# Lycoming XH-2470 > Mediated Wiki article. Canonical URL: https://mediated.wiki/source/Lycoming_XH-2470 > Markdown URL: https://mediated.wiki/source/Lycoming_XH-2470.md > Source: https://en.wikipedia.org/wiki/Lycoming_XH-2470 > Source revision: 1352601903 > License: Creative Commons Attribution-ShareAlike 4.0 International (https://creativecommons.org/licenses/by-sa/4.0/) Aircraft engine developed by Lycoming Engines XH-2470 Lycoming XH-2470-7 Type H engine National origin United States Manufacturer Lycoming Engines First run 1940 Major applications Vultee XP-54 Developed from Lycoming O-1230 The **Lycoming XH-2470** was an [H engine](/source/H_engine) for aircraft designed and developed by [Lycoming Engines](/source/Lycoming_Engines) in the 1930s. Although the engine was flown in an aircraft, it was not fitted to any aircraft selected for production. It was derived from the [Lycoming O-1230](/source/Lycoming_O-1230) engine. ## Design and development In 1932, the engineers at Lycoming Engines became aware that the [United States Army Air Corps](/source/United_States_Army_Air_Corps) (USAAC) wanted a high-performance engine that could produce at least one [horsepower](/source/Horsepower) per cubic inch (46 kW/L) of engine displacement.[1] Determined to become known as a high-performance engine manufacturer, Lycoming began an experimental, high-performance engine of its own. After spending US $500,000, and after many attempts to develop a successful engine, it finally came close to the USAAC specifications with the O-1230 engine, which was a 12-cylinder liquid-cooled horizontally opposed low-profile piston engine.[2] In 1936, the single-cylinder development tests exceeded expectations, passing its 50-hour test requirement. The full-size engine was ready for testing in 1937, and was rated at 1,000 hp. Continued development of the O-1230 reached its peak when the engine was rated at over 1,200 hp (895 kW). The O-1230 was not well received by aircraft manufacturers, because it was not very reliable at that power setting.[2] It was apparent that the O-1230 engine was uncompetitive with the high-performance air-cooled engines that were then becoming available. The US Navy began funding the development of the Lycoming engine.[3] The funding enabled Lycoming's engineers to attempt rescuing the design by proposing a 24-cylinder H-configuration engine made by stacking two of the O-1230 engines, gearing them together to one common output shaft. The new engine was the H-2470. It weighed in at 2,430 pounds and produced 2,300 hp (1,700 kW) at 3,300 rpm.[2] ## Operational history The Navy specified the H-2470 for the [Curtiss XF14C-1](/source/Curtiss_XF14C) experimental fighter.[2] After some rigorous testing the engine's poor performance led to the substitution, before the aircraft flew, of a [Wright R-3350](/source/Wright_R-3350) radial engine, which was also having technical problems but was considered to be more reliable than the H-2470. The testing program was eventually terminated due to the poor performance of the aircraft.[4] The USAAC was also interested in the H-2470, and installed and flew it in the [Vultee XP-54](/source/Vultee_XP-54) prototype fighter. The XP-54 was the only aircraft to actually use it for flight, but like the Navy's XF-14C, the XP-54 never went into production.