This document provides an overview of the geometry, mission requirements, and performance of the Infinity II aircraft. Key points include: - The aircraft will provide aerial reconnaissance over the Galapagos Islands with a 7-hour endurance at 100+ knots and 10,000 foot ceiling. - A canard configuration was selected for its maneuverability and stability. Computational fluid dynamics analysis showed the canard provides downwash without interfering with the wing. - Preliminary analysis found the aircraft meets all mission requirements with a maximum takeoff weight of 1320 pounds. An 8-hour endurance was calculated. - Stability and control analysis showed the aircraft has positive stability margins in cruise and stall conditions

4. A Brief Overview

6. GEOMETRY

11. Mission Requirements
 Provide aerial reconnaissance in support of anti-
poaching efforts in the Galapagos islands
 Establish 50 Mile TV link
 7 hour endurance at cruise, 30 minutes to and
from target
 Max cruise > 100 knots
 Service ceiling of 10,000 feet
 Meet LSA requirements

12. LSA Requirements
 Maximum gross take off weight < 1320 lb
 Maximum airspeed in level flight < 120 KCAS
 Maximum stall speed < 45 knots
 1-2 front seats
 Fixed undercarriage
 Fixed pitch or ground adjustable propeller
 Single engine
 Fixed landing gear
 Unpressurized cabin

13. A Common Belief…about canards
 Relatively uncommon
 Unstable and unsafe
 John Denver
 Obviously inefficient

14. Canard Configuration
 Highly efficient – Rutan’s Model 76 Voyager
 9 days, 3 minutes, 44 seconds around the world
flight
 Properly designed configuration is safe
 FAA approved

15. Advantages
 Inherent instability adds maneuverability
 Very good stalling characteristics
 CL,MAX of a canard may exceed that of aft-tail
 Control authority greater at large α than aft-tail

16. Wing
AR = 7.15 Ctw = 2.30 ft
Sw = 120 sq-ft Wing Sweep at c/4 = 23 degrees
Bw = 29.24 ft Anhedral = 4.5 degrees Fuel Tanks
Crw = 7.24 ft Washout = 8 degrees*

17. Canard
AR = 9.60
Sw = 25.2 sq-ft
Bw = 15.5 ft
Crw = 2.23 ft
Canard Incidence Angle= 3 degrees

18. Vertical Tails a.k.a Winglets
AR = 2.65
Sw = 9.12 sq-ft
Bw = 4.92 ft
} Per Tail
Sweep added to
Increase the tail arm
Lht = 8.24 ft

19. Moments and Forces
LTotal = LW –
LH
Airflow

20. Moments and Forces
LTotal = LH + LW
Airflow

21. Engine and Propeller
 Rotax 912 S
 4 cylinder
 2.4 in stroke
 100 HP
 125 lb
 NEUFORM CR3-65-47-
101,6
 Carbon fiber
 65” diameter
 11.2 lb

22. Camera System
HIGH-PERFORMANCE MULTI-SENSOR THERMAL IMAGING SYSTEM
FLIR TALON
• System Weight: 50lb
• System Type: 6-axis gyro-stabilized multi-senso
• Thermal Imaging Zoom Ratio: 10x optical
• Daytime Imaging Zoom Ratio: 18x optical
• Field of View: 50⁰
• Camera Location: Fwd, Bottom of Fuselage

23. PERFORMANCE

24. Flight envelope
30000
25000
Vmin
20000
Altitude (Feet)
Vmax
15000 V LD max
V ROC
10000 max
Vrange
5000
0
40 50 60 70 80 90 100 110 120
Velocity (KCAS)

26. Preliminary CG Envelope
1400
1200
1000
Weight, lbf
800
600
400
200
0
-40% -35% -30% -25% -20% -15% -10% -5% 0% 5% 10%
CG Location, %MGC

27. Ground Roll
 Weight at Condition = 1320 lbs
 Vliftoff = 84.2 ft/s
 Ground Run = 437.5 ft
 Rotation Distance = 84.2 ft
 Ground Roll = 521.6 ft

