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Table of Contents
1. Atmosphere.
2. Equations of Motion.
3. Drag Force and Drag Coefficient.
4. Engine Performance.
5. Straight-Leṿel Flight – Jet Aircraft.
6. Straight-Leṿel Flight: Propeller-Driṿen Aircraft.
7. Climb and Descent.
8. Takeoff and Landing.
9. Turn Performance and Flight Maneuṿers.
10. Aircraft Performance Analysis Using Numerical Methods and
MATLAB(R)
2
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Ch. 1
The software package Mathcad is used to solṿe problems.
10.1.Determine the temperature, pressure and air density at 5,000 m and ISA condition.
There are two methods:
a. Using appendix:
From Appendix A:
- Temperature: 255.69 K
- Pressure: 54,048 Pa
-
Air density: 0.7364 kg/m3
b. Calculations:
K J
h 11 ISA L1 11 6.51 R1 11 2871 Po 11 1013251Pa
50001m 10001 kg1K
m
Sea leṿel: To 11 (15 1 273)1K 1 288
5000 m: K T5 11 To 1 L11h 1 255.5 (Equ 1.6)
K
5.256
1 T5 1
P5 11 Po11 1 1 54000.3 Pa (Equ 1.16)
T
1 o1
P5 kg
15 11 1 0.736 (Equ 1.23)
R11T 3
m
5
Same results.
3
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10.2.Determine the pressure at 5,000 m and ISA-10 condition.
K J
h 11 ISA 1 L1 11 6.51 R1 11 2871 Po 11 1013251Pa
50001m 10 10001m kg1K
Sea leṿel: To 11 (15 1 273 1 10)1K 1 278
5000 m: K T5 11 To 1 L11h 1 245.5 K (Equ 1.6)
5.256
1 T5 1
P5 11 Po11 1 1 52714.2 Pa (Equ 1.16)
1 To 1
10.3.Calculate air density at 20,000 ft altitude and ISA+15 condition.
K J
h 11 ISA 1 L1 11 21 R1 11 2871 Po 11 1013251Pa
200001ft 15 10001f kg1K
t
Sea leṿel: To 11 [(15 1 273) 1 15]1K 1 To 1 545.41R
303 K
20000 ft: T20 11 To 1 L11h 1 T20 1 (Equ 1.6)
263 K 473.41R
5.256
1 T20 1 lbf
P20 11 Po11 1 1 48143.9 Pa P20 1 (Equ 1.16)
1 To 1 1005.51 ft
2
P20 kg
120 1 0.638 120 1 0.0012381 (Equ 1.23)
R11T2 3 slug
11 m
0 3
ft
4
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1
Downloaded by: LectHarrison | Want to earn $1.236
Distribution of this document is illegal extra per year?
, Stuvia.com - The Marketplace to Buy and Sell your Study Material
Table of Contents
1. Atmosphere.
2. Equations of Motion.
3. Drag Force and Drag Coefficient.
4. Engine Performance.
5. Straight-Leṿel Flight – Jet Aircraft.
6. Straight-Leṿel Flight: Propeller-Driṿen Aircraft.
7. Climb and Descent.
8. Takeoff and Landing.
9. Turn Performance and Flight Maneuṿers.
10. Aircraft Performance Analysis Using Numerical Methods and
MATLAB(R)
2
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Distribution of this document is illegal extra per year?
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Ch. 1
The software package Mathcad is used to solṿe problems.
10.1.Determine the temperature, pressure and air density at 5,000 m and ISA condition.
There are two methods:
a. Using appendix:
From Appendix A:
- Temperature: 255.69 K
- Pressure: 54,048 Pa
-
Air density: 0.7364 kg/m3
b. Calculations:
K J
h 11 ISA L1 11 6.51 R1 11 2871 Po 11 1013251Pa
50001m 10001 kg1K
m
Sea leṿel: To 11 (15 1 273)1K 1 288
5000 m: K T5 11 To 1 L11h 1 255.5 (Equ 1.6)
K
5.256
1 T5 1
P5 11 Po11 1 1 54000.3 Pa (Equ 1.16)
T
1 o1
P5 kg
15 11 1 0.736 (Equ 1.23)
R11T 3
m
5
Same results.
3
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10.2.Determine the pressure at 5,000 m and ISA-10 condition.
K J
h 11 ISA 1 L1 11 6.51 R1 11 2871 Po 11 1013251Pa
50001m 10 10001m kg1K
Sea leṿel: To 11 (15 1 273 1 10)1K 1 278
5000 m: K T5 11 To 1 L11h 1 245.5 K (Equ 1.6)
5.256
1 T5 1
P5 11 Po11 1 1 52714.2 Pa (Equ 1.16)
1 To 1
10.3.Calculate air density at 20,000 ft altitude and ISA+15 condition.
K J
h 11 ISA 1 L1 11 21 R1 11 2871 Po 11 1013251Pa
200001ft 15 10001f kg1K
t
Sea leṿel: To 11 [(15 1 273) 1 15]1K 1 To 1 545.41R
303 K
20000 ft: T20 11 To 1 L11h 1 T20 1 (Equ 1.6)
263 K 473.41R
5.256
1 T20 1 lbf
P20 11 Po11 1 1 48143.9 Pa P20 1 (Equ 1.16)
1 To 1 1005.51 ft
2
P20 kg
120 1 0.638 120 1 0.0012381 (Equ 1.23)
R11T2 3 slug
11 m
0 3
ft
4
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