Then, working with your derived thrust-required and/or power-required curves and table data,explain how to findvarious performance aspects for your aircraft,and provide the specific datafor your example. At a minimum cover the following:

• Maximum range airspeed
• Maximum endurance airspeed
• Best climb conditions
  • Best rate of climb (ROC) & associated airspeed
  • Best angle of climb (AOC) & associated airspeed
• Maximum forward airspeed
• Best glide airspeed

Additionally, discussand highlight numerically a specific example of how weight change influences performance events such as the best range or endurance.

As in previous assignments, you will need to research additional information such as required formulas and pertinent aircraft data. Again, the emphasis in this project task is on explaining your methodology as if you are attempting to instruct someone unfamiliar with the aerodynamic details and relationships. Therefore, make sure to detail all assumptions, all formulas used, and all steps that were taken.The following will give you some starting points for your search and consideration.

1. Required formula
   • Thrust to power relationship
   • Weight change influence on performance airspeeds
   • ROC & AOC relationships
2. Necessary aircraft information:
   • Powerplant output (for simplification, you can assume constant power output at the rated value across the entire speed range);whatever powerplant data you utilize, please make sure toinclude a short discussiondetailing your assumptions.
3. Previous information:
   • Make sure to detail again all assumedinformation used/transferred from last week (e.g., aircraft weight, atmospheric conditions, etc.) since performance data are, obviously, only valid for specific cases and conditions.

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Slide 20- so what is the airspeed? What does max range mean? Slide 21- what is max endurance? explain it. What is the airspeed? Slide 23- How far will your aircraft glide in miles from 10,000' ?

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Using/building on your previous drag (i.e., thrust-required) table and graph created in Module 3, generate additional power-required values in the table and depict the power-required curve for your aircraft. Note- This is POWER not THRUST because it is a propellor aircraft- Read the Lecture for this module on how to derive Power Required- USE THEACTUAL HORSEPOWEROF YOUR AIRCRAFT FOR POWER AVAILABLE!(this will be at all altitudes and speeds knowing this is not really the way it is, but will make your work easier to do).

Then, working with your derived power-required curves and table data, explainhow to findvarious performance aspects for your aircraft,and provide thespecific datafor your example. At a minimum cover the following:

Maximum range airspeed

Maximum endurance airspeed

Best climb conditions

Best rate of climb (ROC) & associated airspeed

Best angle of climb (AOC) & associated airspeed

Maximum forward airspeed

Best glide airspeed

Additionally, discussand highlight numerically on aspecific example how weight change influences performance events such as best range or endurance. (Numerically means to use a formula with actual numbers in it to prove you point IE at a wt of ...Best range is....and at a wt of.... Best range is ....).

