uses the following dry-air approximation equation in their standards:

where

DA = density altitude in feet

P is the station pressure (atmospheric static pressure) in inches of mercury (inHg).

T is the station temperature (atmospheric temperature) in Fahrenheit (F).

Note that the NWS standard specifies that the density altitude should be rounded to the nearest 100 feet.

You will need to add the DA to the airport elevation to arrive at the final result. Your code should implement a density altitude function;

public double densityAltitude()

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True Airspeed

True airspeed is the indicated airspeed corrected for altitude. For each 1,000 feet of altitude the aircrafts airspeed increases by approximately 2%. The following formula corrects indicated airspeed (IAS) for altitude:

TAS = IAS + (altitude / 1000) * 0.02 * IAS

Example:

Altitude: 8000 feet

IAS: 100 knots

TAS = 116 knots

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Wind Correction Angle

Wind correction angle is the angle that must be added to the desired course heading to offset the effect of a wind on the aircraft. Without such a correction, the aircraft would be flying an incorrect course. Delta-a is the wind correction angle in the following formula:

w is the wind direction in radians. d is the desired course in radians. Va is the true airspeed in knots. Vw is the wind speed in knots.

The programmer user of the E6B class will instantiate the E6B object with the above data, but will use degrees for w and d, instead of radians. Javas Math class has toDegrees() and toRadians() methods. The result will come out in radians, but make your method return the delta-a in degrees. Suggested method header:

public double windCorrectionAngle()

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Ground Speed

Ground speed is the true airspeed (TAS) corrected for winds aloft. The following formula computes ground speed:

desired course is d

?ground speed is Vg?

heading correction angle is delta-a

?true airspeed is Va?

wind direction is w

?wind speed is Vw?

d, a and w are angles entered by the user in degrees. Javas Math class methods assume radians, they should be in degrees

Vg, Va and Vw are consistent units of speed (usually knots).

Suggested method header:

public double groundSpeed()

Suggested Approach

Determine the necessary fields. If a value is used in a computation, you should most likely create a field for it. ?

Make a constructor that initializes each field. Yes, its going to have a lot of parameters. ?

Make each formula a function that returns a single value. ?

Put a main method in your class that tests each method. How do you know if the ?method worked? Use a calculator to verify the method output. A spreadsheet would also be handy for testing. There are also numerous E6B simulators online. ?

Test Data

Station Pressure: 29.45 in Hg

Station Temperature: 95 F

Airport Elevation: 4000 ft

Aircraft Altitude: 8000 ft

Indicated Airspeed: 100 knots

Desired Course: 360

Wind Direction: 300

Wind Speed: 5 knots