Bf 109K-4 vs P-51D Mustang
Bf 109K-4 Statistics:
Engine: Daimler Benz DB-605D with MW-50 boost.
Power: 2,000 HP.
Max. Speed: 727 km/h. (452 mph.)
Max. Climb: 1,470 m/min (4,823 ft/min.)
Empty Weight: 2,673 kg. (5,298 lbs.)
Loaded Weight *Clean*: 3,148 kg. (6,940 lbs.)
Max. Weight: 3,373 kg. (7,438 lbs.)
Wing-Span: 9.97 m. (32.7 ft.)
Wing-Area: 16.4 sq.m. (176.6 sq.ft.)
Armament: 2x 13mm HMG's (MG 131) 1x 30mm cannon (MK 108).
Bf 109K-4 Aerodynamic statistics:
Wing-loading *Loaded*: 191.9 kg/sq.m. (39.2 lbs/sq.ft.)
Wing Aspect-Ratio: 6.06 .
Airfoil: NACA 2R1 14.2 - 2R1 11.35.
Airfoil Thickness Ratio: Root= 14.2% Tip= 11.35%.
Wing CL-max *Freeflow*: 1.48 . (No slats or flaps deployed)
Lift-loading *Loaded*: 129.69 kg/sq.m. (26.5 lbs/sq.ft.)
Power-loading *Loaded*: 1.57 kg/hp. (3.47 lbs/hp.)
Bf 109K-4 Additional features:
-Automatic-Slats Flettner-Tabs.
-Inclined seat position for better G-load resistance Friese ailerons.
P-51D Mustang Statistics:
Engine: Packard Merlin V-1650-7.
Power: 1,720 HP.
Max.Speed: 703 km/h (437mph).
Max. Climb: 1,060 m/min. (3,478 ft/min)
Empty Weight: 3,175 kg. (7,000 lbs.)
Loaded Weight *Clean*: 4,286 kg. (9,449 lbs.)
Max. Weight: 5,487 kg. (12,096 lbs.)
Wing-Span: 11.3 m. (37.07 ft.)
Wing-Area: 21.83 sq.m. (233 sq.ft.)
Armament: 6x .50 cal HMG's (M2).
P-51D Mustang Aerodynamic statistics:
Wing-Loading *Loaded*: 196.33 kg/sq.m. (40.5 lbs/sq.ft.)
Wing Aspect-Ratio: 5.81 .
Airfoil: "Laminar" NAA/NACA 45-100 - NAA/NACA 45-100.
Airfoil Thickness Ratio: Root= 14.8 or 15% Tip= 12%.
Wing CL-max *Freeflow*: 1.28 . (No flaps deployed)
Lift-loading *Loaded*: 153.38 kg/sq.m. (31.6 lbs/sq.ft.)
Power-loading *Loaded*: 2.49 kg/hp. ( 5.49 lbs/hp.)
P-51D Mustang Additional features:
-Laminar wing Tear-shaped canopy.
-Gyro-Gunsight.
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Aerodynamic Facts:
Airfoil Thickness Ratio - Higher is better.
Wing CL-max - Higher is better.
Wing Aspect Ratio - Higher is better.
Lift-loading - Lower is better.
Power-loading - Lower is better.
Automatic leading edge slats info:
Slats extend up the range of AoA where the airflow stays attached to the wing. Without slats a wing would stall at a certain AoA, the airflow turning turbulent at the same moment with a sudden enormous increase in drag. With slats the airflow stays non-turbulent for some extra amount of AoA, and there will not be any "stepped" increase in drag when the slats deploy, only at the point where even the slats cannot prevent the wing entering a stall. The automatic-slats work at all speeds, and significantly increase the stall angle and CL-max of the airfoil.
Illustration: http://history.nasa.gov/SP-367/fig63.jpg
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.
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Wing Cl-max were obtained from:
Bf-109: from full scale Windtunnel test in Charlais Meudan.
P-51: from Naca Report 829, Page 26 in the PDF of the Naca Report server.
