According to Wikipedia, one of the factors which almost caused B-29 44-27297 (Bockscar) to run out of fuel and crash at the end of its 9 August 1945 strike mission was the selection of an excessively high en-route cruise altitude1 (my emphasis):

Bockscar took off from Tinian’s North Field at 03:49. The mission profile directed the B-29s to fly individually to the rendezvous point, changed because of bad weather from Iwo Jima to Yakushima Island, and at 17,000 feet (5,200 m) cruising altitude instead of the customary 9,000 feet (2,700 m), increasing fuel consumption.

This does not make sense; generally, an aircraft’s fuel burn decreases with increasing altitude (due to the thinner air at high altitudes, which causes a given indicated airspeed to correspond to a much higher true airspeed, causing the aircraft to cover more distance in the same amount of time for the same amount of fuel burned [resulting in a lower per-distance fuel burn, and, as an extra bonus, a quicker flight]), all the way up to the altitude where indicated airspeed starts being limited by either declining engine power (as the engines can’t get as much air in the thinner high-altitude air, reducing their power output) or the aircraft’s mach limits (as a given indicated airspeed corresponds to a greater and greater true airspeed with increasing altitude, whereas, below the tropopause, a given mach number corresponds to a lower and lower true airspeed with increasing altitude, due to the progressive decrease in air temperature with increasing altitude in the troposphere), forcing the aircraft to fly at a slower indicated airspeed (which both makes the flight take longer, increasing the amount of time the engines are burning fuel, and forces the aircraft to fly at a higher, draggier angle of attack).

For most aircraft (even those not designed for high-mach flight), indicated airspeed (and, thus, per-distance fuel burn) generally only starts becoming mach-limited around 25-30 kilofeet (below this, approaching the aircraft’s mach limits would require airspeeds that are, except for specialised high-speed fighter and attack aircraft, greatly in excess of VNE, and would cause the aircraft to disintegrate from uncontrolled flutter), or even higher for aircraft optimised for transonic flight,2 so an aircraft’s per-distance fuel efficiency should continue to improve until at least these altitudes, as long as the engines can still produce enough power. The B-29’s3 engine, the Wright R-3350, is a turbocharged piston engine, and, thus (as the power output of turbocharged piston engines, like that of turbine engines,4 remains fairly flat up to very high altitudes, unlike that of naturally-aspirated piston engines, which drops off very rapidly with increasing altitude, or that of mechanically-supercharged piston engines, which also drops off considerably at high altitudes, although not nearly as much as naturally-aspirated piston engines), the B-29’s indicated airspeed would not be expected to be limited by available engine power below the altitudes at which it would become mach-limited.

Why, then, was Bockscar’s fuel burn apparently higher at 17 kft than at 9 kft, rather than lower?

1: Other factors were a broken fuel pump, which rendered unuseable all the fuel in one of the aircraft’s fuel tanks; the decision to take off with said fuel tank full of useless fuel, rather than defuelling the unuseable tank first to lighten the aircraft; the pilot’s circling at the rendezvous point for three-quarters of an hour waiting for an aircraft that never arrived, when he had been specifically ordered to wait no longer than fifteen minutes; the primary target’s having been covered by smoke and cloud which would not have been there absent the half-hour delay, resulting in the aircraft having to circle over the primary target, burning fuel, for fifty minutes before diverting to the secondary target; and twenty minutes wasted circling over the emergency landing field attempting (unsuccessfully, due to a broken radio) to gain landing clearance even when said clearance was not needed due to the aircraft’s critical low-fuel emergency.

2: Such as, for instance, all modern jetliners.

3: Bockscar was a B-29-36 (“Silverplate”) aircraft, extensively modified from the stock B-29 configuration to enable it to carry nuclear weapons; however, the vast majority of these changes were internal, having no effect on the aircraft’s aerodynamics. Of the exceptions, one (the use of reversible-pitch propellers on the Silverplate aircraft) would have no effect on the aircraft’s high-altitude performance except in the case of a propeller reversing in flight (hopefully not a normal, or even a common, occurrence), a second (the removal of almost all of the gun turrets found on a stock B-29) would considerably decrease the aircraft’s drag, making fuel burn less critical in any case, and, while the weight reduction (reducing the amount of lift - and, thus, the amount of induced drag - needed to maintain level flight) and more powerful engines (tending to cause the aircraft’s IAS to become power-limited at a higher altitude) of the Silverplates would tend to shift the minimum-per-distance-fuel-burn altitude upwards compared to that of the stock B-29 configuration, even the unmodified aircraft routinely operated at very high altitudes without difficulty, indicating that excessive fuel burn at high altitudes was probably not a big issue even for non-Silverplate B-29s.

4: And for exactly the same reason - the precompression of the intake air compensates for the lower density of high-altitude air.

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    $\begingroup$ "the power output of turbocharged piston engines... remains fairly flat up to very high altitudes" only if the degree of boost can be changed to maintain a constant manifold pressure. I'd guess they just didn't have enough boost to be efficient at that altitude. $\endgroup$ Commented Mar 19, 2020 at 10:15
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    $\begingroup$ What were the wind speed and direction at both altitudes that day? $\endgroup$ Commented Mar 19, 2020 at 13:21

1 Answer 1


From the B-29's commander training manual, page 69:

The range loss at high altitudes is caused almost entirely by the rich mixtures required at high powers and the larger cowl flap openings needed to cool the engines at high altitudes. In general, there is no loss in range up to 15,000 feet and the range losses at higher altitudes occur almost entirely when flying at the highest weights. You can avoid them, to a considerable extent, by flying at low altitudes until fuel has been used and a moderate weight has been obtained and then climbing to a higher altitude. [emphasis added]

Engine-driven forced induction isn't free, it comes from somewhere: fuel. And the cooling at high altitudes needs bigger cowl flap angles: drag.

enter image description here
B-29 cowl flaps; YouTube

Note: The B-29's engines are air-cooled, and the higher, the thinner the air. Each engine has a two-speed engine-driven supercharger as well as two exhaust-driven turbochargers (similar setup on the B-17 can be seen here). An intercooler is used to cool the exhaust-boosted air, which will be limited in thin air as well. The cruise manifold pressure was 28" Hg, compared to 47½" Hg on takeoff.

The same engines powered the Starliner, which also had better range when flying at 10,000 feet, compared to 15,000 and 21,800.$^1$

The remark on weight is due to the limited thrust when compared to a jet-powered airplane. By using the lift equation, jetliners have the ability to fly faster (TAS), whereas a B-29 will need to alter the $C_L$ somehow (angle of attack).

$^1$: Related: How does the efficiency of a piston aircraft change with altitude?

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    $\begingroup$ Re "Forced induction isn't free..." that depends on whether your forced induction system is an engine-driven supercharger, or a turbocharger that captures waste heat/energy from the exhaust. $\endgroup$
    – jamesqf
    Commented Mar 19, 2020 at 18:32
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    $\begingroup$ @jamesqf: Good point, I've expanded that part. $\endgroup$
    – user14897
    Commented Mar 19, 2020 at 19:02
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    $\begingroup$ it's fascinating that thinnner air (although it's colder up there) is worse at cooling than, uh, the cooler aspect of the air up there. Good one. $\endgroup$
    – Fattie
    Commented Mar 20, 2020 at 22:45
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    $\begingroup$ @Fattie: The cold air is excessively good for cooling a human being at 37C, but to an engine at maybe 200C ALL air is very cold in comparison. Thus density is more important. See: what-if.xkcd.com/155 $\endgroup$ Commented Apr 6, 2020 at 5:18

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