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The dataset generation failed because of a cast error
Error code: DatasetGenerationCastError
Exception: DatasetGenerationCastError
Message: An error occurred while generating the dataset
All the data files must have the same columns, but at some point there are 3 new columns ({'query_id', 'query', 'relevant_docs_gt_0'}) and 4 missing columns ({'id', 'text', 'dense', 'sparse'}).
This happened while the csv dataset builder was generating data using
hf://datasets/opensporks/CranfieldEmbedded/qrels.csv (at revision 4045c25c7adfdba1153802a1d064aa5b0b563cf6)
Please either edit the data files to have matching columns, or separate them into different configurations (see docs at https://hf.co/docs/hub/datasets-manual-configuration#multiple-configurations)
Traceback: Traceback (most recent call last):
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/builder.py", line 2013, in _prepare_split_single
writer.write_table(table)
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/arrow_writer.py", line 585, in write_table
pa_table = table_cast(pa_table, self._schema)
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/table.py", line 2302, in table_cast
return cast_table_to_schema(table, schema)
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/table.py", line 2256, in cast_table_to_schema
raise CastError(
datasets.table.CastError: Couldn't cast
query_id: int64
query: string
relevant_docs_gt_0: string
-- schema metadata --
pandas: '{"index_columns": [{"kind": "range", "name": null, "start": 0, "' + 620
to
{'id': Value(dtype='int64', id=None), 'text': Value(dtype='string', id=None), 'dense': Value(dtype='string', id=None), 'sparse': Value(dtype='string', id=None)}
because column names don't match
During handling of the above exception, another exception occurred:
Traceback (most recent call last):
File "/src/services/worker/src/worker/job_runners/config/parquet_and_info.py", line 1396, in compute_config_parquet_and_info_response
parquet_operations = convert_to_parquet(builder)
File "/src/services/worker/src/worker/job_runners/config/parquet_and_info.py", line 1045, in convert_to_parquet
builder.download_and_prepare(
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/builder.py", line 1029, in download_and_prepare
self._download_and_prepare(
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/builder.py", line 1124, in _download_and_prepare
self._prepare_split(split_generator, **prepare_split_kwargs)
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/builder.py", line 1884, in _prepare_split
for job_id, done, content in self._prepare_split_single(
File "/src/services/worker/.venv/lib/python3.9/site-packages/datasets/builder.py", line 2015, in _prepare_split_single
raise DatasetGenerationCastError.from_cast_error(
datasets.exceptions.DatasetGenerationCastError: An error occurred while generating the dataset
All the data files must have the same columns, but at some point there are 3 new columns ({'query_id', 'query', 'relevant_docs_gt_0'}) and 4 missing columns ({'id', 'text', 'dense', 'sparse'}).
This happened while the csv dataset builder was generating data using
hf://datasets/opensporks/CranfieldEmbedded/qrels.csv (at revision 4045c25c7adfdba1153802a1d064aa5b0b563cf6)
Please either edit the data files to have matching columns, or separate them into different configurations (see docs at https://hf.co/docs/hub/datasets-manual-configuration#multiple-configurations)Need help to make the dataset viewer work? Make sure to review how to configure the dataset viewer, and open a discussion for direct support.
id int64 | text string | dense string | sparse string |
|---|---|---|---|
1 | experimental investigation of the aerodynamics of a
wing in a slipstream . experimental investigation of the aerodynamics of a
wing in a slipstream .
an experimental study of a wing in a propeller slipstream was
made in order to determine the spanwise distribution of the lift
increase due to slipstream at different a... | [-0.07191337645053864, 0.038404058665037155, 0.03211066871881485, -6.380776903824881e-05, 0.0059929802082479, 0.01862715184688568, -0.04963424429297447, 0.04158153757452965, 0.08827923238277435, -0.01516458485275507, 0.04696153104305267, 0.023280780762434006, 0.025424763560295105, 0.0070450762286782265, 0.0067297723144... | {6388: 3, 4812: 2, 1997: 12, 1996: 13, 28033: 2, 2015: 2, 1037: 9, 3358: 4, 1999: 5, 17433: 6, 25379: 6, 1012: 7, 2019: 3, 2817: 1, 15692: 1, 2001: 4, 2081: 2, 2344: 1, 2000: 5, 5646: 1, 8487: 2, 14244: 1, 4353: 1, 6336: 4, 3623: 1, 2349: 2, 2012: 2, 2367: 3, 12113: 1, 2886: 1, 1998: 1, 2489: 1, 5460: 1, 10146: 1, 2187... |
2 | simple shear flow past a flat plate in an incompressible fluid of small
viscosity . simple shear flow past a flat plate in an incompressible fluid of small
viscosity .