[2] ## Applications - [Vultee XP-54](/source/Vultee_XP-54) ### Intended - [Curtiss XF14C](/source/Curtiss_XF14C) - [Northrop N-1](/source/Northrop_N-1) ## Specifications ### General characteristics - **Type:** 24-cylinder, 'H' piston engine - **[Bore](/source/Bore_(engine)):** 5.25 in. (133.35 mm) - **[Stroke](/source/Stroke_(engine)):** 4.75 in. (120.65 mm) - **[Displacement](/source/Engine_displacement):** 2467.8 cu in (40.44 L) - **[Dry weight](/source/Dry_weight):** 2,430 lb (1,102 kg) ### Components - **[Valvetrain](/source/Valvetrain):** [Dual overhead camshafts](/source/Overhead_camshaft_engine) (DOHC) with four valves per cylinder - **[Supercharger](/source/Supercharger):** Single-speed, single-stage (two-speed on the -5 variant) - **Fuel system:** Carburetor (with potential for gasoline injection in testing) - **Fuel type:** 100/130 [octane](/source/Octane) gasoline - **Cooling system:** Liquid-cooled ### Performance - **Power output:** 2,300 hp at 3,300 rpm - **[Compression ratio](/source/Compression_ratio):** 6.5:1 ## See also **Comparable engines** - [Fairey P.24](/source/Fairey_Monarch) - [Napier Sabre](/source/Napier_Sabre) **Related lists** - [List of aircraft engines](/source/List_of_aircraft_engines) ## References 1. **[^](#cite_ref-White379_1-0)** White p. 379 1. ^ [***a***](#cite_ref-White380_2-0) [***b***](#cite_ref-White380_2-1) [***c***](#cite_ref-White380_2-2) [***d***](#cite_ref-White380_2-3) [***e***](#cite_ref-White380_2-4) White p. 380 1. **[^](#cite_ref-Balzer_3-0)** Balzer p. 24 1. **[^](#cite_ref-White381_4-0)** White p. 381 - White, Graham, *Allied Aircraft Piston Engines of World War II*, SAE International, 1995 - Balzer, Gerald C., *American Secret Pusher Fighters of World War II*, Specialty Press. 2008 - Wagner, Ray, *American Combat Planes*, Third Enlarged Edition, Doubleday, 1982. - Wegg, John, *General Dynamics Aircraft and Their Predecessors*, Naval Institute Press, 1990. ## External links - [XH-2470 in a test cell](http://postfiles7.naver.net/data44/2009/1/5/166/result_2009_0_1_11_9_40_656_2-naljava69.jpg?type=w2) v t e Lycoming aircraft engines Opposed piston engines O-145 O-233 IO-233 O-235 O-290 O-320 O-340 O-360 (O-360 variants) IO-390 O-435 O-480 O-540 TIO-541 GSO-580 IO-580 IO-720 O-1230 Radial engines and H engines R-680 XR-7755 XH-2470 Aircraft diesel engines DEL-120 Turbofans PLF1 ALF 502/YF102 LF 507 Turboprops/Turboshafts AGT1500 LTS101/LTP101 T53 T55 Aero-derivative marine gas turbines TF-40 Joint development Avco (Lycoming)/Pratt & Whitney: T800-APW (Turboshaft) See also AlliedSignal Aerospace/Honeywell Aerospace v t e United States military piston aircraft engine designation system H (four-bank H-configuration inline) H-1640 XH-2240 XH-2470 XH-2600 XH-3130 XH-3730 H-4070 IV (inverted-V inline) IV-1430 IV-2040 IV-2220 L (single-bank inline) L-330 L-365 L-375 L-390 L-410 L-440 L-510 L-825 O (opposed) O-15 O-40 O-45 O-90 O-100 O-145 O-150 O-170 O-175 O-180 O-190 O-200 (C) O-200 (F) O-205 O-235 O-290 O-300 O-335 O-360 (C) O-360 (L) O-405 O-425 O-435 O-470 O-480 O-520 O-540 (F) O-540 (L) O-550 O-580 O-805 O-1230 R (radial) R-250 R-265 R-270 R-370 (LB) R-370 (K) R-420 R-440 R-500 R-540 (W) R-540 (K) R-545 R-550 R-600 R-670 R-680 R-720 R-755 R-760 R-790 R-830 R-915 R-975 DR-980 R-985 R-1044 R-1300 R-1340 R-1454 R-1510 R-1535 R-1640 R-1670 R-1690 R-1740 R-1750 R-1820 R-1830 R-1860 R-2000 R-2060 R-2160 R-2180 R-2600 R-2800 R-3350 R-4090 R-4360 R-7755 V (upright-V inline) V-720 V-1150 V-1237 V-1400 V-1440 V-1460 V-1510 V-1560 V-1570 V-1650 (P) V-1710 V-1950 V-3420 V (inverted-V inline) V-770 V-1650 (L) VG (inverted-V inline) VG-1410 W (three-bank W-configuration inline) W-2779 See also: X-1800 US military gas turbine aeroengines Piston engine configurations This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. --- Adapted from the Wikipedia article [Lycoming XH-2470](https://en.wikipedia.org/wiki/Lycoming_XH-2470) by Wikipedia contributors ([contributor history](https://en.wikipedia.org/wiki/Lycoming_XH-2470?action=history)). Available under [Creative Commons Attribution-ShareAlike 4.0 International](https://creativecommons.org/licenses/by-sa/4.0/). Changes may have been made.