Summer is a time to slip the surly bonds and go on that adventure to the coast or to the mountains, to load
up the family and make your way to Disneyland, or airplane camping and fishing in the wilderness. It is a time
to use your craft in the myriad ways for which it was intended. But, when the mercury rises, you know your airplane
just isn't going to perform in the way to which you are accustomed, especially at higher altitudes.
At a given gross weight, increase in density altitude (DA) means a reduction in engine horsepower (thus a reduction
in thrust), increased ground speed (thus longer takeoff and landing rolls), and decreased climb performance. The
changes can be significant, especially at higher elevations. 
photo by Amy Hoover

A turbocharger can solve some of the problems (except with your pocketbook). However, loss
of propeller efficiency is a big factor, even on turbocharged aircraft. If your summer flying takes you to the
mountains, you will learn to operate in the morning or late evening when your engine, propeller, and wings perform
better. A major item you can control is how you load your airplane; you determine is how you load your airplane.
When you operate at higher elevation airports in the heat
of the summer, do you have a handle on how much weight reduction is necessary for safe operations? How often do
you really know just what you can expect from your airplane at higher density altitudes? Your aircraft performance
charts are a good place to start. However, many charts only give performance figures at gross weight, and some
older aircraft substantial charts or data. Remember that you are not flying a new airplane and your performance
will probably not meet the expectations of the charts.
photo by Amy Hoover 
An excellent method of determining effects of density altitude
is to build your own performance charts. Load your airplane to different weight and Center of Gravity positions
and record takeoff and landing distances at different density altitudes for each weight/CG combination. This requires
some time commitment, but is worth it. Use a runway where you have references, such as spacing of runway edge lights,
to be as accurate as possible in recording takeoff and landing distances. You may need to factor in other variables
such as runway gradient, runway surface conditions, and wind. If you get the chance, attend a density altitude
clinic, such as the ones sponsored by the FAA, to collect data on your aircraft performance. 
Determining Density Altitude (DA):
Following is a simple way to determine density altitude
(DA) at a given pressure altitude (PA):
Rule of thumb:
To determine DA at a given PA, add 600 feet to existing
PA for every 10° F above standard temperature for that altitude. 
To do this, you must know the standard temperature at a given PA as shown
in the table to the right. You should know the standard temperature for your home field and otherelevations you
use often. 
Pressure altitude......... Standard
temperature
Sea level....................59.0° F.............15° C
1000 feet ....................55.5° F.............13° C
2000 feet ....................52.0° F.............11° C
3000 feet ....................48.5° F...............9° C
4000 feet ....................45.0° F...............7° C
5000 feet ....................41.5° F...............5° C
6000 feet ....................38.0° F...............3° C
7000 feet ....................34.5° F...............1° C
8000 feet ....................31.0° F..............1° C
9000 feet ....................27.5° F..............3° C

Standard Temperature at
Different pressure altitudes
Here is an example using this simple rule of thumb. Suppose you want
to depart from an airport at elevation 5000 feet on a summer day and the temperature is 85°F.
Example:
Pressure altitude (PA)...............= 5000 feet
Temperature.............................= 85° F
Standard temp at 5000 ft...........= 41.5° F
Temp = 85  41.5......................= 43.5° above standard
Using the Rule of thumb, round off the numbers to make it easier:
Density altitude (DA).................= 5000 + (600 x 4.4)
...............................................= 5000 + 2640
...............................................=7600 feet 
Thus, A typical summer density altitude in much of the mountain west
is over a mile and a half high when you are sitting on the ground!
Another example:
PA..........................................= 9000 feet
Temp......................................= 70° F
Standard temp at 9000 feet.......= 27.5° F
Temp .....................................= 70  27.5
..............................................= 42.5 degrees above standard
Density Altitude (DA)...............= 9000 + (600 X 4.3)
..............................................= 9000 + 2580
..............................................=11,600 feet 
In the mountains,
where you will be flying at actual elevations ranging from over a mile to as much as 17,500 feet, increased density
altitudes create a problem! Do you fly an airplane whose service ceiling is only a few hundred feet above the density
altitude? What will your climb rate be? These are questions you should be posing when the temperatures start to
rise. Having a quick idea of the density altitude is the best starting point. The next step is to determine…
Reduction in engine horsepower due to DA increase:
As density altitude increases, engine horsepower decreases. If you know what the decrease is and how to apply that
knowledge, you can determine roughly what your performance degradation will be and how much weight you may have
to take out of the airplane to operate safely. The following is based on standard atmospheric pressure lapse rate
and reciprocating engine efficiency.
Rule of thumb: A normally aspirated aircraft engine loses approximately
3.5% hp per 1000 feet increase in DA

