AS 309- Aerodynamics Final Project
AS 309- Aerodynamics Final Project 1
AS 309- Aerodynamics Final Project
You have been hired to assist the director of operations for a large and very well-known flight school. The director of operations has asked you to analyze aerodynamics and performance data of the Cessna 172 S NAV III Skyhawk in order to buy 45 new aircraft to replace their old fleet. You are to calculate the information and present a report of your findings to the Director of Operations of the organization.
The Project will consist of two parts:
I. Answers to the aerodynamics and performance questions in Canvas quiz (80% of Grade) II. Technical report (minimum of 3 pages, not including the cover page) to the company Director of
Operations to describe the following: (20% of Grade)
a. cover page that includes the names of each group member, the class title and number, and semester and year.
b. A brief description of the aircraft
c. Answers to report questions (20 questions total) in grey boxes at the bottom of each section.
d. Peer/self-evaluation form
Because of the limitations of Canvas, each individual person must submit answers and documents
online. If you fail to submit the assignment, you will receive a zero. All parts need to be submitted
(report and numerical answers), in order to receive a grade for the final project. Failure to submit one
of these elements, will result in a zero on the final project
AS 309- Aerodynamics Final Project 2
1. Lift
Questions to be answered in Canvas quiz:
Utilizing the aircraft information provided in Appendix A, calculate the following:
@ 2550 lbs
1. Vs1-Stall speed no flaps (in knots) @ 2550 lbs
2. Vr (in knots) @ 2550 lbs
3. Vs2 – Stall Speed with full flaps (in knots) @ 2550 lbs
4. Vref (in knots) @ 2550 lbs
5. CL (coefficient of lift)@ 115 kts @ 2550 lbs
6. What is the angle of attack for zero lift? (make sure to indicate + or – sign)
@2200 lbs
7. Vs1-Stall speed no flaps (in knots) @ 2200 lbs
8. Vr (in knots) @ 2200 lbs
9. Vs2 – Stall Speed with full flaps (in knots) @ 2200 lbs
10. Vref (in knots) @ 2200 lbs
11. CL @ 115 kts@ 2200 lbs
@ 2100 lbs
12. Vs1-Stall speed no flaps (in knots) @ 2100 lbs
13. Vr (in knots) @ 2100 lbs
14. Vs2 – Stall Speed with full flaps (in knots) @ 2100 lbs
15. Vref (in knots) @ 2100 lbs
16. CL @ 115 kts @ 2100 lbs
Questions to be answered in Report:
1. In the report include a description of how stall speed, rotation speed and approach speed
change with weight and how the values obtained above compared to the book values in the
C-172 Owner’s Manual (see Appendix B)
AS 309- Aerodynamics Final Project 3
2. Drag
Questions to be answered in Canvas quiz:
Utilizing the aircraft information provided in Appendix A, calculate the following (Use Appendix A1 and A2 for the best L/D speed questions!)
1. Wing Di @2550lbs & 100 kts
2. Wing Dp @2550lbs & 100 kts
3. Wing Dtotal @2550lbs & 100 kts
4. Best L/D speed @2550lbs
5. Wing Di @ 2100lbs &100 kts
6. Wing Dp @ 2100lb & 100 kts
7. Wing Dtotal @ 2100lbs & 100 kts
8. Best L/D speed @ 2100lbs
Questions to be answered in Report:
2. In the report make a table to explain which of the following factors will affect which kind of drag (induced or parasite)
1. load factor 2. air density 3. wing area 4. weight 5. air speed 6. wing span 7. aspect ratio
AS 309- Aerodynamics Final Project 4
3. Lift to Drag Ratio
Questions to be answered in Canvas quiz:
Utilizing the aircraft information provided in Appendix C, determine the following:
9. Velocity for minimum sink in knots @ 2,550 lbs
10. Value for minimum sink in ft/min @ 2,550 lbs
11. Velocity for best L/D in knots @ 2,550 lbs
12. Value for best L/D @ 2,550 lbs
13. Velocity for minimum sink in knots @ 2,100 lbs
14. Value for minimum sink in feet/min @2,100 lbs
15. Velocity for best L/D in knots @ 2,100 lbs
16. Value for best L/D in knots @ 2,100 lbs
Questions to be answered in Report:
In the Report:
3. The wing drag data calculated in section 2 are based on theoretical data for wing drag only. The
lift to drag ratio information in Appendix C is based on flight test data and calculations based on the
drag and power of the entire aircraft. Explain whether the best L/D speeds are different in
questions 4,8; 11 and 15. If so explain why are they different and compare values for the C-172 in
Appendix C based on experimental data.