in the study of high-speed viscous flow past a two-dimensional body it
is usually necessary to consider a curved shock wave emitting from the
nose or le... | [-0.05897046998143196, 0.025672635063529015, 0.07825838029384613, -0.05759742483496666, 0.09697356820106506, -0.03216995298862457, -0.07361289113759995, 0.08138982951641083, 0.024152617901563644, -0.0718063935637474, 0.03965277597308159, -0.0540878027677536, -0.041934143751859665, -0.0012081308523193002, 0.000810840225... | {3722: 3, 18330: 3, 4834: 7, 2627: 5, 1037: 10, 4257: 4, 5127: 4, 1999: 11, 2019: 3, 4297: 3, 25377: 3, 8303: 3, 7028: 3, 8331: 3, 1997: 7, 2235: 3, 25292: 5, 13186: 3, 3012: 3, 1012: 11, 1996: 18, 2817: 2, 2152: 1, 1011: 6, 3177: 1, 27199: 2, 2048: 2, 8789: 2, 2303: 2, 2009: 2, 2003: 5, 2788: 1, 4072: 1, 2000: 2, 5136... |
3 | the boundary layer in simple shear flow past a flat plate . the boundary layer in simple shear flow past a flat plate .
the boundary-layer equations are presented for steady
incompressible flow with no pressure gradient . | [-0.035630133002996445, 0.040053874254226685, 0.032900381833314896, -0.031648971140384674, 0.03140444681048393, -0.009553992189466953, -0.09835833311080933, 0.024583688005805016, 0.0013244750443845987, -0.10184615850448608, -0.018437769263982773, -0.07645055651664734, -0.025778446346521378, 0.016924843192100525, 0.0063... | {1996: 3, 6192: 3, 6741: 3, 1999: 2, 3722: 2, 18330: 2, 4834: 3, 2627: 2, 1037: 2, 4257: 2, 5127: 2, 1012: 3, 1011: 1, 11380: 1, 2024: 1, 3591: 1, 2005: 1, 6706: 1, 4297: 1, 25377: 1, 8303: 1, 7028: 1, 2007: 1, 2053: 1, 3778: 1, 17978: 1} |
4 | approximate solutions of the incompressible laminar
boundary layer equations for a plate in shear flow . approximate solutions of the incompressible laminar
boundary layer equations for a plate in shear flow .
the two-dimensional steady boundary-layer
problem for a flat plate in a
shear flow of incompressible fluid i... | [-0.05991241708397865, 0.06186901405453682, 0.051258888095617294, -0.0460890457034111, -0.0042056189849972725, -0.029525287449359894, -0.058265168219804764, 0.021466422826051712, 0.008725897409021854, -0.12880165874958038, 0.021316006779670715, -0.09195461869239807, -0.036005258560180664, 0.03686906397342682, -0.065168... | {15796: 2, 7300: 3, 1997: 5, 1996: 9, 4297: 3, 25377: 3, 8303: 3, 7028: 3, 16983: 2, 3981: 2, 2099: 2, 6192: 6, 6741: 6, 11380: 2, 2005: 4, 1037: 5, 5127: 3, 1999: 4, 18330: 3, 4834: 4, 1012: 5, 2048: 1, 1011: 4, 8789: 1, 6706: 1, 3291: 1, 4257: 1, 8331: 1, 2003: 1, 2641: 1, 14983: 1, 1010: 2, 3096: 1, 15012: 1, 1998: ... |
5 | one-dimensional transient heat conduction into a double-layer
slab subjected to a linear heat input for a small time
internal . one-dimensional transient heat conduction into a double-layer
slab subjected to a linear heat input for a small time
internal .