28. Endurance
 8.25 Hour Endurance
 Velocity for L/DMAX is 64
knots

29. Balked Landing Test Results
 V = 54 KCAS
 Angle of Attack = 7.17 °
 AIL Defl = .0088°
 ELV Defl = 5.73 °
 RDR Defl = -.0211 °

30. Absolute Ceiling
 Absolute Ceiling: 23,645 ft
 Service Ceiling: 21,403 ft

31. 290 mi
325 mi

32. Climb, Cruise and Descent
 Max Level Airspeed: 105KCAS
 Best Endurance Speed: 49KCAS
 Best Range Speed: 84 KCAS
 Best Glide Speed: 64 KCAS

33. • Max ROC of 1085 fpm
• 72 knots

35. COMPUTATIONAL FLUID DYNAMICS (CFD)

36. Canard Airfoil – GOE 390

37. Canard downwash
DIMENSIONS

38. Canard downwash

39. Vortex streamlines

40. Wing Airfoil – FX-62-k-153/20 2
0.25
1.5
0.2
Coefficient of Drag
Coefficient of Lift
0.15 1
0.1
0.5
0.05
0
0
11
-10
-7
-4
-1
-8.5
-5.5
-2.5
14
8
0.5
2
3.5
5
6.5
9.5
12.5
-0.5 0 0.5 1 1.5 2
Coefficient of Lift Re 100000 -0.5
Re 300000 Angle of Attack in Degrees
Re 500000
Re 100000
Re 300000
Re 500000

41. Canard Airfoil – GOE 390
3
0.25
2.5
Coefficient of Drag
0.2
Coefficient of Lift
2
0.15
1.5
0.1 1
0.05 0.5
0
0
20
14
17
23
2
5
8
11
-10
-7
-4
-1
-1 0 1 2 3
-0.5
Coefficient of Lift
Re 100000 Angle of Attack in Degrees
Re 300000
Re 500000 Re 100000
Re 300000
Re 500000

42. Canard Placement
Canard and wing on same plane
Weaker vortices seen by the wing
Canard
Canard lower than the wing Wing

43. Drag Analysis

44. Drag Results
 Drag build-up method: 340 drag counts
 Surfaces: 400 drag counts*
 Mainly because of high washout. New design with
less washout is being considered for the final iteration.

45. Stability and Control

46. Longitudinal – SM Envelopes
CASES
AOA ELV de SM
CRUISE (100 KCAS)
1 PAX + 250 lb FUEL
-0.5112 -3.1702 9.35 %
2 PAX + 0 lb FUEL
0.3196 -2.3394 15.71 %
STALL (45 KCAS)
1 PAX + 250 lb FUEL 14.7057 3.9569 9.75 %
2 PAX + 0 lb FUEL 12.9563 10.5454 16.44 %

47. Stability Derivatives
 Cma = -0.551 per rad
 Cnb = 0.104 per rad
 Clb = -0.079 per rad
Roll Rate: 174 degrees/second

48. Lift Distribution
Lift Distribution at 45 KCAS at Stall

49. Lift Distribution
Lift Distribution at 84 KCAS at Cruise

50. 45 Knots
Converges at
2.5 seconds

51. 100 Knots
Converges at
1.5 seconds

52. 45 Knots
Converges at
20 seconds

53. 100 Knots
Converges in
60 seconds

54. 45 Knots
Diverges after
200 seconds

55. 100 Knots
Diverges at
100 seconds

56. 45 Knots
Converges in
1.1 seconds

57. 100 Knots
Converges in
0.5 seconds

58. 45 Knots
Converges at
20 seconds

59. 100 Knots
Converges at
8 seconds

60. Conclusion
Infinity II meets all the requirements of the mission.
An ideal candidate for multi-purpose use.
Future Steps
Reduce the washout and increase overall efficiency. In
detail study of stall characteristics of the wings and the
canard.

61. Thank You. Any Questions?