4. Explain how L/D, sink rate and L/D change or don’t change with weight. Include graphs in the
report.
AS 309- Aerodynamics Final Project 5
4. Power and Thrust
Questions to be answered in Canvas quiz:
Utilizing the aircraft information provided in Appendix D, determine the following:
1. Max level airspeed in knots
2. Best range speed in knots
3. Best endurance speed in knots
4. Vx in knots
5. Vy in knots
6. Value in feet per minute for best rate of climb
Questions to be answered in Report:
In the Report: 5. Include the following:
a. Power v. Velocity graph b. Thrust v. velocity graph c. ROC v. velocity graph d. Indicate where the maximum level flight speed is, Vx, Vy, Best L/D, best range and
best endurance in graphs.
5. Slow flight, stalls, spins
Questions to be answered in Canvas quiz:
1. The C-172 has a lot of twist/washout on the wings
2. Twist or washout is designed to maintain the ailerons less stalled when the aircraft has exceeded critical angle of attack
3. The C-172 has a wing that is nearly
4. In a slip the stall speed is:
5. In a skid the stall speed is:
6. In a skid the inclinometer or ball will be
AS 309- Aerodynamics Final Project 6
7. In a slip the position of the flight controls will be
8. In a skid the position of the flight controls will be
Questions to be answered in Report:
In the Report: 6. What can you say about the lift distribution on the wing in the C-172 (What part will stall first,
does the wing have twist or washout?)
7. What is the spin recovery procedure for the C-172?
8. Why is the spin recovery order important?
9. What are the differences between a slip and a skid (position of the flight controls, inclinometer,
stall speed)?
1. Vg Diagram
Questions to be answered in Canvas quiz:
Utilizing the aircraft information provided in Appendix E, determine the following:
1. What is Vs or stall speed at 1G without flaps and maximum gross weight of 2,550 lbs (KIAS) for the C-172 2. Vs or stall speed at 2G without flaps and maximum gross weight of 2,550 lbs (KIAS) 3. Vs or stall speed at 3G without flaps and maximum gross weight of 2,550 lbs (KIAS) 4. Vs or stall speed at 1G without flaps and weight of 2,100 lbs (KIAS) 5. Va or maneuvering speed at 2550 (KIAS) 6. Va or maneuvering speed at 2100 (KIAS) 7. Vs or stall speed at 1G with flaps and weight of 2,100 lbs (KIAS)
Questions to be answered in Report:
In the Report:
10. Draw a VG diagram for the C-172 at 2,500lbs
11. Calculate Va and Vs at 2,100 lbs and draw the VG diagram at 2,100 lbs
12. Explain what airspeeds change and what airspeeds do not change with weight. Make sure to
include vs, Va, Vne and Vno.
