Technical Assessment: He 1078 A
Own History: Heinkel P 1078 A 3D-Printed Model Kit
Technical Assessment Report
The Heinkel He 1078 A (P 1078 mit Leitwerk)
1. Project Genesis and Strategic Context
The development of the Heinkel He 1078 A was dictated by the terminal strategic realities of the European theater. The "extraordinary shortage of oil production" documented in internal summaries necessitated a radical departure from the resource-intensive, twin-engine configurations typified by the Messerschmitt Me 262. To sustain defensive operations, the Ernst Heinkel Aktiengesellschaft prioritized the "Jagdeinsitzer" (single-seat fighter) concept—a light, fuel-efficient interceptor optimized for rapid production.
A critical design constraint was the lack of small-diameter jet engines with efficiencies comparable to the Heinkel-Hirth HeS 11. Consequently, the airframe was built specifically around this single, high-thrust powerplant to achieve the necessary performance within a compact frame. This report evaluates the technical profile of the "A" variant (mit Leitwerk or "with tail") as of September 1945. It synthesizes engineering data from the Landsberg (Lech) office (14 September 1945) and the subsequent design critiques provided by Prof. Heinkel (22 September 1945).
2. Physical Dimensions and Airframe Architecture
The He 1078 A was designed with a streamlined, compact structural layout intended for superior mass-production efficiency compared to the earlier He 162. The design leveraged a high-speed aerodynamic profile centered on a 40-degree swept-wing configuration.
| Specification | Measurement |
|---|---|
| Spanweite (Wingspan) | 8.8 m |
| Länge (Length) | 9.5 m |
| Höhe (Height) | 3.1 m |
| Flügelfläche (Wing Area) | 16.85 m² |
| Pfeilung (Sweep) | 40° |
| Flächenbelastung (Wing Loading) | 240 kg/m² |
| Leistungsbelastung (Power Loading) | 3.12 kg/kp |
Central to the aerodynamic profile was the "Flügelknick" (wing crank). While intended to influence "Schieberollmomente" (roll-due-to-yaw moments) and lateral stability, Prof. Heinkel’s analysis suggests the crank introduced unnecessary manufacturing complexity and static weight penalties.
Historical Precision in 3D
Our model captures the distinct 40° sweep and the "Flügelknick" discussed in Prof. Heinkel's original Landsberg reports.
Explore the Shop3. Propulsion System: The HeS 11 Turbojet
The He 1078 A was powered by a single Heinkel-Hirth HeS 11 turbojet. The decision to utilize a single-engine layout was a strategic maneuver to maximize maneuverability and high-altitude agility, as the HeS 11 offered a superior power-to-weight ratio for a light airframe.
HeS 11 Performance Data:
- Standschub (Static Thrust): 1300 kg
- Thrust at 11 km altitude (900 km/h): 445 kg
- Specific Fuel Consumption: 1.82 kg/kp.h (SL) to 1.435 kg/kp.h (11 km)
The "Einlaufkanal" (intake duct) design was uniquely advantageous for airframe integration. Because the engine diameter was significantly larger than the intake duct itself, the internal layout was "besonders günstig" (particularly favorable), as it provided the necessary volume for the landing gear to retract into the space adjacent to the duct. This efficiency allowed for a narrower fuselage without sacrificing the structural integrity of the landing gear housing.
4. Weight Distribution and Armament
Militärische Last (Total 700 kg)
- Waffen (2 x 30 mm MK 108) 180 kg
- Munition 85 kg
- Panzerung (Armor) 100 kg
- Ausrüstung (Radio/Inst.) 135 kg
- Reserve 100 kg
- Besatzung (Pilot) 100 kg
Operating Weights
- Leergewicht (Empty) 2150 kg
- Abfluggewicht (Take-off) 4050 kg
- Landegewicht (20% Fuel) 3090 kg
5. Comprehensive Performance Evaluation
| Metric | 0 km (Sea Level) | 6 km | 11 km |
|---|---|---|---|
| Max Speed | 980 km/h | 955 km/h | 890 km/h |
| Climb Rate (max) | 26.3 m/sec | 16.8 m/sec | 6.7 m/sec |
| Range (Full Throttle) | 580 km | 930 km | 1500 km |
Steigzeit to 6 km 5.8 min
Steigzeit to 11 km 16.1 min
Dienstgipfelhöhe 12.9 km
Startstrecke (Normal) 790 m
Startstrecke (Rockets) 390 m
Landegeschwindigkeit 160 km/h
6. Design Critique and Pilot Considerations
In his critique dated 22 September 1945, Prof. Heinkel preferred the single-engine P 1078 over the Me 262, specifically citing the design’s "greater maneuverability" and "superior roll rate." However, he identified several critical areas requiring remediation:
Visibility Issues (B variant)
Heinkel noted a "bad view" (schlechte Sicht) due to the "excentrische Sitzen" (eccentric/off-center seating position). The pilot's view was particularly obstructed to one side, an ergonomic failure that Heinkel warned would cause pilot "Unsicherheit" (uncertainty) during combat.
