Q2:A) What are the classifications of the NACA Aerofoil section? B) Select the appropriate NACA airfoil section for the wing, which will use for a civilian category airplane with the following characteristics: MTO=9500 kg, S = 40 m², Vc = 300 m/sec (at 9000m, p-0.4671 kg/m³), Vs = 20 m/sec (at sea level) The high lift device (plain flap) will provide act. -0.5 when deflected. Use the figure below for selecting if it fits, then, discuss your answer. Maximum lift coefficient (Cimer) 45,-018 65,-021 0000 1.5 64,015 64,013 16-01863,-01260,915 66,-021 64,-021 1.3 64,018 1 teas 66,012 0.7 1.3 0.9 0.8 0012 www 63,-015 54-218.653-2 43,018 2455,0. 24 1.1009 64-112 €5.000 164-019 0 1410 0006 66006 GADIO, GEAd10 900-19 0010-34 0010-35 44-110 +8612-45 1.066-09-19. 1408 63-210 95,-212 0.1 44-2184 64-209 63,-211 1412 63,315 0012-644-418 64,-21265215 64A-210 65-210 2410 64-A315 65-221 012-59253 439-409 65-209 0.2 66-206 23013 65-415 S 63,-415 21-211 23012 45-410 255-415 25-01 44,-418 64,-421 3476415 65-418 7476315 2421 33034 L(medin 166-17 64,-411 65,415 64,415 65,412 64M41 0.3 43-421 65,-431 63,318 63-309 64-210 DIEVED 66-211 66,-212 04412 0.4 4415 PELA 2418,2408 All dan at Re of 6x10, and no Dap deflection 4424 0.5 63-613 65,-618 64,-628 63,618 63-618 0.6

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
icon
Related questions
Question
Q2:A) What are the classifications of the NACA Aerofoil section?
B) Select the appropriate NACA airfoil section for the wing, which will use for a civilian
category airplane with the following characteristics:
mro = 9500 kg, S = 40 m², Vc=300 m/sec (at 9000m, p=0.4671 kg/m³), Vs = 20 m/sec
(at sea level) The high lift device (plain flap) will provide act = 0.5 when deflected.
Use the figure below for selecting if it fits, then, discuss your answer.
Maximum
lift
coefficient 1.7
(C)
45,-018
65,-021
0000
1.5
64, 0154
44,013
C6-01863,-01266,015
14
13
66,-021
64,-021
1.3
1.1
0.8
0.9
0.7
64,-231
63,-015 54.218.653-2181
43,018
1465,015
0012
1410
64--112
0
64-019
1.000.
64,018
$2009
€5.400
66,012
64ADIO, 64AS10
0006
66006
63-006
0010-34
0010-35
·8612-65
63,-218
44-110
1408
0.1
63,-212
46-2184
64-207
#1413
463,215 0012-64 6,-438
64,-211 $65215
63-210
65-410
65-210
2412
2415
64A-210
2410
65-221
221 65-210
60-431
64-A215
65-299
15:29
0.2
64-2
65-206
65365
66-206
23013
2424
6,418
63,-415
WIDE
21-214
23011
65-415
63,414
25-01
44,-418
64,-421
7476415 65,-418
63,-421
65,-431
7476315
2421
23024
65-17.
44-412
63,415
64,-415
64,-412
64A43
0.3
63,218
63-209
64-210
63A210
66-21
66,-212
04412
0.4
104435
14421
2418,2408
All data at He of 6x10, and no Dap deflection
4424
53,613
65,-618
64-628
963,-618
65-615
0.5
0.6
Ideal lift coefficient (C)
Transcribed Image Text:Q2:A) What are the classifications of the NACA Aerofoil section? B) Select the appropriate NACA airfoil section for the wing, which will use for a civilian category airplane with the following characteristics: mro = 9500 kg, S = 40 m², Vc=300 m/sec (at 9000m, p=0.4671 kg/m³), Vs = 20 m/sec (at sea level) The high lift device (plain flap) will provide act = 0.5 when deflected. Use the figure below for selecting if it fits, then, discuss your answer. Maximum lift coefficient 1.7 (C) 45,-018 65,-021 0000 1.5 64, 0154 44,013 C6-01863,-01266,015 14 13 66,-021 64,-021 1.3 1.1 0.8 0.9 0.7 64,-231 63,-015 54.218.653-2181 43,018 1465,015 0012 1410 64--112 0 64-019 1.000. 64,018 $2009 €5.400 66,012 64ADIO, 64AS10 0006 66006 63-006 0010-34 0010-35 ·8612-65 63,-218 44-110 1408 0.1 63,-212 46-2184 64-207 #1413 463,215 0012-64 6,-438 64,-211 $65215 63-210 65-410 65-210 2412 2415 64A-210 2410 65-221 221 65-210 60-431 64-A215 65-299 15:29 0.2 64-2 65-206 65365 66-206 23013 2424 6,418 63,-415 WIDE 21-214 23011 65-415 63,414 25-01 44,-418 64,-421 7476415 65,-418 63,-421 65,-431 7476315 2421 23024 65-17. 44-412 63,415 64,-415 64,-412 64A43 0.3 63,218 63-209 64-210 63A210 66-21 66,-212 04412 0.4 104435 14421 2418,2408 All data at He of 6x10, and no Dap deflection 4424 53,613 65,-618 64-628 963,-618 65-615 0.5 0.6 Ideal lift coefficient (C)
Expert Solution
steps

Step by step

Solved in 3 steps

Blurred answer
Knowledge Booster
Applied Fluid Mechanics
Learn more about
Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.
Similar questions
  • SEE MORE QUESTIONS
Recommended textbooks for you
Elements Of Electromagnetics
Elements Of Electromagnetics
Mechanical Engineering
ISBN:
9780190698614
Author:
Sadiku, Matthew N. O.
Publisher:
Oxford University Press
Mechanics of Materials (10th Edition)
Mechanics of Materials (10th Edition)
Mechanical Engineering
ISBN:
9780134319650
Author:
Russell C. Hibbeler
Publisher:
PEARSON
Thermodynamics: An Engineering Approach
Thermodynamics: An Engineering Approach
Mechanical Engineering
ISBN:
9781259822674
Author:
Yunus A. Cengel Dr., Michael A. Boles
Publisher:
McGraw-Hill Education
Control Systems Engineering
Control Systems Engineering
Mechanical Engineering
ISBN:
9781118170519
Author:
Norman S. Nise
Publisher:
WILEY
Mechanics of Materials (MindTap Course List)
Mechanics of Materials (MindTap Course List)
Mechanical Engineering
ISBN:
9781337093347
Author:
Barry J. Goodno, James M. Gere
Publisher:
Cengage Learning
Engineering Mechanics: Statics
Engineering Mechanics: Statics
Mechanical Engineering
ISBN:
9781118807330
Author:
James L. Meriam, L. G. Kraige, J. N. Bolton
Publisher:
WILEY