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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

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
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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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)
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