At a minimum cover the following aspects:

• Positive and negative limiting load factor (i.e., the maximum G allowed for your aircraft)
• Stall speeds at 1, 2, 3, and so on G up to the maximum positive G (at your selected weight)
• Ultimate load factor (ULF)
• Positive ultimate load (i.e., the actual force [lbs]) at the selected weight
• Maneuvering speed
• The bank angle associated with the positive limiting load factor
• Rate and radius formula
• The turn performance diagram (Figure 2.29 in Aerodynamics for Naval Aviators, Hurt, 1965, p.179 or the Constant altitude turn performance diagram/figure in the textbook for in Chapter 11)

As in previous assignments, you will need to research a variety of additional information such as required formulas andpertinent aircraft data and/or assume a few parameters for your aircraft. Please make sure to detail those:

1. Required Formulas:
   • Bank angle to G relationship
   • Turn rate and radius
   • Stall speed under elevated G / bank
2. Necessary aircraft information:
   • Limiting load factors (positive and negative) for your example aircraft (from research)
   • Assumed aircraft weight
3. Previous information:
   • Utilize your previous module work to find 1G stall speedfor your selected weight
   • Assume atmospheric conditions

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*At a minimum cover the following aspects:

*Positive and negative limiting load factor (i.e., the maximum G allowed for your aircraft)

*Stall speeds at 1, 2, 3, and so on G up to the maximum positive G (at your selected weight)

*Ultimate load factor (ULF)

*Positive ultimate load (i.e., the actual force [lbs]) at the selected weight

*Maneuvering speed

*The bank angle associated with the positive limiting load factor

* For the specific maneuvering speedof your aircraft identified above,explain how to numerically find (provide thespecific example and values) the associated turn rate and radius utilizing both of the following methods:

*Rate and radius formula-So one slide is where you use the formula to determine Rate and Radius using the formulas-

*The next slide you will use the following turn performance diagram to determine Rate and Radius-show your work.

*Theturn performance diagram(Figure 2.29 in Aerodynamics for Naval Aviators, Hurt, 1965, p. 179 or Figure 13.14, Dole et al., 2017, p. 239)

*The bank angle associated with the positive limiting load factor

* As in previous assignments, you will need to research a variety of additional information such as required formulas andpertinent aircraft data and/or assume a few parameters for your aircraft. Please make sure to detail those:

*Required Formulas

*Bank angle to G relationship

*Turn rate and radius

*Stall speed under elevated G / bank

*Necessary aircraft information:

*Limiting load factors (positive and negative) for your example aircraft (from research)

*Assumed aircraft weight

*Previous information:

*Utilize your previous module work to find 1G stall speedfor your selected weight

*Assume atmospheric conditions-

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How do you use this chart?

What is the formula to find maneuvering speed and what is that speed?

You needed to provide the answers

Maneuvering Performance Structural Damage Bank angle associated with positive limit load factor 120 1.6 140 1.6 156, 3.4 100, 5.8 We can find the bank angle associated with the positive Accelerated Stall limit loadfactor (3.8G) using the following formula (Dole, 0711487504. 5 2017) . =(G)=0=74.74 degrees 7170062761, 2 Va Structural At 74.74 degrees angle of bank, we will need to induce 171 Damage +3.8G load factor to maintain level flight. The aircraft will or Failure either need to start descending beyond this AOB or exceed 158,0 the positive load factor limit, risking structural damage. 120 1:40 180 Rate and radius calculation via formulas (Dole. 2017) Accelerated Stall Rate of Turn $41. -1 158 -1 52 70, -1.52 50, -152 110, -1.52 130,-1.52 150,-1.52 ROT= = bank angle. ) is given airspeed Structural Damage At a 30 degree bank at 100 knots; ROT= =6.3 degrees per second Radius 1 =. For a 30 degree bank at 100 knots: 1 = = 1538 ft radius Centrifugal force - 1.73 Gs Load Incler Q unital 10 20" 3 40 60' 60' 70' 80 8 Bank anga Figure 6-62. Two forces case load factor daring Awnis. Figure 9-43, Angle of bank clampes load factor in level flickr.Maneuvering Performance 5 120 3.8 140, 3.8 158, 3.8 VG Diagram/ data table of our C172 100, 3.8 Calculations were conducted from values in the table, 87.81497594, 3 standard atmospheric conditions N 71.70062761, 2 Flight load factor limits: +3.8G, -1.52G (per POH) VNE (Never exceed speed) = 158 KIAS 50.7, 1 Calculations (Dole, 2017) = stall speed under 1G (50.7 KTAS) 158, 0 20 40 60 80 100 120 140 160 180 - stall speed under other than 1G flight -1 G- load factor To solve for : 56.2, -1 158, -1.52 . rearrange the above equation to: = 70, -1.52 90, -1.52 110, -1.52 130, -1.52 150, -1.52 -2 KTAS for 2G load factor VG Diagram For +3.8G: W 2400 G+ 3.8 S 185 G- -1.52 Clmax 1.58 Clmin 1.29 VS 50.7 V- S 56.2 Vne 158 G 2 3.8 3.8 3.8 3.8 3.8 V 50.7 71.70063 87.81498 98.83249 100 120 140 158 G -1 -1.52 -1.52 -1.52 -1.52 -1.52 -1.52 -1.52