Currently I do fuel planning as follows:
From several flights I obtained the following empirical numbers for fuel flow during cruise flight:
| Fuel Flow (1,000 pph) | Speed (M) |
| Altitude (FL) | 0.63 | 0.66 | 0.70 | 0.80 | 0.82 | 0.827 | 0.83 |
| 100 | 21.2 |
| 150 | | 19.2 |
| 250 | | | 14.4 | 18.8 |
| 270 | | | | 17.2 |
| 330 | | | 11.6 | 12.8 | 14.4 | | 15.6 |
| 350 | | | | | 13.6 |
| 370 | | | 9.6 | 11.8 | 12.0 | 12.6 |
| 390 | | | | 10.0 | 11.2 |
| 410 | | | | 9.6 | 10,4 |
01) [Speed of Sound at cruising altitude (kts)]
= IF [Flight Level] > 370 THEN 573.17 ELSE (-0.2378 * [Flight Level] + 660.98) END
02) [True Cruising Airspeed (kts)]
= [Mach Cruising Speed]
* [Speed of Sound at cruising altitude]
03) Estimated [Climb, Descent & Approach Distance on course (nm)] = 130
04) [Cruising Distance (nm)]
= [Flight Plan Distance (nm)]
- [Climb, Descent & Approach Distance on course (nm)]
05) [Time of Cruise Flight (hrs)]
= [Cruising Distance (nm)]
/ [True Cruising Airspeed (kts)]
06) [Cruise Fuel (1,000 lbs)]
= [Cruising Fuel Flow (1,000 pph) from table]
* [Time of Cruise Flight (hrs)]
07) Estimated [Taxi-out Fuel (1,000 lbs)] = 1.3
08) Estimated [Takeoff & Climb Fuel (1,000 lbs)] = 12
09) Estimated [Descent & Approach & Landing Fuel (1,000 lbs)] = 5
10) Estimated [Taxi-in Fuel (1,000 lbs)] = 0.9
11) [Fuel Required (1,000 lbs)]
= [Taxi-out Fuel]
+ [Takeoff & Climb Fuel]
+ [Cruise Fuel]
+ [Descent & Approach & Landing Fuel]
+ [Taxi-in Fuel]
12) [Diversion-to-Alternate Fuel (1,000 lbs)]
=
(
IF ([Distance to Alternate (nm)] - [Climb, Descent & Approach Distance on course (nm)] < 0
THEN 0
ELSE
([Distance to Alternate (nm)] - [Climb, Descent & Approach Distance on course (nm)]
END
)
/ [True Cruising Airspeed (kts)]
* [Cruising Fuel Consumption (1,000 pph)]
+ [Takeoff & Climb Fuel (1,000 lbs)]
+ [Descent & Approach & Landing Fuel (1,000 lbs)]
13) Estimated [Holding Fuel (30 min @ 225 KIAS, 1,000 lbs)] = 5.2
14) [Safety Addition (10%) (1,000 lbs)]
= 0.1
*
(
[Fuel Required (1,000 lbs)]
+ [Diversion Fuel (1,000 lbs)]
+ [Holding Fuel (30 min @ 225 KIAS, 1,000 lbs)]
)
15) [Total Fuel (1,000 lbs)]
= [Fuel Required (1,000 lbs)]
+ [Diversion Fuel (1,000 lbs)]
+ [Holding Fuel (30 min @ 225 KIAS, 1,000 lbs)]
+ [Safety Addition (10%) (1,000 lbs)]
I do not take into account
- the actual weight of the airplane
- cruise climbs
- actual pressure altitude
- ...
- ...
but it works well enough.
--------------
Markoz:
What altitude at what weight?
Derived from the Pan Am 707-300 Aircraft Operating Manual:
0.82M Cruise Optimum Altitudes:Gross Weight (GW) <= 205,000 lbs : FL410 / FL390
GW <= 265,000: FL370
GW <= 275,000: FL350
GW <= 315,000: FL330 / FL320
Long Range Cruise Optimum Altitudes (0.805M … 0.806M):GW <= 195,000: FL410
GW <= 215,000: FL390
GW <= 275,000: FL370
GW <= 295,000: FL350
GW <= 315,000: FL330
Best regards
Alex