Let's use a common airplane as an example, a Cessna 182.
Example: 230 hp airplane at the 5000 ft airport where the DA = 7600 feet
HP reduction.................= 3.5% x 7.6
....................................= 27% reduction (approximately 73% available)
230hp x (73%)...............= 168 hp available
at 7600 ft DA 
Another way to determine the amount of power reduction is to know
what your engine will produce at full power on the MP gauge at sea level on a standard day. Then, determine the
amount of power per inch it is producing, and calculate power reduction based on the fact the engine will lose
one inch of manifold pressure per 1000ft DA.
Example:
given a 230hp engine that produces 28" MP at full power, sea level standard day
Horsepower per inch..................= 230hp divided by 28"
...............................................= 8.2 hp per inch
At 7600 ft DA the engine will produce approximately 20.4" (28"  7.6") at full power and the horsepower
will be:
8.2 hp per inch X 20.4"..............= 168 hp available at 7600 ft
DA 
Either of the above methods work in estimating your power reduction and
give similar results. The amount of reduction may seem a shock at first, but it should alert you to the realities
of density altitude related performance problems.
The next question is, how much weight must you remove to compensate for
the reduced power if you want to operate at a roughly equivalent sea level performance? One way to do this is do
determine the aircraft power loading at which you want to operate, and load the aircraft accordingly. 

photo by George Dorris
Power loading and weight reduction
Sea level standard day power loading is defined as gross weight (GW)
divided by horsepower available. In many of the newer Owners manuals or Pilots Operating Handbooks sea level power
loading is given with other performance figures, but it is easy to calculate. Using the Cessna 182 again:
Example:
The Cessna 182 is A 2950lb, 230hp airplane at sea level:
Power loading ......................= 2950lb......= 12.8 lb/HP
...............................................230HP
To get sea level power loading out of the airplane at higher density
altitudes, you would have to remove enough weight such that the new weight to hp ratio equals 12.8 lb/HP. To do
this, first compute net HP for density altitude:
From the previous example:.....5000 ft PA and 85° F
Density altitude......................= 7600 ft
Horsepower available..............= 168 hp
Original (certified) GW............= 2950 lbs
To calculate the "effective" gross weight that will give equivalent
power loading, multiply the net HP available by the desired sea level power loading:
net HP available x SL power loading........= new GW
..............168hp
x 12.8...........................= 2150 lbs
Thus to obtain sea level equivalent power loading for the Cessna 182
on a summer day at 5000ft elevation and 85° F you must remove roughly 800
lbs!! That is equivalent to two
180lb passengers, two 75lb bags, and 48 gallons of gas!
The calculation may be done using any power loading you choose to get
an approximation of the expected performance. For example, if you usually operate from a 3000ft elevation airport
and the performance there is adequate, simply calculate the power loading using 3000ft pressure altitude and standard
temperature, and use that figure as the standard of comparison.
Aircraft loading and weight are items over which pilots have direct and
immediate control. We have looked at how to reduce aircraft weight to get better performance. However, you may
choose to fly with a given weight and accept the decrease in performance. If so, you should have a good idea of
just what that decrease in performance is going to be. If an aircraft has inadequate performance charts, you may
choose to make your own, as suggested earlier. Or, you may have to make some choices, such as flying only in the
morning or evening, or making multiple trips carrying lighter loads.
The bottom line is, be aware of the effects of density altitude on the
performance of any aircraft, and learn to lighten up!!
Author: Amy L. Hoover