13. Explain what Va is and how it changes with weight
AS 309- Aerodynamics Final Project 7
6.Stability and control
Questions to be answered in Canvas quiz:
A pilot performs a landing roll in a tailwheel airplane with no crosswind correction. There is a
strong cross wind. Neglecting engine effects please fill in the following blanks:
The airplane will start to yaw _____________________ (away from, into) the wind due to
______________ (dihedral effect, weather vane stability, scuff effect). This turn is due to lack of
proper __________________ (elevator, rudder, aileron) control. As a result, the airplane will be
on the _________________ (upwind, downwind) side of the centerline. The proper placement
of the ailerons would be _____________(towards the centerline, away from the centerline, into
the wind, downwind). The airplane will tend to roll__________________ (away from, into) the
relative wind. The effect that can further aggravate this yawing situation is
__________________ (dihedral effect, adverse yaw, spiraling slipstream)
The worst thing that can be done in this situation is to apply ________________ (downwind,
into the wind) ailerons.
Questions to be answered in Report:
In the Report:
14. What kind of longitudinal static stability would you expect a C-172 to have? Positive/negative –
explain
15. What kind of longitudinal dynamic stability would you expect a C-172 to have?
Positive/negative - explain
16. Where would the CG be located in relationship with the neutral point?
17. What will provide dihedral effect to C-172 Explain in report
18. How does a PIO occur?
19. How does a ground loop occur?
20. What would happen if the pilot takes off with the CG aft of the aft CG limit. Explain
AS 309- Aerodynamics Final Project 8
Appendix A1
Airplane Information Length: 27 ft Wingspan: 36 ft Wing area: 174 sq ft CLmax no flaps: 1.22 CLmax full flaps: 1.7 Max Gross Weight 2,550 lbs Standard density: 0.002377 Airfoil: modified NACA 2412 n=1 e (Oswald’s Efficiency number) =0.8 K-factor= 0.030049 Cdo=0.01
AS 309- Aerodynamics Final Project 9
Appendix A2
Wing Drag @ 2,500 lbs
Airspeed (kts)
Induced Drag (lbs)
Parasite Drag (lbs)
Total Drag (lbs)
40 198.40 9.45 207.85 45 156.76 11.96 168.72 50 126.98 14.76 141.74 55 104.94 17.86 122.81 60 88.181 21.26 109.44 65 75.136 24.95 100.09 70 64.78 28.94 93.72 75 56.43 33.22 89.65 80 49.60 37.80 87.40 85 43.93 43.67 86.61 90 39.193 47.84 87.03 95 35.17 53.30 88.47 100 31.74 59.06 90.80 105 28.79 65.11 93.91 110 26.23 71.46 97.70 115 24.00 78.11 102.11 120 22.04 85.05 107.09 125 20.31 92.28 112.60 130 18.78 99.81 118.60 135 17.41 107.64 125.06 140 16.19 115.76 131.96 145 15.09 124.18 139.28 150 14.10 132.89 147.00 155 13.21 141.90 155.11 160 12.40 151.20 163.60
0
100
200
300
400
500
0 50 100 150 200 250
D ra
g
Airspeed
Drag vs Airspeed
Induced
Parasite
Total
AS 309- Aerodynamics Final Project 10
Appendix A3
Wing Drag @ 2,100 lbs
Airspeed (kts)
Induced Drag (lbs)
Parasit e Drag (lbs)
Total Drag (lbs)
