Supersonic Flight Calculator (Concorde & Beyond)
Mach 2 at FL600: TAS, ground-referenced crossing times, and the stagnation heating that set Concorde's skin temperature — supersonic flight in numbers.
At M2.0 the stagnation math yields ~117 °C — Concorde's nose actually ran near 127 °C, stretching the airframe 20+ cm in cruise. M2.2 was the aluminum limit; faster designs (SR-71, M3.2) required titanium. Heating, not thrust, capped the speed.
Formula
⚠️ For flight planning and education only — verify with your POH/AFM, certified instruments and official sources. Not for primary navigation or airworthiness decisions.
Mach 2 at FL600: TAS, ground-referenced crossing times, and the stagnation heating that set Concorde's skin temperature — supersonic flight in numbers.
About Supersonic Flight Calculator (Concorde & Beyond)
Concorde crossed the Atlantic in under three hours not at '1,323 knots' (twice sea-level Mach 1) but at about 1,147 — because Mach 2 is measured against the cold stratosphere's slower sound. This calculator runs supersonic cruise in numbers: TAS from Mach and temperature, still-air crossing times for any route, and the stagnation-temperature formula that explains the deepest constraint of supersonic transport — at Mach 2, aluminum flies a continuous bake at 120 °C, and at Mach 3 it simply melts its strength away.
How to use Supersonic Flight Calculator (Concorde & Beyond)
- 1Enter — sensible defaults are pre-filled so you see a worked result immediately.
- 2Read the live results: .
- 3Check the "With your numbers" line to see the formula TAS = M·a(T); T_stag = T·(1 + 0.2M²) — the kinetic heating that aluminum must survive substituted step by step.
- 4Adjust inputs (or flip the unit toggle) until the scenario matches yours, then copy or share the result.
Why use Supersonic Flight Calculator (Concorde & Beyond)?
- ✓Instant, free and private — every calculation runs in your browser, nothing is uploaded
- ✓Built on the published formula TAS = M·a(T); T_stag = T·(1 + 0.2M²) — the kinetic heating that aluminum must survive with sources cited on the page
- ✓At M2.0 the stagnation math yields ~117 °C — Concorde's nose actually ran near 127 °C, stretching the airframe 20+ cm in cruise. M2.2 was the aluminum limit; faster designs (SR-71, M3.2) required titanium. Heating, not thrust, capped the speed.
- ✓Switch units, tweak any input and watch every result update live
Frequently asked questions
How fast was Concorde really going at Mach 2?+
About 1,147 kt TAS (2,124 km/h / 1,320 mph) in standard −56.5 °C stratospheric air at FL550–600. Ground speed varied with winds: the eastbound record crossing (2h 52m JFK–LHR in 1996) rode a jet stream to ground speeds well past 1,200 kt. Westbound took half an hour longer for the same reason in reverse.
Why did kinetic heating limit the speed rather than engine power?+
Stagnation temperature grows with M²: 117 °C at M2.0, but 240 °C at M2.7 and 330 °C at M3.0. Conventional aluminum alloys lose certified strength rapidly above ~130 °C, fixing Concorde's M2.04 limit. The M3+ SR-71 paid the titanium price — in money and manufacturing pain — to survive its own friction.
Did Concorde physically stretch in cruise?+
Yes — thermal expansion lengthened the fuselage 15–25 cm at cruise temperature, famously opening a gap by the flight engineer's panel that closed permanently on the final flight, trapping a cap placed there as a retirement gesture. Expansion joints throughout the structure were a primary design feature, not a curiosity.
Could a new supersonic airliner beat these numbers?+
The physics hasn't moved: M1.7–2.2 remains the practical band for thermally conventional materials, and the sonic-boom ground bar (the focus of NASA's X-59 low-boom work) constrains routes more than speed. Modern proposals (Boom Overture at M1.7) sit deliberately below Concorde's Mach — the constraint was never engine ambition; it's the same T·(1+0.2M²) computed on this page.
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