See shock stall in All languages combined, or Wiktionary
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"ref": "1944 April 27, Peter Caygill, quoting Tony Martindale, “Problems with Compressibility”, in Sound Barrier: The Rocky Road to MACH 1.0+, Barnsley, South Yorkshire: Pen & Sword Aviation, Pen & Sword Books, published 2006, →ISBN, page 41:",
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"ref": "1947 August, Oliver Stewart, “Breaking the World’s Speed Record”, in Max Karant, editor, Flying, volume 41, number 2, Chicago, Ill.: Ziff-Davis Publishing Company, →ISSN, →OCLC, page 60, column 1:",
"text": "His [Group Captain Hugh Joseph Wilson's] flights revealed at least two things: the effectiveness of turbojets used for the first time in international record breaking, and he came sufficiently close to the speed of sound to experience the effects of a partial shock stall. [...] It was noticed that changes in the air flow occur when the speed approaches the speed of sound—or, in other words, the speed at which waves propagate themselves in air—and that these changes could lead to a partial or complete shock stall.",
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"text": "A new realm in aerodynamics is entered, with sound and shock waves, Mach number and compressibility making their appearance. Life saving dope is disseminated [during ground training] on the warning signals and recognition of shock stalls and measures in recovering from them.",
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"ref": "1956, A. S. Hartshorn, L. F. Nicholson, The Aerodynamics of the Cooling of Aircraft Reciprocating Engines (Reports and Memoranda; 2498), London: Her Majesty’s Stationery Office, →OCLC, page 37:",
"text": "Direct evidence is meagre, but suggests that local shockstalls of this type do not generally imply a severe increase of drag, but may occasionally set up buffeting effects.",
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"ref": "1968, Lars E. Ericsson, J. Peter Reding, Unsteady Airfoil Stall and Stall Flutter (NASA Contractor Report; NASA/CR-111906), Washington, D.C.: National Aeronautics and Space Administration, →OCLC, page 34:",
"text": "Compressibility effects are not found to change the dynamic stall characteristics in principle until the Mach number gets high enough to cause shock-stall rather than leading edge stall.",
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"text": "In the present work, the shock stall of an oscillating NACA64A010 airfoil for which detailed experimental data are available is studied.",
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"text": "Anyone on the instructor's course should be experienced enough to handle the odd shock stall, which by definition was only going to happen at height where there was plenty of room to sort things out.",
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"text": "The tailplane usually becomes more effective as a stabiliser at high Mach numbers because there are decreases of wing lift-curve slope and rate of change of downwash with mean lift coefficient. The latter effect is mainly due to the wing-root shock stalling at a lower Mach number than the rest of the wing.",
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"text": "The separation of the flow over wings precipitated by the compression shock that forms as speeds are increased into the supercritical Mach number range has imposed serious difficulties in the improvement of aircraft performance. These difficulties arise principally as a consequence of the rapid drag rise and the loss of lift that causes serious stability changes when the wing shock-stalls.",
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"text": "In fact, in this case, after stalling in the normal manner, he would probably have fallen off in a dive and in doing so, increase his speed until he shock[-]stalled before effecting recovery.",
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"ref": "1949 October, K. W. Todd, An Experimental Study of Three-dimensional High-speed Air Conditions in a Cascade of Axial-flow Compressor Blades (Aeronautical Research Council Reports and Memoranda; no. 2792), London: Her Majesty's Stationery Office, published 1954, →OCLC, archived from the original on 2015-10-03, page 1:",
"text": "As a result of these tests it was shown that at the design incidence the conventional cascade shock stalled at some 75 per cent of the critical inlet velocity.",
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"text": "When the wing shock stalls, the lift gradient a falls and, if no shock stalling occurs on the tail plane, the term #x5C;frac#x7B;a#x5F;1#x5C;bar#x7B;V",