40 139.99 9.45 149.44 45 110.61 11.96 122.57 50 89.59 14.76 104.36 55 74.04 17.86 91.91 60 62.22 21.26 83.48 65 53.01 24.95 77.97 70 45.71 28.94 74.65 75 39.82 33.22 73.04 78 36.81 35.93 72.75 80 34.99 37.80 72.80 85 31.00 42.67 73.67 90 27.65 47.84 75.49 100 22.39 59.06 81.46 105 20.31 65.11 85.43 110 18.51 71.46 89.97 115 16.93 78.11 95.04 120 15.55 85.05 100.60 121 15.29 86.47 101.77 125 14.33 92.28 106.62 130 13.25 99.81 113.07 135 12.29 107.64 119.93 140 11.42 115.76 127.19 145 10.65 124.18 134.83 150 9.95 132.89 142.84 155 9.32 141.90 151.22 160 8.74 151.20 159.95
0 100 200 300 400 500
-50 50 150 250
D ra
g
Airspeed
Drag vs Airspeed
Induced
Parasite
Total
AS 309- Aerodynamics Final Project 11
Appendix B
Stall Speed Information from Cessna Manual
AS 309- Aerodynamics Final Project 12
Appendix C
Sink rate v. Velocity
Figure 1. Sink rate v. Velocity
e 0.8 hp 180 rho 2.38E-03 cdo 0.05 eta 0.75 weight 2550
weight 2100
Vkts Vfps e ta Thrus t Dra g @ 2550 R/C L/D @ 2550 Si nk Ra te @
2550l bs i n ft/mi n a ngl e dra g a t 2100 L/D a t 2100 s i nk ra te a t
2100l bs i n ft/mi n
40 67.55556 0.6 879.2763 415.3281576 737.4653 6.139723381 654.4352051 9.235286 296.8605858 7.074027677 569.216446 45 76 0.62 807.6316 350.5980078 817.2836 7.273287192 623.0454482 7.815395 256.9940004 8.171396984 555.2830533 50 84.44444 0.64 750.3158 309.3400224 876.1871 8.243356228 611.6477183 6.905181 233.5207764 8.992775857 561.109978 55 92.88889 0.65 692.7632 283.932203 893.5495 8.981017204 618.0224858 6.342862 221.2716691 9.490595919 585.0890804 60 101.3333 0.67 654.5724 269.7890305 917.4442 9.451829806 640.877551 6.029309 217.1367764 9.671323463 626.4365345 65 109.7778 0.68 613.2389 264.01756 902.0409 9.658448474 679.5378237 5.90125 219.1541009 9.582298445 684.8993846 70 118.2222 0.71 594.5583 264.7195273 917.5122 9.632836784 733.7418612 5.916828 226.0362385 9.290545683 760.5719823 75 126.6667 0.72 562.7368 270.6074829 870.6601 9.423242745 803.5091644 6.047464 236.9100402 8.864124111 853.7788947 80 135.1111 0.73 534.8931 280.783265 807.8367 9.081737831 889.0523104 6.273083 251.166372 8.360991891 964.9979586 85 143.5556 0.74 510.3251 294.6048384 728.655 8.655662322 990.7173955 6.579222 268.3698052 7.825023378 1094.807934 90 152 0.75 488.4868 311.6033969 632.6184 8.183479467 1108.942539 6.95521 288.202395 7.28654597 1243.851518
100 168.8889 0.75 439.6382 353.8212956 341.0239 7.207028044 1397.114534 7.886344 334.8664841 6.271156117 1602.373072 110 185.7778 0.75 399.6711 405.5314616 -25.6173 6.288044803 1757.954502 9.021082 389.8663282 5.386461585 2046.090988 120 202.6667 0.75 366.3651 465.5875152 -473.155 5.476950985 2196.02392 10.32998 452.4244517 4.641658938 2580.314148 130 219.5556 0.75 338.1832 533.2662201 -1007.8 4.781851735 2715.722898 11.79195 522.0503553 4.022600461 3209.765095
-3500
-3000
-2500
-2000
-1500
-1000
-500
0 0 20 40 60 80 100 120 140
S in
k ra
te
V(kts)
sink rate
2100 lbs 2550 lbs
AS 309- Aerodynamics Final Project 13
Appendix D
Power Available & Power Required
Figure 2. Power Available & Power Required v. Velocity