analytic solutions are presented for the transient heat
conduc... | [0.019646866247057915, 0.03522230684757233, 0.06297660619020462, 0.028489241376519203, 0.01222902536392212, -0.03587677702307701, -0.04088636115193367, -0.007834702730178833, 0.03777141124010086, 0.03153689205646515, 0.04983813688158989, -0.049252793192863464, 0.03313542902469635, -0.033652521669864655, 0.0665177032351... | {2028: 3, 1011: 4, 8789: 2, 25354: 3, 3684: 6, 6204: 3, 3258: 3, 2046: 2, 1037: 7, 3313: 2, 6741: 2, 17584: 2, 13532: 2, 2000: 3, 7399: 2, 7953: 2, 2005: 4, 2235: 2, 2051: 2, 4722: 2, 1012: 4, 23521: 1, 7300: 1, 2024: 1, 3591: 1, 1996: 1, 1999: 1, 12490: 1, 28761: 1, 6086: 1, 2012: 1, 3302: 1, 14023: 1, 3446: 2, 2023: ... |
6 | one-dimensional transient heat flow in a multilayer
slab . one-dimensional transient heat flow in a multilayer
slab .
in a recent contribution to the readers'
forum wassermann gave analytic
solutions for the temperature in a double
layer slab, with a triangular heat
rate input at one face, insulated at the other,
and... | [-0.04882737621665001, 0.03383438289165497, 0.05919436365365982, 0.009107321500778198, 0.025084828957915306, 0.016861381009221077, -0.036068398505449295, -0.002286538016051054, 0.0022780094295740128, -0.018619941547513008, 0.0545395091176033, -0.09513647854328156, 0.04927917942404747, -0.052594561129808426, 0.016037749... | {2028: 3, 1011: 2, 8789: 2, 25354: 2, 3684: 4, 4834: 2, 1999: 4, 1037: 5, 4800: 2, 24314: 2, 17584: 3, 1012: 6, 3522: 1, 6691: 1, 2000: 5, 1996: 10, 8141: 1, 1005: 1, 7057: 1, 2001: 2, 8043: 2, 5804: 2, 2435: 1, 23521: 1, 7300: 3, 2005: 3, 4860: 1, 3313: 1, 6741: 1, 1010: 5, 2007: 2, 14023: 1, 3446: 1, 7953: 2, 2012: 3... |
7 | the effect of controlled three-dimensional roughness
on boundary layer transition at supersonic speeds . the effect of controlled three-dimensional roughness
on boundary layer transition at supersonic speeds .
experiments were performed in the 12-in. supersonic wind
tunnel of the jet propulsion laboratory of the cali... | [0.037293076515197754, -0.07550406455993652, 0.09171322733163834, -0.010615951381623745, -0.00640288507565856, -0.03770982846617699, -0.09650424122810364, -0.019290506839752197, 0.060108914971351624, -0.11653117835521698, -0.08154643326997757, -0.013457217253744602, -0.01403820887207985, -0.02329634130001068, -0.015989... | {1996: 25, 3466: 4, 1997: 15, 4758: 2, 2093: 4, 1011: 8, 8789: 4, 5931: 8, 2791: 8, 2006: 4, 6192: 5, 6741: 5, 6653: 6, 2012: 5, 3565: 3, 18585: 3, 10898: 2, 1012: 9, 7885: 1, 2020: 1, 2864: 1, 1999: 3, 2260: 1, 3612: 1, 5234: 1, 6892: 1, 16404: 1, 5911: 1, 2662: 1, 2820: 1, 2974: 1, 2000: 4, 8556: 1, 3787: 3, 1006: 7,... |
8 | measurements of the effect of two-dimensional and three-dimensional
roughness elements on boundary layer transition . measurements of the effect of two-dimensional and three-dimensional
roughness elements on boundary layer transition .
in his study of the effect of roughness on transition, h. l.
