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Drag Exercise (Answer the questions on word file)
  • From Physics, General Physics
  • Due on 04 Oct, 2017 12:00:00
  • Asked On 03 Oct, 2017 12:43:50
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Complete the Drag Exercise with showing work. Need to be answered on the attached word file.

Make sure its own work and with showing work for the solution.

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Exercise 4: Drag and Applications
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  • Submitted On 03 Oct, 2017 03:26:54
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Exercise 4: Drag and Applications The first part of this week’s assignment is to revisit our reciprocating engine powered (i.e. propeller type) aircraft from last week. 1. Selected Aircraft (from last week’s module): Aero Commander 720 Shrike Make sure to review your data and results from last week and any feedback that you may have received on your work, in order to prevent continuing with faulty data. 2. Main Wing Airfoil type & on-line database designator (from last week’s module): NACA 23012 3. Aircraft Maximum Gross Weight [lbs] (from last week’s module): 6750 lbs 4. Wing Span [ft] (from last week’s module): 49 ft 1 in = 49 ft 5. Average Chord Length [ft] (from last week’s module): 5.2 ft 6. Wing Area ‘S’ [ft2] (from last week’s module): 255 ft^2 7. Find the Aspect Ratio ‘AR’ for your selected aircraft wing. (Use the wing span and average chord length from last week’s module/from above. See also page 63 in your textbook.): Span = 49 ft , average chord = 5.2 ft AR = span/average chord = 49 / 5.2 = 9.42 8. CLmax for your airfoil (from last week’s module): CLmax = 1.5413 AOA = 15.75 9. Standard sea level Stall Speed ‘Vs’ for your aircraft [kts] (from last week’s calculation): L = W = 6750 lbs Cl Max =1.5413 , =1 S =255 ft^2 V^2 = 295 * 6750 / 1.5413/ 255 V = 71.18 KTAS Find the appropriate drag polar curve for your airfoil selection (2. above; from last week’s module). You can utilize any officially published airfoil diagram for your selected airfoil or use again the Airfoil Tool at http://airfoiltools.com/search . Concentrate for this exercise on the Cl/Cd (coefficient of lift vs coefficient of drag) plot, i.e. the so called drag polar. Use again only the curve for the highest Reynolds-number (Re) selected (i.e. remove all checkmarks, except the second to last, and press the “Update plots” tab). 10. From the polar plot, find the CDmin value for your airfoil, i.e. the lowest value ...
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Drag Exercise Answer file)
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  • Submitted On 04 Oct, 2017 10:55:50
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Please find the attached file, In one...
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Drag Exercise (Answer the questions on word file)
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  • Submitted On 04 Oct, 2017 04:13:56
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Complete the Drag Exercise with showing...
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