e 0.8 hp 180 rho 2.38E-03 cdo 0.05 eta 0.75 weight 2550
weight 2100
Vkts Vfps
eta (Propeller Efficiency)
Thrust (lbs) Drag (lbs)
RoC (ft/min) L/D
Sink Rate in ft/min
angle of climb in degrees
drag at 2100 in lbs
L/D at 2100
sink rate at 2100
Excess Thrust in
LBS
Power Required
in HP Power Available in
HP
Excess Power in
HP 40 67.55556 0.75 1099.095 415.3282 1086.877 6.139723 654.4352 9.235286 296.8605858 7.074028 569.2164 683.7672 51.11731 135.2732794 84.15597 45 76 0.75 976.9737 350.598 1120.107 7.273287 623.0454 7.815395 256.9940004 8.171397 555.2831 626.3757 48.54434 135.2732794 86.72894 50 84.44444 0.75 879.2763 309.34 1132.422 8.243356 611.6477 6.905181 233.5207764 8.992776 561.11 569.9363 47.59077 135.2732794 87.68251 55 92.88889 0.75 799.3421 283.9322 1126.491 8.981017 618.0225 6.342862 221.2716691 9.490596 585.0891 515.4099 48.05007 135.2732794 87.22321 60 101.3333 0.75 732.7303 269.789 1103.797 9.45183 640.8776 6.029309 217.1367764 9.671323 626.4365 462.9412 49.80721 135.2732794 85.46607 65 109.7778 0.75 676.3664 264.0176 1065.1 9.658448 679.5378 5.90125 219.1541009 9.582298 684.8994 412.3488 52.80351 135.2732794 82.46977 70 118.2222 0.75 628.0545 264.7195 1010.689 9.632837 733.7419 5.916828 226.0362385 9.290546 760.572 363.335 57.01651 135.2732794 78.25677 75 126.6667 0.75 586.1842 270.6075 940.5424 9.423243 803.5092 6.047464 236.9100402 8.864124 853.7789 315.5767 62.44788 135.2732794 72.8254 80 135.1111 0.75 549.5477 280.7833 854.425 9.081738 889.0523 6.273083 251.166372 8.360992 964.998 268.7644 69.11588 135.2732794 66.1574 85 143.5556 0.75 517.2214 294.6048 751.9491 8.655662 990.7174 6.579222 268.3698052 7.825023 1094.808 222.6165 77.0505 135.2732794 58.22278 90 152 0.75 488.4868 311.6034 632.6184 8.183479 1108.943 6.95521 288.202395 7.286546 1243.852 176.8834 86.29017 135.2732794 48.98311
100 168.8889 0.75 439.6382 353.8213 341.0239 7.207028 1397.115 7.886344 334.8664841 6.271156 1602.373 85.81686 108.8681 135.2732794 26.40519 110 185.7778 0.75 399.6711 405.5315 -25.6173 6.288045 1757.955 9.021082 389.8663282 5.386462 2046.091 -5.86041 137.2568 135.2732794 -1.98352 120 202.6667 0.75 366.3651 465.5875 -473.155 5.476951 2196.024 10.32998 452.4244517 4.641659 2580.314 -99.2224 171.9092 135.2732794 -36.636 130 219.5556 0.75 338.1832 533.2662 -1007.8 4.781852 2715.723 11.79195 522.0503553 4.0226 3209.765 -195.083 213.3065 135.2732794 -78.0332
0
50
100
150
200
250
0 20 40 60 80 100 120 140
Power Available v. Power Required
Power Required in HP Power Available in HP V(TAS) in kts
Po w
er A
va ila
bl e
& P
ow er
R eq
ui re
d in
L bs
AS 309- Aerodynamics Final Project 14
Appendix D (Continued)
Thrust & Drag
Figure3. Thrust & Drag v. Velocity
Figure 4. Rate of Climb v. Velocity
0
200
400
600
800
1000
1200
0 20 40 60 80 100 120 140
Thrust and Drag
Thrust (lbs) Drag (lbs)
-1500
-1000
-500
0
500
1000
1500
0 20 40 60 80 100 120 140
RoC (ft/min)
RO C
(F t/
M in
)
V(TAS) in kts
V(TAS) in kts
Th ru
st a
nd D
ra g
in L
bs
AS 309- Aerodynamics Final Project 15
Appendix E
C-172 Envelope Information from Cessna Manual