Cessna 172 Drag AS-310 Gulfstream 450 Drag Assignment Due Dates: 13 April 2020 (Section 3) 14 April 2020 (Sections 1 & 2) Part 1 of this project is designed to provide you with the confidence to...

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Cessna 172 Drag AS-310 Gulfstream 450 Drag Assignment Due Dates: 13 April 2020 (Section 3) 14 April 2020 (Sections 1 & 2) Part 1 of this project is designed to provide you with the confidence to manipulate relationships of drag, velocities, and the methodology involved that would be used for determining the total drag plots for a typical Corporate Aircraft. Part 2 consists of simple estimates of Specific Range & Endurance. As an option, you may collaborate in teams of 2 from the same Section both of whom will receive the identical grade; if exercised be sure to list both Team Members on the cover sheet. Grading shall be based upon the objective accuracy of calculations and subjective clarity of submissions at the sole discretion of the evaluating Professor. Deliver electronically via CANVAS NLT 1500 on the date due. Keep copy of your work. Given: Ref: Gulfstream G450 Altitude = 8000 feet msl Standard Day S = 950 ft2; b = 77.9 ft Max Takeoff Gross Wt = 73,900 lbs @ Sea Level: Vstall = 110 KTAS flaps up = 100 KTAS @ 60 deg flaps Best glide speed, flaps up: Vglide = 160 KTAS at W = 73,900 lbs Vne = 510 KTAS; Glide distance = 34.5 nm from 20,000 ft AGL Va= 340 KTAS (.88 Mach) Fuel Consumption 568gals/hr Jet A @ 420 KTAS Note: KCAS = KEAS = KTAS at low Mach numbers at Sea Level. Use ( for standard day at 8000’. Part 1: Items 1-7 work for sea level and MTOGW of 73,900lbs 1. Glide ratio = (L/D)max 2. Minimum drag, Dmin 3. Dp, Di, and q for V = Vglide = 160 KTAS 4. CDpmin 5. AR 6. Flat plate drag area (f) Part 2: Specific Range 7. Estimate Specific Range on a trip of 600nm at 420 KTAS. 8. Estimate Specific Endurance if Fuel Flow/hr = 75% of Fuel Flow in 420 KTAS Cruise PAGE 1