Ta 152H-1 vs P-51H Focke Wulf Ta 152H-1 
Ta 152H-1 Statistics:
Empty weight: 4,031 kg
Fully loaded weight: Escort Mission = 5,220 kg - Fighter Mission = 4,750 kg
Maximum loaded weight: 5,220 kg
Internal fuel capacity: 594 L B4 and 85 L GM-1 in the fuselage, 400 + 115 L B4 and 70 L MW-50 in the wings - Total = 1,109 L B4 + 85 L GM-1 + 70 L MW-50
Ta 152H-1 Dimensions:
Wing span: 14.44 m
Wing area: 23.3 m
2
Lenght: 10.71 m
Height: 4 m
Ta 152H-1 Aerodynamics:
Wing loading: 224 - 203 kg/sq.m
Span loading: 361 - 328 kg/m
Wing aspect ratio: 8.94
Wing profile: Root = NACA FW 23015.3 or xxx20.6 - Tip = NACA FW 23009
Wing thickness ratio: Root 15.3% - 20.6% - Tip = 9%
Power loading: 2.54 - 2.31 kg/hp
Ta 152H-1 Performance: Max speeds:
- 598 km/h at sea level using MW-50
- 749 km/h at 9,500 m using MW-50
- 760 km/h at 12,500 m using GM-1 (MAX)
Note: These speeds were superceded in combat as engine performance apparently was better with the Ta152H's in service compared to the test-bed(s).
Climb rates and time:
- 20m/s at Start u. Notlesitung = 1,730 HP @ 3,250 RPM
- ~26m/s at Sonder Notleistung = 2,050 HP @ 3,250 RPM
- 10.1 min to climb 10,000 m using MW-50
Service ceiling: 14,800 - 15,100m
Jumo 213E performance:
- 1,580 HP @ 3,000 RPM = Steig u. Kampfleistung
- 1,730 HP @ 3,250 RPM = Start u. Notleistung
- 2,050 HP @ 3,250 RPM = Sonder Notleistung
Ta 152H-1 Armament:
1x 30mm MK108 cannon and 2x 20mm MG151/20 cannons
Ta 152H-1 Service record::
Service entering date: 27th January 1945
Losses to aerial combat: 0
Losses to accidents: 3 (two of them occured in combat)
Confirmed kills in aerial combat: 11
North American P-51H Mustang 
P-51H Statistics:
Empty weight: 3,193 kg
Loaded weight: Escort Mission = 5,216 kg - Fighter Mission = 4,310 kg
Maximum loaded weight: 5,216 kg
Internal fuel capacity: 965 L of 100/150 grade fuel.
P-51H Dimension:
Wing span: 11.27 m
Wing area: 21.64 m
2
Length: 10.15 m
Height: 4.16 m
P-51H Aerodynamics:
Wing loading: 241 - 199.1 kg/sq.m
Span loading: 462 - 382.4 kg/m
Wing aspect ratio: 5.86
Wing profile: Root = NACA 66-(1.8 )15.5 – Tip = NACA 66-(1.8 )12 “Laminar”
Wing thickness ratio: Root = 15.5% - Tip = 12%
Power-loading: 2.35 – 1.94 kg/hp
P-51H Performance: Max speeds:
- 714 km/h at 1,524 m using (W)WEP
- 745 km/h at 4,570 m using (W)WEP
- 783 km/h at 7,620 m using (W)WEP (MAX)
Climb rates and time:
- ~24-25 m/s at sea level using (W)WEP
- 1.5 min to climb 1,524 m using (W)WEP
- 5 min to climb 4,570 m using (W)WEP
Service ceiling: 12,679 m
Packard V-1650-9 performance:
- 1,380 HP @ 3,000 RPM = Take Off Power
- 1,720 HP @ 3,000 RPM = War Emergency Power
- 2,218 HP @ 3,000 RPM = Wet War Emergency Power
P-51H Armament:
6x 12.7mm machine-guns.
P-51H Service record:
Non WWII aircraft.
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Aerodynamic Facts:
Airfoil Thickness Ratio -
Higher is better.
Wing Aspect Ratio -
Higher is better.
Span-loading -
Lower is better.
Power-loading -
Lower is better. Laminar wing info:
Laminar flow wings lowered the drag, but this came at the cost of lower lift, especially under high G loads. A Laminar flow wing will stall earlier and more violently than a conventional wing.
Wing aspect ratio info:
There is a component of the drag of an aircraft called induced drag which depends inversely on the aspect ratio. A higher aspect ratio wing has a lower drag and a higher lift than a lower aspect ratio wing.
Span loading info:
The turning drag/lift factor is proportional to the span loading (W/b^2) at a given G loading and indicated airspeed (IAS). It is related to induced drag and is familiar to aerodynamicists. It is the dominant parameter in calculating sustained G. In air-combat turns, the induced drag at a given G level is directly proportional to the span loading.
Linear Mode