dryden found, on the ba... | [-0.01816405914723873, 0.009179331362247467, 0.10438792407512665, -0.010662601329386234, -0.0075240968726575375, -0.08142438530921936, -0.0808560773730278, 0.06319228559732437, 0.019537588581442833, -0.09974490106105804, -0.08118334412574768, -0.028967050835490227, -0.0014722548658028245, 0.0506746843457222, -0.0065622... | {11702: 2, 1997: 17, 1996: 18, 3466: 4, 2048: 4, 1011: 8, 8789: 7, 1998: 4, 2093: 3, 5931: 7, 2791: 7, 3787: 4, 2006: 7, 6192: 3, 6741: 3, 6653: 5, 1012: 7, 1999: 3, 2010: 2, 2817: 1, 1010: 9, 1044: 1, 1048: 1, 4318: 1, 4181: 1, 2179: 1, 3978: 1, 2800: 1, 2951: 2, 2008: 1, 1037: 5, 5783: 3, 2107: 1, 2004: 1, 1013: 2, 4... |
9 | transition studies and skin friction measurements on
an insulated flat plate at a mach number of 5.8 . transition studies and skin friction measurements on
an insulated flat plate at a mach number of 5.8 .
an investigation of transition and skin friction on an insulated
flat plate, 5 by 26 in., was made in the galcit... | [0.0015236316248774529, 0.02698235958814621, 0.059300497174263, 0.0017933344934135675, 0.06527799367904663, -0.02689485251903534, -0.03796474635601044, 0.06969396770000458, -0.010493059642612934, -0.013863791711628437, 0.013752657920122147, -0.09585438668727875, -0.04236371070146561, 0.008845044299960136, 0.02694517374... | {6653: 6, 2913: 2, 1998: 9, 3096: 5, 15012: 5, 11702: 4, 2006: 5, 2019: 5, 16021: 3, 8898: 3, 4257: 4, 5127: 5, 2012: 10, 1037: 10, 24532: 3, 2193: 4, 1997: 22, 1019: 10, 1012: 21, 1022: 3, 4812: 2, 1010: 8, 2011: 4, 2656: 1, 1999: 7, 2001: 10, 2081: 2, 1996: 17, 14891: 1, 26243: 1, 23760: 2, 18585: 2, 3612: 1, 5234: 2... |
10 | the theory of the impact tube at low pressure . the theory of the impact tube at low pressure .
a theoretical analysis has been made for an impact tube of the
relation between free-stream mach number and the impact and
free-stream pressures and densities for extremely low pressures .
it is shown that the results diff... | [-0.015002978965640068, 0.03152976185083389, 0.014111502096056938, 0.029221350327134132, -0.0019367532804608345, 0.021203020587563515, 0.017047209665179253, 0.16421008110046387, -0.0012137748999521136, -0.014336262829601765, -0.019571419805288315, -0.0060020494274795055, 0.01603228598833084, 0.017152994871139526, 0.003... | {1996: 8, 3399: 2, 1997: 3, 4254: 4, 7270: 3, 2012: 2, 2659: 3, 3778: 2, 1012: 4, 1037: 1, 9373: 1, 4106: 1, 2038: 1, 2042: 1, 2081: 1, 2005: 2, 2019: 1, 7189: 1, 2090: 1, 2489: 2, 1011: 2, 5460: 2, 24532: 1, 2193: 1, 1998: 3, 15399: 2, 7939: 1, 24279: 1, 5186: 1, 2009: 1, 2003: 1, 3491: 1, 2008: 1, 3463: 1, 11234: 1, ... |
11 | similar solutions in compressible laminar free mixing
problems . similar solutions in compressible laminar free mixing
problems .
there are in supersonic aerodynamics many situations of
practical interest wherein streams of different velocities and,
in general, different stagnation pressures mix with one another .
in t... | [-0.03522880747914314, -0.05621832236647606, -0.0024169189855456352, -0.05477166548371315, -0.06642463803291321, -0.04085983335971832, -0.0335698276758194, -0.018874211236834526, -0.002704053418710828, -0.1021791324019432, 0.03747706860303879, -0.010207291692495346, 0.017788061872124672, -0.06096617877483368, 0.0019686... | {2714: 2, 7300: 2, 1999: 7, 4012: 2, 20110: 2, 7028: 2, 16983: 2, 3981: 2, 2099: 2, 2489: 2, 6809: 4, 3471: 3, 1012: 6, 2045: 1, 2024: 1, 3565: 1, 18585: 1, 28033: 1, 2015: 2, 2116: 1, 8146: 1, 1997: 9, 6742: 1, 3037: 1, 16726: 2, 9199: 2, 2367: 2, 2310: 1, 4135: 1, 26243: 1, 3111: 1, 1998: 2, 1010: 2, 2236: 1, 2358: 1... |
12 | some structural and aerelastic considerations of high
speed flight . some structural and aerelastic considerations of high
speed flight .