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"text": "Compressibility effects are not found to change the dynamic stall characteristics in principle until the Mach number gets high enough to cause shock-stall rather than leading edge stall.",
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},
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"text": "In the present work, the shock stall of an oscillating NACA64A010 airfoil for which detailed experimental data are available is studied.",
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},
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"text": "The tailplane usually becomes more effective as a stabiliser at high Mach numbers because there are decreases of wing lift-curve slope and rate of change of downwash with mean lift coefficient. The latter effect is mainly due to the wing-root shock stalling at a lower Mach number than the rest of the wing.",
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"text": "The separation of the flow over wings precipitated by the compression shock that forms as speeds are increased into the supercritical Mach number range has imposed serious difficulties in the improvement of aircraft performance. These difficulties arise principally as a consequence of the rapid drag rise and the loss of lift that causes serious stability changes when the wing shock-stalls.",
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"text": "In fact, in this case, after stalling in the normal manner, he would probably have fallen off in a dive and in doing so, increase his speed until he shock[-]stalled before effecting recovery.",
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"text": "As a result of these tests it was shown that at the design incidence the conventional cascade shock stalled at some 75 per cent of the critical inlet velocity.",
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},
{
"ref": "1951, staff of the RAE [Royal Aircraft Establishment] High Speed Wind Tunnel, High Speed Wind Tunnel Tests on Models of Two Jet-propelled Fighters (Meteor and Vampire) (Aeronautical Research Council Reports and Memoranda; no. 2504), London: Her Majesty's Stationery Office, →OCLC, page 35:",
"text": "When the wing shock stalls, the lift gradient a falls and, if no shock stalling occurs on the tail plane, the term #x5C;frac#x7B;a#x5F;1#x5C;bar#x7B;V",
"type": "quote"
}
],
"glosses": [
"Of an aircraft or a component of it: to undergo a shock stall."
],
"links": [
[
"aviation",
"aviation"
],
[
"aircraft",
"aircraft"
],
[
"component",
"component"
],
[
"undergo",
"undergo"
],
[
"shock stall",
"#Noun"
]
],
"raw_glosses": [
"(intransitive, aviation) Of an aircraft or a component of it: to undergo a shock stall."
],
"tags": [
"intransitive"
],
"topics": [
"aeronautics",
"aerospace",
"aviation",
"business",
"engineering",
"natural-sciences",
"physical-sciences"
]
}
],
"sounds": [
{
"ipa": "/ˈʃɒk ˌstɔːl/",
"tags": [
"Received-Pronunciation"
]
},
{
"audio": "LL-Q1860 (eng)-Vealhurl-shock stall.wav",
"mp3_url": "https://upload.wikimedia.org/wikipedia/commons/transcoded/4/4f/LL-Q1860_%28eng%29-Vealhurl-shock_stall.wav/LL-Q1860_%28eng%29-Vealhurl-shock_stall.wav.mp3",
"ogg_url": "https://upload.wikimedia.org/wikipedia/commons/transcoded/4/4f/LL-Q1860_%28eng%29-Vealhurl-shock_stall.wav/LL-Q1860_%28eng%29-Vealhurl-shock_stall.wav.ogg"
},
{
"ipa": "/ˈʃɑk ˌstɔl/",
"tags": [
"General-American"
]
}
],
"synonyms": [
{
"word": "shock-stall"
}
],
"word": "shock stall"
}
Download raw JSONL data for shock stall meaning in English (11.6kB)
{
"called_from": "parser/304",
"msg": "HTML tag <math> not properly closed",
"path": [
"shock stall"
],
"section": "English",
"subsection": "verb",
"title": "shock stall",
"trace": "started on line 1, detected on line 1"
}
This page is a part of the kaikki.org machine-readable English dictionary. This dictionary is based on structured data extracted on 2024-12-15 from the enwiktionary dump dated 2024-12-04 using wiktextract (8a39820 and 4401a4c). The data shown on this site has been post-processed and various details (e.g., extra categories) removed, some information disambiguated, and additional data merged from other sources. See the raw data download page for the unprocessed wiktextract data.
If you use this data in academic research, please cite Tatu Ylonen: Wiktextract: Wiktionary as Machine-Readable Structured Data, Proceedings of the 13th Conference on Language Resources and Evaluation (LREC), pp. 1317-1325, Marseille, 20-25 June 2022. Linking to the relevant page(s) under https://kaikki.org would also be greatly appreciated.