ASCI 310: Aircraft Performance Research Project
Objectives
One of the requirements for this course is an Aircraft
Performance Research Project that entails planning a flight from Denver
International Airport (KDEN) to Chicago O’Hare International Airport (KORD) for
a given aircraft, weather conditions, and assumptions. The objective is to apply what has been
learned throughout this course. Drawing
on aeronautics theory and using the performance charts and equations presented
in the course, each student is to answer a sequence of questions that step
through the planning process. Remember,
as with all of the exercises, all work (calculations) must be shown as much as
possible. After all of the questions
have been answered, the next task is to create a two-dimensional representation
of the flight path showing the airspeeds, distance, fuel burned, and fuel
remaining for the Takeoff, Climb, Cruise, Descent, and Approach phases of the
flight.
Project Files – Save all of the files to your computer or a
memory device for ready access outside of this course. In Week 5, familiarize yourself the project
files to get an idea of the expectations.
Much of the knowledge and skills for solving this project are covered in
Modules 6 through 8.
Here are some important notes for this project:
1. Max takeoff weight may not be realized taking off from a
high-density altitude airfield.
2. To find out how many passengers you can transport, you
need to know how much fuel you need for the flight.
3. Make sure you don’t exceed the max landing weight.
4. You might have to do some iterative calculations to
complete the profile.
5. Show your work as much as possible.
6. Answers can vary due to chart interpretations and because
one wrong answer will carry throughout the project. Consequently, this will be considered in the
grading.
Deadline
The Aircraft Performance Research Project is due by the last
day of the course. The deliverable (answers and flight profile) must be
submitted using the activity link in Module 9.
You may submit the deliverable as a Microsoft Word or PowerPoint file or
an Adobe PDF file.
Project Evaluation
Thecompleted Project will be evaluated using this Project
Evaluation Rubric on a 0 to 100-pt scale. The score on theproject is worth 15%
of the course grade.
Evaluation
Description
Points
Questions
There are eight sections.
Except for questions 6.1 and 8.1, each question in each sectionis worth
1.5 points.
69
Question 6.1
Find Maximum passengers/baggage and fuel required for the
flight.
3
Question 8.1
Find average takeoff acceleration using takeoff ground roll
and VR.
3
Flight Profile
Two-dimension representation of the flight path showing
airspeed, altitude, time, distance, and fuel burned and remaining for each
flight segment.
15
Style
Overall Presentation
10
Total Possible Score
100
Aircraft Information
Aircraft
C-9B
Engines
Twin JT8D-9 engines rated at 14,500 lb static sea level
Max Ramp Gross Weight
111,000 lb
Max Takeoff Gross Weight
110,000 lb
Max Landing
99,000 lb
Empty Weight Including Aircrew
60,000 lb
Estimated Wing Area
1300 ft2
Glide Ratio at (L/D)max
17/1
Max Fuel
38,000 lb
Max Passengers
90
Assumptions
Start/Taxi Fuel
300 lb
Takeoff Fuel Burn
700 lb
Approach Fuel Burn
300 lb /approach
Average Weight per Passenger including Baggage
225 lb/per person
Fuel Required
Start/Taxi Fuel +Takeoff Fuel + Climb Fuel + Cruise Fuel +
Descent Fuel + Approach Fuel + 30 min reserve at Cruise Speed/Fuel Flow
KDEN Denver International Airport and Weather Information
Winds
160 deg @ 20 kts
Barometric Altimeter Setting
29.32
Temperature
+30 deg
KORD Chicago International Airport and Weather Information
Winds
320 deg @ 25 kts
Barometric Altimeter Setting
30.52
Temperature
0 ºC
Winds and Temperature Aloft
Cruise FL350 Winds
240 deg @ 100 kts Temperature Standard
Climb-Assume
No Winds & Temperature is ISA +15 ºC for the Climb
SECTION 1: Takeoff Questions atKDEN
Note. Assume Flaps at
15 deg.
1.1. (1.5 pts) Find Maximum Takeoff Weightfor the given
conditions.Assume takeoff is at Max Recommended Takeoff weight accounting for
Density altitude(see Figure 11-21).
1.2. (1.5 pts) Find Takeoff Speeds:V1, V2, VR(see Figure
11-25). Assume Min Speed due to VMCG
Requirements is OK.
1.3. (1.5 pts) Find Flap Retraction Speed (KIAS).
1.4. (1.5 pts) Find Slat Retraction Speed (KIAS).
1.5. (1.5 pts) Find Critical Field Length (ft).
1.6. (1.5 pts) Find Distance to Accelerate and Stop with a
Single Engine Failure at V1(ft).
1.7. (1.5 pts) Find Distance to Liftoff with Single Engine
Failure at V1 and continue Takeoff(ft).
1.8. (1.5 pts) Find Two Engine Takeoff Ground Roll (ft).
1.9. (1.5 pts) Isthe runway long enough at KDEN to safely
takeoff?
