Given: Ref: Gulfstream G450 Altitude = 8000 feet stp MSL S=950 ft; span = 77.9 ft...

Transcribed Image Text:

Given: Ref: Gulfstream G450 Altitude = 8000 feet stp MSL S=950 ft; span = 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 V = 510 KTAS; ne mach) Glide distance = 34.5 nm from 20,000 ft AGL V = 340 ktas (.88 a Note: KCAS=KEAS = KTAS at low Mach numbers at Sea Level. Use S for standard day at 8000'. Required: Items 1-7 work for sea level and MTOGW of 73900 lbs Part I 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. e, Oswald efficiency factor (also referred to as the wing efficiency factor) 7. f, flat plate drag area Item 8-10 accomplish for sea level and 8000 feet msl. 8. Calculate and plot Di, Dp, and Dtot vs. V (table of values and graph) for Vstall @ full flaps (sea level) through the following airspeeds: V = 110, 160, 210, 270, 300, 320, 350, 400, 420, 450 KTAS. Note: Adjust the sea level airspeeds for 8,000 ft. when plotting the total drag curve for that altitude. Choose "X-Y Scatter" graph for graphing. 9. Show sample calculations for item 8 at one velocity other than Vglide Part II 10. Using the results from #8, create the thrust required curves for this aircraft. 11. List the speeds where the G-450 would achieve the following performance: (At Sea Level) a. Maximum engine out glide range. b. Maximum endurance. c. Maximum no-wind range d. Minimum thrust required Given: Ref: Gulfstream G450 Altitude = 8000 feet stp MSL S=950 ft; span = 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 V = 510 KTAS; ne mach) Glide distance = 34.5 nm from 20,000 ft AGL V = 340 ktas (.88 a Note: KCAS=KEAS = KTAS at low Mach numbers at Sea Level. Use S for standard day at 8000'. Required: Items 1-7 work for sea level and MTOGW of 73900 lbs Part I 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. e, Oswald efficiency factor (also referred to as the wing efficiency factor) 7. f, flat plate drag area Item 8-10 accomplish for sea level and 8000 feet msl. 8. Calculate and plot Di, Dp, and Dtot vs. V (table of values and graph) for Vstall @ full flaps (sea level) through the following airspeeds: V = 110, 160, 210, 270, 300, 320, 350, 400, 420, 450 KTAS. Note: Adjust the sea level airspeeds for 8,000 ft. when plotting the total drag curve for that altitude. Choose "X-Y Scatter" graph for graphing. 9. Show sample calculations for item 8 at one velocity other than Vglide Part II 10. Using the results from #8, create the thrust required curves for this aircraft. 11. List the speeds where the G-450 would achieve the following performance: (At Sea Level) a. Maximum engine out glide range. b. Maximum endurance. c. Maximum no-wind range d. Minimum thrust required