the dominating factors in structural design of high-speed
aircraft are thermal and aeroelastic in origin . the subject
matter is concerned largely with a discussion of these facto... | [0.048347849398851395, 0.07746336609125137, -0.052324019372463226, 0.03179536759853363, 0.01523650623857975, -0.035007819533348083, -0.009905549697577953, 0.005250415299087763, -0.004953310359269381, 0.05200949311256409, 0.0452873520553112, 0.01695740409195423, -0.01312048826366663, -0.04199346527457237, 0.044298399239... | {2070: 4, 8332: 4, 1998: 8, 29347: 2, 16570: 3, 20875: 2, 16852: 2, 1997: 12, 2152: 5, 3177: 5, 3462: 4, 1012: 8, 1996: 8, 21949: 1, 5876: 2, 1999: 2, 2640: 1, 1011: 3, 2948: 2, 2024: 3, 9829: 2, 18440: 2, 10581: 3, 10074: 3, 4761: 1, 3395: 1, 3043: 1, 2003: 3, 4986: 1, 4321: 1, 2007: 3, 1037: 2, 6594: 1, 2122: 1, 2037... |
13 | similarity laws for stressing heated wings . similarity laws for stressing heated wings .
it will be shown that the differential equations for a heated
plate with large temperature gradient and for a similar plate at
constant temperature can be made the same by a proper
modification of the thickness and the loading f... | [-0.028591059148311615, 0.02087344601750374, -0.06355740875005722, -0.0025351860094815493, -0.032903119921684265, -0.05985196307301521, 0.03018607385456562, -0.002185807330533862, 0.038838889449834824, 0.026780137792229652, 0.004521017894148827, -0.023653890937566757, -0.018228475004434586, 0.012967255897819996, 0.0104... | {14402: 3, 4277: 3, 2005: 5, 6911: 3, 2075: 3, 9685: 5, 4777: 3, 1012: 7, 2009: 1, 2097: 1, 2022: 4, 3491: 1, 2008: 2, 1996: 16, 11658: 1, 11380: 1, 1037: 5, 5127: 5, 2007: 1, 2312: 1, 4860: 2, 17978: 1, 1998: 5, 2714: 1, 2012: 1, 5377: 1, 2064: 3, 2081: 1, 2168: 2, 2011: 3, 5372: 1, 14080: 1, 1997: 5, 14983: 1, 10578:... |
14 | piston theory - a new aerodynamic tool for the
aeroelastician . piston theory - a new aerodynamic tool for the
aeroelastician .
representative applications are described which illustrate the
extent to which simplifications in the solutions of high-speed
unsteady aeroelastic problems can be achieved through the use of... | [-0.06670428067445755, 0.0755978375673294, -0.04930005222558975, -0.03147517144680023, -0.021815069019794464, -0.0226439256221056, 0.009713513776659966, 0.01830979809165001, 0.03264119103550911, 0.003445266978815198, 0.055374693125486374, 0.0036986416671425104, -0.09270317852497101, -0.021397588774561882, -0.0125157246... | {16733: 7, 3399: 8, 1011: 13, 1037: 9, 2047: 3, 28033: 6, 6994: 2, 2005: 5, 1996: 23, 18440: 5, 10581: 5, 10074: 5, 2937: 2, 1012: 17, 4387: 1, 5097: 2, 2024: 7, 2649: 1, 2029: 3, 19141: 1, 6698: 1, 2000: 5, 21934: 1, 24759: 1, 9031: 1, 2015: 6, 1999: 5, 7300: 2, 1997: 19, 2152: 2, 3177: 1, 4895: 2, 25647: 2, 2100: 2, ... |
15 | on two-dimensional panel flutter . on two-dimensional panel flutter .