SECTION 2: Climb Questions (Long Range Climb to FL350)
Hint. Remember, the
aircraft is taking off at a higher pressure altitude!
2.1. (1.5 pts) Find Climb Schedule (Airspeed/Mach to be
flown in the Climb).
2.2. (1.5 pts) Find Time to Climb (min).
2.3. (1.5 pts) Find Distance to Climb (nm).
2.4. (1.5 pts) Find Fuel for Climb (lb).
SECTION 3: Cruise Questions (Long Range Cruise at FL350)
KDEN – KORD
Note. Assume no
anti-ice and two engines.
3.1. (1.5 pts) Find Cruise Indicated Airspeed (KIAS).
3.2.(1.5 pts) Find Cruise True Airspeed (KTAS).
3.3.(1.5 pts) Find Cruise Ground Speed (KGS).
3.4.(1.5 pts) Find Total Cruise Fuel Flow (lb/hr). Note,
fuel flow listed is for each engine.
3.5.(1.5 pts) Find Cruise Mach (M).
3.6.(1.5 pts) Find Cruise Specific Range (nm/1000lb).
3.7.(1.5 pts) Find Maximum Level Flight Speed: Max Thrust at
the Top of Climb Weight.
SECTION 4: Descent Questions (Long Range Optimum Descent
from FL350)
4.1.(1.5 pts) Find Decent Schedule (Airspeed/Mach to be
flown in the Descent).
4.2.(1.5 pts) Find Time to Descent (min).
4.3.(1.5 pts) Find Fuel for Descent (lb).
4.4.(1.5 pts) Find Distance for Descent (nm).
SECTION 5: Holding and Endurance
5.1.(1.5 pts) Find Max endurance and holding speed for
aircraft at GW75klb@10kft Pressure Altitude.
SECTION 6: Approach and Landing (Flaps 50 deg) KORD
6.1.(3 pts) Find Maximum passengers/baggage and fuel
required for flight.
Hint: Find fuel for each segment of the flight plus
reserves, and then subtract from Max Recommended Takeoff weight determined in
Section 1. Then divide allowable Weight
by passenger Cargo Weight.
6.2.(1.5 pts) Find Reference Speed for predicted Landing
Weight (KIAS).
6.3.(1.5 pts) Find Final Approach speedwith 50 degflaps
(KIAS).
6.4.(1.5 pts) Find Landing DistanceFull Anti-Skid/ No
Reverse Thrust/Full Spoilers(ft).
6.5.(1.5 pts) FindMax Angle of Bankfor Stick Shaker at Vref
+5 for predicted Landing Weight.
SECTION 7: Lost Airspeed Indication beforeDescent
7.1.(1.5 pts) Find Cruise FL350 Target Pitch Attitude and
%N1.
7.2.(1.5 pts) Find Descent Profile.
7.3.(1.5 pts) Find Terminal Area Flight Profile (0 deg
Flaps).
7.4.(1.5 pts) Find Final Approach Profile (50 deg Flaps).
SECTION 8: Additional Performance Questions
8.1.(3 pts) Find average takeoff acceleration using takeoff
ground roll and VR. (Hint. Convert VR to
KTASand then to Ground Speed.)
8.2.(1.5 pts) Find average drag on takeoff roll assuming
constant thrust. Account for reduced
thrust at higher density altitude: Use Equation 6.5, let x = 0.8, and constant
rolling friction.
Assume no lift on wings until rotation.
8.3.(1.5 pts) Find Stall Speed (KIAS) at Takeoff weight with
flaps at 15 degand slats extended.
8.4.(1.5 pts) Find CLMAX at Takeoff weight with flaps at 15
degand slats extended.
8.5.(1.5 pts) Find Stick Shaker Speed (KIAS) at Takeoff
weight with Flaps at 15 degand slats extended.
8.6.(1.5 pts) Find CL at Stick Shaker Speed with flaps at 15
degand slats extended.
8.7.(1.5 pts) Find Airspeed Envelope Maximum and Minimum
Mach for Wings Level, GW 80,000 lb, andFL350 based on Buffet Boundary.
8.8.(1.5 pts) Find Maximum Load factor (g) and AOBat FL350
andGW 80,000 lb for buffet free flight.
8.9.(1.5 pts) Find Initial Climb Gradient for Takeoff
Conditions fora single engine.
8.10.(1.5 pts) Find Initial Rate of Climb for a
single-engine takeoff
8.11.(1.5 pts) Find Excess Thrust (lb) for initial single
engine climb. Assume V= 1.23 Vs and V is converted to TAS.
8.12.(1.5 pts) Ifboth engines flameout at FL350 125 nm prior
to Chicago, and you fly at best glide speed, will you make Chicago on a
flameout approach?
8.13.(1.5 pts) Find Drag (Thrust Required) at (L/D)max at
Sea Level Takeoff weight.
8.14.(1.5 pts) Find Temperature Ram Rise at Cruise Mach for
a standard temperature probe assuming 100% recovery.