Bf 109K-4 Statistics:
Engine: Daimler Benz DB-605D with MW-50 boost.
Power: 2,000 HP.
Max. Speed: 727 km/h. (452 mph.)
Max. Climb: 1,470 m/min (4,823 ft/min.)
Empty Weight: 2,673 kg. (5,298 lbs.)
Loaded Weight *Clean*: 3,148 kg. (6,940 lbs.)
Max. Weight: 3,373 kg. (7,438 lbs.)
Wing-Span: 9.97 m. (32.7 ft.)
Wing-Area: 16.4 sq.m. (176.6 sq.ft.)
Armament: 2x 13mm HMG's (MG 131) 1x 30mm cannon (MK 108).
Bf 109K-4 Aerodynamic statistics:
Wing-loading *Loaded*: 191.9 kg/sq.m. (39.2 lbs/sq.ft.)
Wing Aspect-Ratio: 6.06 .
Airfoil: NACA 2R1 14.2 - 2R1 11.35.
Airfoil Thickness Ratio: Root= 14.2% Tip= 11.35%.
Wing CL-max *Freeflow*: 1.48 . (No slats or flaps deployed)
Lift-loading *Loaded*: 129.69 kg/sq.m. (26.5 lbs/sq.ft.)
Power-loading *Loaded*: 1.57 kg/hp. (3.47 lbs/hp.)
Bf 109K-4 Additional features:
-Automatic-Slats Flettner-Tabs.
-Inclined seat position for better G-load resistance Friese ailerons.
P-51D Mustang Statistics:
Engine: Packard Merlin V-1650-7.
Power: 1,720 HP.
Max.Speed: 703 km/h (437mph).
Max. Climb: 1,060 m/min. (3,478 ft/min)
Empty Weight: 3,175 kg. (7,000 lbs.)
Loaded Weight *Clean*: 4,286 kg. (9,449 lbs.)
Max. Weight: 5,487 kg. (12,096 lbs.)
Wing-Span: 11.3 m. (37.07 ft.)
Wing-Area: 21.83 sq.m. (233 sq.ft.)
Armament: 6x .50 cal HMG's (M2).
P-51D Mustang Aerodynamic statistics:
Wing-Loading *Loaded*: 196.33 kg/sq.m. (40.5 lbs/sq.ft.)
Wing Aspect-Ratio: 5.81 .
Airfoil: "Laminar" NAA/NACA 45-100 - NAA/NACA 45-100.
Airfoil Thickness Ratio: Root= 14.8 or 15% Tip= 12%.
Wing CL-max *Freeflow*: 1.28 . (No flaps deployed)
Lift-loading *Loaded*: 153.38 kg/sq.m. (31.6 lbs/sq.ft.)
Power-loading *Loaded*: 2.49 kg/hp. ( 5.49 lbs/hp.)
P-51D Mustang Additional features:
-Laminar wing Tear-shaped canopy.
-Gyro-Gunsight.
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Aerodynamic Facts:
Airfoil Thickness Ratio - Higher is better.
Wing CL-max - Higher is better.
Wing Aspect Ratio - Higher is better.
Lift-loading - Lower is better.
Power-loading - Lower is better.
Automatic leading edge slats info:
Slats extend up the range of AoA where the airflow stays attached to the wing. Without slats a wing would stall at a certain AoA, the airflow turning turbulent at the same moment with a sudden enormous increase in drag. With slats the airflow stays non-turbulent for some extra amount of AoA, and there will not be any "stepped" increase in drag when the slats deploy, only at the point where even the slats cannot prevent the wing entering a stall. The automatic-slats work at all speeds, and significantly increase the stall angle and CL-max of the airfoil.
Illustration: http://history.nasa.gov/SP-367/fig63.jpg
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 Cl-max were obtained from:
Bf-109: from full scale Windtunnel test in Charlais Meudan.
P-51: from Naca Report 829, Page 26 in the PDF of the Naca Report server.