Cessna 172 Unaccelerated Performance . Maximum range airspeed can be found with the equations Horsepower Required 300.00 below (Dole, 2017): Specific Range (SR) = Speed (knots) 250.00 Fuel Flow (hr) SRmax = V (Speed) FF (Fuel Flow ) max OR at: (FF (Fuel Flow v (Speed) min 200.00 The above equation essentially expresses that maximum 150.00 specific range is achieved at maximum airspeed for the minimum amount of fuel consumption. 100.00 . On a power required curve, a straight line drawn from the origin and tangent to the curve will indicate the maximum 50.00 specific-range velocity. On power producing aircraft, this is the L/D max point (Dole, 2017) 0.00 50.7 65 80 95 110 125 140 155 170 185Cessna 172 Unaccelerated Performance . Endurance can be described as such: Fuel available (1b) Example HP req'd vs Velocity Chart (Dole, 2017) Endurance = Fuel Flow (hr) (hrs) Maximizing endurance means the maximum amount of time the aircraft 2000 + 4000 can be airborne and is independent of distance covered. Therefore, PROP AIRPLANE DATA minimizing fuel flow is essential. Since fuel flow is proportional to WEIGHT 20,000 lbs power, minimizing fuel flow = minimizing power to the minimum WING AREA (S) 500 ft2 SEA LEVEL DENSITY o = 1 amount required (Dole, 2017). 1500+ 3000 . Maximum Endurance is mathematically equal to Cj / CD (max), also known as the minimum power required point (Dole, 2017). MAX ENDURANCE 3/2 FF min ~ HPR min ~ DV min . .C CL ) max 1000 2000 HORSEPOWER REQUIRED HORSEPOWER REQUIRED (HPR) MAX ENDURANCE V q= a x CL= CDI=[1/ CD= CL^(3/2)/C Dp=CDp Di = Cdi Dt = q s Di + P[HP]-(T[Ibs]"V[kts])/32 500+ : 1000 3/2 (KTAS) VA21295 Wigs (IeAR)] CDP COP+CDI CL/CD (Ib/ft^2) D q s CL^2 (ib) (ib ) CL) Dp max RANGE MAX (lb) ()min = (HPP) min 50.7 8.72 1.58 0. 126 0.021 0.15 10.76 13.54 31.86 191.1 223.0 34.79 (DV) min . : ()max 65 14.32 0.96 0.047 0.021 0.07 14.23 13.96 52.33 116.3 168.7 33.73 FUEL FLOW-(Ibs/hr) 100 200 300 80 21.69 0.64 0.020 0.021 0.04 15.38 12.26 79.27 76.8 156.1 38.42 VELOCITY-(KNOTS) 95 30.59 0.45 0.010 0.021 0.03 14.44 9.69 111.79 54.5 166.3 48.60 110 41.02 0.34 0.006 0.021 0.03 12.60 7.31 149.88 40.6 190.5 64.48Cessna 172 Unaccelerated Performance q- d x V (KTAS) V*2/295 CL- CDI-[1/ (TreAR)] CDp CD- CL/CD Dp CDp q s Pi = Cdig S Dt = Di + P[HP]-(T[Ibs] (Ib/ft^2) W/qS CL^2 CDP+CDI (1b) (lb) DP *V[kts])/325 50.7 8.72 1.58 0.126 0.021 0.15 10.76 31.86 191.1 223.0 34.79 Maximum Forward Airspeed 65 14.32 0.96 0.047 0.021 0.07 14.23 52.33 116.3 168.7 33.73 . Unaccelerated maximum velocity 80 21.69 0.64 0.020 0.021 0.04 15.38 79.27 76.8 156.1 38.42 will occur at the intersection of full 95 30.59 0.45 0.010 0.021 0.03 14.44 111.79 54.5 166.3 48.60 110 41.02 0.34 0.006 0.021 0.03 12.60 149.88 40.6 190.5 64.48 power available, and power required 125 52.97 0.26 0.003 0.021 0.02 10.67 193.54 31.5 225.0 86.54 (Dole, 2017). 140 66.44 0.21 0.002 0.021 0.02 242.77 25.1 267.9 115.38 As the Cessna 172's maximum 155 81.44 0.17 0.001 0.021 0.02 7.55 297.58 20.5 318.0 151.68 engine output is 160hp, we can 170 97.97 0.14 0.001 0.021 0.02 6.40 357.97 17.0 375.0 196.14 conclude that max forward airspeed 185 116.02 0.12 0.001 0.021 0.02 5.48 423.93 14.4 438.3 249.49 is just over 155 KTAS. Airspeed vs. Drag Best Glide Speed 500.00 450.00 .Best glide speed is obtained at (L/D). 400.00 The aircraft will travel the furthest 350.00 distance for the lift produced at this 300.00 Dra 250.00 point (FAA, 2018). According to our 200.00 drag table, this value is obtained at 150.00 approximately 80 KTAS. 100.00 50.00 0.00 50.7 65 80 95 110 125 140 155 170 185 Airspeed -Parasite Drag -Induced Drag -Total Drag