Can you please attempt question 1 please. 2.1. Find the compressible Cp_min and lift coefficient for the subsonic and transonic aerofoils usingthe data provided in Tables 1, 2 and 4. Use 2 compressibility corrections of your choice; whichone is more accurate and why?Determine the critical Mach number and the drag-divergence Mach number for the subsonicand transonic aerofoils, using any method you prefer. Compare the values between the twoaerofoils and explain whether the transonic aerofoil is better than the subsonic one and why. FontAerofoilNACA 2412NACA 34011SupersonicWingAssessment Information/BriefParagraphAerofoilSubsonic aerofoilSubsonic/TransonicSupersonict/c (%)12116Speed RegimeSubsonicTransonicSupersonic-0.7Transonic aerofoil -0.98Max t/c position (c) Max camber (%c)292293933Table 1: Aerofoil informationIncompressible min Cp Incompressible C₁ Analysis conditions0.3857M = 0.2, Re = 6000000,AoA = 1StylesM-0.2, Re-6000000,AoA=1Table 2: Incompressible Low Speed Analysis Data:Span (m) Area (m²)302090850.3769Max camber position (c)402040Aspect Ratio Sweep (deg.) Aerofoil1025.84.725.8Table 3: Wing Parametric DataMach Number0.50.82Table 4: Aircraft Cruise PerformanceSubsonic/TransonicSupersonicAngle of Attack (deg.)01.52IFocusVoice

Given: Incompressible Cp and Cl values for subsonic and transonic airfoils at M=0.2 To find:…

1. Find the compressible Cp_min and lift coefficient for the subsonic and transonic aerofoils using the data provided in Tables 1, 2 and 4. Use 2 compressibility corrections of your choice; which one is more accurate and why?

1. Find the compressible Cp_min and lift coefficient for the subsonic and transonic aerofoils using the data provided in Tables 1, 2 and 4. Use 2 compressibility corrections of your choice; which one is more accurate and why?

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

Can you please attempt question 1 please.

2.
1. Find the compressible Cp_min and lift coefficient for the subsonic and transonic aerofoils using
the data provided in Tables 1, 2 and 4. Use 2 compressibility corrections of your choice; which
one is more accurate and why?
Determine the critical Mach number and the drag-divergence Mach number for the subsonic
and transonic aerofoils, using any method you prefer. Compare the values between the two
aerofoils and explain whether the transonic aerofoil is better than the subsonic one and why.

Font
Aerofoil
NACA 2412
NACA 34011
Supersonic
Wing
Assessment Information/Brief
Paragraph
Aerofoil
Subsonic aerofoil
Subsonic/Transonic
Supersonic
t/c (%)
12
11
6
Speed Regime
Subsonic
Transonic
Supersonic
-0.7
Transonic aerofoil -0.98
Max t/c position (c) Max camber (%c)
29
2
29
39
3
3
Table 1: Aerofoil information
Incompressible min Cp Incompressible C₁ Analysis conditions
0.3857
M = 0.2, Re = 6000000,
AoA = 1
Styles
M-0.2, Re-6000000,
AoA=1
Table 2: Incompressible Low Speed Analysis Data:
Span (m) Area (m²)
30
20
90
85
0.3769
Max camber position (c)
40
20
40
Aspect Ratio Sweep (deg.) Aerofoil
10
25.8
4.7
25.8
Table 3: Wing Parametric Data
Mach Number
0.5
0.8
2
Table 4: Aircraft Cruise Performance
Subsonic/Transonic
Supersonic
Angle of Attack (deg.)
0
1.5
2
I
Focus
Voice

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