Landing Hazards
To mitigate the risk of engine damage during gear-up landings, Heinkel insisted on a "Sicherung für Bauchlandung" (Belly landing protection). He recommended reinforcing the fuselage underside with "Längsprofilen" (longitudinal profiles) to act as skids.
7. Final Technical Summary
The Heinkel He 1078 A represents a sophisticated evolutionary step in interceptor design, maximizing the output of the HeS 11 turbojet within a streamlined, mass-producible airframe. Its performance metrics—specifically its climb rate and high-altitude range—suggest it would have been a highly capable defensive asset.
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Order Now| P 1078 Jagdeinsitzer mit Strahltriebwerk HeS 11 |
|||
|---|---|---|---|
| Abmessungen: | Aerodynamische Fläche (40° gepfeilt) Spannweite Streckung |
||
| m² | mit Leitwerk | ohne Schwanz | |
| 18,65 | 20,3 | ||
| m | 8,5 | 9,4 | |
| 3,85 | 4,355 | ||
| Triebwerk: | 1 × HeS 11 Standschub Schub in 0 km Höhe bei 900 km/h Verbrauch Schub in 11 km Höhe bei 900 km/h Verbrauch |
||
| kg | kg | ||
| 1300 | 1300 | ||
| 1055 | 1055 | ||
| 445 | 445 | ||
| 445 | 445 | ||
| Gewichte: | Waffen (2 x 30 mm Kanonen) Munition Panzerung Ausrüstung (o. Waffen u. Panzerung) Reserve (f. zusätzl. Ausrüstung) Besetzung |
||
| Militärische Last | |||
| kg | 700 | 700 | |
| Flugwerk | kg | 1200 | 1200 |
| Triebwerk mit Behälter | kg | 900 | 900 |
| Kraftstoff | kg | 1200 | 1200 |
| Abfluggewicht | kg | 4050 | 3900 |
| Landgewicht (20% Betriebsstoff) | kg | 3450 | 3300 |
| Flugleistungen: | |||
| Höchstgeschwindigkeit (mittel) | km/h | 980 | 950 |
| in 6 km | km/h | 885 | 875 |
| in 11 km | km/h | 870 | 850 |
| Flugdauer (Vollgas) (mittel) | h | 0,6 | 0,6 |
| in 6 km | h | 1,0 | 1,0 |
| in 11 km | h | 1,75 | 1,75 |
| Steigzeit nach Start auf 6 km | min | 5,8 | 5,0 |
| auf 11 km | min | 16,1 | 12,6 |
| Steiggeschwindigkeit (mittel) | m/sec | 26,3 | 29,8 |
| in 6 km | m/sec | 19,5 | 21,8 |
| in 11 km | m/sec | 10,5 | 13,5 |
| Dienstgipfelhöhe (mittel 1 m/sec Steigen) | km | 12,9 | 13,7 |
| Rollweg | m | 790 | 730 |
| Rollweg mit Startraketen (1000 kg Schub) | m | 390 | 360 |
| Landegewschwindigkeit (e.g. 1,5/1,25) | km/h | 160 | 155 |
Data table from original source.
| Heinkel P 1078 | P 1078 A | P 1078 B |
|---|---|---|
| Verwendungszweck | Jagdeinsitzer | Jagdeinsitzer |
| Besatzung | 1 Mann | 1 Mann |
| Triebwerk | 1 × He S 11 | 1 × He S 11 |
| Leistung: Standschub | 1 × 1300 kp | 1 × 1300 kp |
| Schub in 0 m Höhe bei 900 km/h | 1035 kp | 1035 kp |
| Treibstoffverbrauch | 1,82 kg/kp·h | 1,82 kg/kp·h |
| Spannweite | 8,8 m | 9,4 m |
| Länge | 9,5 m | 6,1 m |
| Höhe | 3,0 m | 3,0 m |
| Flügelfläche | 16,85 m² | 20,3 m² |
| Flächenbelastung | 240 kg/m² | 192 kg/m² |
| Leistungsbelastung | 3,12 kg/kp | 3,12 kg/kp |
| Leergewicht | 2000 kg | 2000 kg |
| Kraftstoff | 1200 kg | 1200 kg |
| Militärische Last | 700 kg | 700 kg |
| Fluggewicht | 3900 kg | 3900 kg |
| Höchstgeschwindigkeit | 780 km/h | 820 km/h |
| Reisegeschwindigkeit | 1500 km | 1550 km |
| Reichweite | 1500 km | 1550 km |
| Flugdauer max in 11 km Höhe | 1,75 h | 1,75 h |
| Steigzeit auf 6 km | 5,8 min | 4,9 min |
| Steiggeschwindigkeit max | 26,3 m/sec | 29,8 m/sec |
| Gipfelhöhe | 12,9 km | 13,7 km |
| Startstrecke | 790 m | 730 m |
| Startstrecke mit Startraketen (1000 kp Schub) | 390 m | 360 m |
| Lande-geschwindigkeit | 160 km/h | 155 km/h |
| Bewaffnung | 2 × MK 108 (30 mm K) | 2 × MK 108 (30 mm K) |
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