Using the given regarding airframe and airfoil in questions 1-9, I need help with filling the chart out for question 10 and identifying the information to answer the remaining questions.  

 

 

1 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): Pilata PC-12
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):
NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il)
3. Aircraft Maximum Gross Weight [lbs] (from last week’s module): 10,450 lbs
4. Wing Span [ft] (from last week’s module): 53.3 ft
5. Average Chord Length [ft] (from last week’s module): 5.23 ft
6. Wing Area ‘S’ [ft2] (from last week’s module): 277.8 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.):10.19 ft
8. CLmax for your airfoil (from last week’s module): 1.9024
9. Standard sea level Stall Speed ‘Vs’ for your aircraft [kts] (from last week’s calculation): 76.38
kts
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 . This document was developed for online learning in ASCI 309.
File name: Ex_4_Drag&Applications
Updated: 07/11/2015 2
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). How to find the
minimum Cd
10. From the polar plot, find the CDmin value for your airfoil, i.e. the lowest value that the
coefficient of drag ‘Cd’ (bottom scale in the online tool depiction) reaches. (Tip: for a numerical
breakdown of the plotted curve, you can again select the “Details” link and directly read the
lowest CD value in the table – third column, labeled “CD”):
What we’ve just found (…with some degree of simplification…) is the parasite drag coefficient
for our airfoil, i.e. the drag that exists due to skin friction and the shape of our airfoil, even
when little or no lift is produced. However, this value will only represent the airfoil, i.e. main
wing portion of our aircraft; therefore, let us for the remainder of our calculations assume
that our aircraft is a Flying Wing type design and the total CDP for the aircraft is the same
as the CDmin that we’ve just found.
Let us also assume that we are at standard sea level atmospheric conditions and that our
wing has an efficiency factor of e = 0.82.
A. Prepare and complete the following table for your aircraft (with the data from 1. through 8.
above). Start your first row with the Stall Speed ‘V s’ (from 7. above) and start the second row
from the top with the next higher full twenty knots above that stall speed. Then increase speed
with every subsequent row by another 20 knots until reaching 300 kts. You are again
encouraged to utilize MS® Excel as shown in the tutorial video and can also increase your table
detail. However, the below depicted, and above described, interval is the minimum required for
this assignment. This document was developed for online learning in ASCI 309.
File name: Ex_4_Drag&Applications
Updated: 07/11/2015 3 V
(KTAS) q
(psf) CL CDP CDI CD CL / CD DP
(lb) DI
(lb) DT
(lb) VS
60
80
100
120
140
160
180
200
220
240
260
280
300
Equations for Table: W CDi =[1/ (πeAR)] CL 2 q= CL = CD = CDP + CDi CD = CDP + [1/ ( e AR)] CL 2 qS Di = CDi q S = [1/ ( e AR)] CL2 q S Dp = CDp q S Dt = Di + Dp = CD q S Answer the following questions from your table.
I) Determine the minimum total drag ‘Dmin’ [lbs] (i.e. the minimum value in the total drag
‘DT’ column):
II) Determine the airspeed at which this minimum drag occurs ‘V Dmin’ [kts] (i.e. the
speed associated with the row in which ‘Dmin’ was found):
III) Compare parasitic ‘DP’ and induced ‘DI’ drag at VDmin. What is special about this point
in your table? This document was developed for online learning in ASCI 309.
File name: Ex_4_Drag&Applications
Updated: 07/11/2015 4 IV) Determine the maximum CL/CD value in your table (i.e. the maximum value in the
CL/CD column) and the speed at which it occurs.
V) Compare your results in IV) with II) and comment on your findings. and VI) Explain which values in your table will directly allow glide performance prediction
how (Tip: Reference again the textbook discussion pp. 61-63). B. If the gross weight of your aircraft is decreased by 10% (e.g. due to fuel burn), how would
the stall speed change? Support you answer with calculation as well as written assessment.
(Remember, stall speed references and discussions can be found pp. 43-45 in your textbook.) For the second part of this assignment use the given figure below (Figure 1.13 from
Aerodynamics for Naval Aviators [1965]) to answer the following questions. (This
assignment is designed to review some of the diagram reading skills required for your
midterm exam; therefore, please make sure to fully understand all the diagram
information and review book, lecture, and/or tutorials if necessary.): Figure 1.13 from Aerodynamics for Naval Aviators (1965).
C. What is the Angle of Attack at Stall for the aircraft in Figure 1.13?
This document was developed for online learning in ASCI 309.
File name: Ex_4_Drag&Applications
Updated: 07/11/2015 5 D. What Angle of Attack is associated with Best L/D?
E. What would be the best Glide Ratio for this aircraft?
F. What is the maximum coefficient of lift (CLmax) value? This document was developed for online learning in ASCI 309.
File name: Ex_4_Drag&Applications
Updated: 07/11/2015