4. The Wright brothers used a very thin wing on their 1903 flyer. In addition, they made extensive use of a homebuilt wind tunnel to test their wing designs. span, b chord, c Model of Wright Flyer (a) The Wright's wind-tunnel models had chord length, c, of about 0.04 m and wing span (length) of 0.26 m. The wind tunnel operated at approximately the same wind speed as the full-scale aircraft - about 13 m/s. Estimate the drag (friction) of a single wind-tunnel model wing under standard conditions (= 1.225 kg/m³, = 1.7894 x 10-³ kg/s-m). Note that the wing is mounted in the wind tunnel so that both upper and lower surfaces are exposed to the flow. (b) The full-scale 1903 flyer had a chord length of 1.9 m and a wing span of 12.3 m. Estimate the drag (friction) of a single full-scale Wright flyer wing flying at 13 m/s under standard atmospheric conditions. (e) Consider the main wing configuration, which consisted of two wing surfaces (biplane) connected by 18¹ cylindrical rods. We will neglect the cross-bracing cables for this problem. Each rod is 1.8 m long and has diameter 3 cm. Estimate the viscous drag of the full main wing flying at 13 m/s under standard atmospheric conditions. The following drag coefficient table may be useful for completing this problem.
4. The Wright brothers used a very thin wing on their 1903 flyer. In addition, they made extensive use of a homebuilt wind tunnel to test their wing designs. span, b chord, c Model of Wright Flyer (a) The Wright's wind-tunnel models had chord length, c, of about 0.04 m and wing span (length) of 0.26 m. The wind tunnel operated at approximately the same wind speed as the full-scale aircraft - about 13 m/s. Estimate the drag (friction) of a single wind-tunnel model wing under standard conditions (= 1.225 kg/m³, = 1.7894 x 10-³ kg/s-m). Note that the wing is mounted in the wind tunnel so that both upper and lower surfaces are exposed to the flow. (b) The full-scale 1903 flyer had a chord length of 1.9 m and a wing span of 12.3 m. Estimate the drag (friction) of a single full-scale Wright flyer wing flying at 13 m/s under standard atmospheric conditions. (e) Consider the main wing configuration, which consisted of two wing surfaces (biplane) connected by 18¹ cylindrical rods. We will neglect the cross-bracing cables for this problem. Each rod is 1.8 m long and has diameter 3 cm. Estimate the viscous drag of the full main wing flying at 13 m/s under standard atmospheric conditions. The following drag coefficient table may be useful for completing this problem.
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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Transcribed Image Text:Elliptical cylinder:
1:1
2:1
4:1
8:1
Laminar
1.2
0.6
0.35
0.25
Drag coefficients for long cylinders.
Turbulent
0.3
0.2
0.15
0.1
Transcribed Image Text:4. The Wright brothers used a very thin wing on their 1903 flyer. In addition, they made extensive use of a
homebuilt wind tunnel to test their wing designs.
span, b
chord, c
Model of Wright Flyer
(a) The Wright's wind-tunnel models had chord length, c, of about 0.04 m and wing span (length) of 0.26 m.
The wind tunnel operated at approximately the same wind speed as the full-scale aircraft - about 13 m/s.
Estimate the drag (friction) of a single wind-tunnel model wing under standard conditions (o = 1.225
kg/m³, = 1.7894 x 10-³ kg/s-m). Note that the wing is mounted in the wind tunnel so that both
upper and lower surfaces are exposed to the flow.
(b) The full-scale 1903 flyer had a chord length of 1.9 m and a wing span of 12.3 m. Estimate the drag
(friction) of a single full-scale Wright flyer wing flying at 13 m/s under standard atmospheric conditions.
(c) Consider the main wing configuration, which consisted of two wing surfaces (biplane) connected by 18¹
cylindrical rods. We will neglect the cross-bracing cables for this problem. Each rod is 1.8 m long and
has diameter 3 cm. Estimate the viscous drag of the full main wing flying at 13 m/s under standard
atmospheric conditions. The following drag coefficient table may be useful for completing this problem.
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