theory and experiments of the flutter of a buckled plate are
discussed . it is shown that an increase in the initial deviation
from flatness or a static pressure differential across the plate
raises the critical value of the /reduced velocity ./
... | [0.019483814015984535, 0.08785310387611389, -0.01551581360399723, -0.057818472385406494, -0.08571914583444595, -0.03100103698670864, -0.03962698578834534, 0.02052399143576622, -0.07097871601581573, -0.017566457390785217, 0.0454237274825573, 0.03367499262094498, 0.001328932587057352, 0.02151380106806755, -0.027619820088... | {2006: 2, 2048: 2, 1011: 2, 8789: 2, 5997: 2, 23638: 6, 1012: 8, 3399: 1, 1998: 4, 7885: 1, 1997: 12, 1996: 17, 1037: 4, 26368: 2, 5127: 5, 2024: 1, 6936: 1, 2009: 1, 2003: 2, 3491: 1, 2008: 1, 2019: 4, 3623: 1, 1999: 3, 3988: 1, 24353: 1, 2013: 1, 4257: 1, 2791: 1, 2030: 1, 10763: 1, 3778: 1, 11658: 1, 2408: 1, 13275:... |
16 | transformation of the compressible turbulent boundary
layer . transformation of the compressible turbulent boundary
layer .
the transformation of the compressible turbulent boundary-
layer equations to their incompressible equivalent is
demonstrated analytically . the transformation is essentially the same
as that f... | [-0.06507650762796402, 0.05281822010874748, 0.027777740731835365, 0.0032520098611712456, 0.033625148236751556, 0.015694232657551765, -0.041083790361881256, -0.04356784746050835, 0.08002088963985443, -0.07273705303668976, -0.053197648376226425, -0.05380278453230858, -0.018776625394821167, 0.005035694222897291, 0.0070338... | {8651: 6, 1997: 9, 1996: 22, 4012: 3, 20110: 3, 7028: 5, 22609: 4, 6192: 5, 6741: 5, 1012: 7, 1011: 3, 11380: 1, 2000: 4, 2037: 1, 4297: 2, 25377: 2, 8303: 2, 5662: 1, 2003: 5, 7645: 1, 17826: 1, 2135: 2, 7687: 1, 2168: 1, 2004: 1, 2008: 3, 2005: 1, 16983: 1, 3981: 1, 2099: 1, 1010: 4, 2034: 1, 2445: 1, 2011: 1, 5954: ... |
17 | remarks on the eddy viscosity in compressible mixing flows . remarks on the eddy viscosity in compressible mixing flows .
in connection with a study of the wakes behind bodies in hypersonic flow
carried out for the missile and space vehicle division of the general
electric company, it was desired to estimate the eddy v... | [-0.004534080158919096, 0.054399460554122925, 0.06003314256668091, 0.018996771425008774, 0.032148707658052444, -0.0004075636970810592, -0.06070204824209213, -0.034809790551662445, 0.06102347373962402, -0.075437530875206, -0.030501138418912888, -0.0288943350315094, 0.04614804685115814, -0.04908470809459686, 0.0157834663... | {12629: 2, 2006: 2, 1996: 15, 16645: 3, 25292: 3, 13186: 3, 3012: 3, 1999: 6, 4012: 5, 20110: 5, 7028: 7, 6809: 2, 6223: 4, 1012: 6, 4434: 1, 2007: 3, 1037: 1, 2817: 1, 1997: 7, 17507: 2, 2369: 1, 4230: 1, 23760: 1, 18585: 1, 4834: 1, 3344: 1, 2041: 1, 2005: 4, 7421: 1, 1998: 3, 2686: 1, 4316: 1, 2407: 1, 2236: 1, 3751... |
18 | the flow field in the diffuser of a radial compressor . the flow field in the diffuser of a radial compressor .
this note discusses the two-dimensional diffuser flow field
in a radial compressor outside the impeller wheel . it is
assumed that the diffuser has guide vanes arranged in a circular
row at a radius . the i... | [-0.06566868722438812, -0.023290148004889488, -0.08157161623239517, 0.005028183106333017, 0.057428743690252304, -0.035990264266729355, -0.062268100678920746, 0.0006395966629497707, 0.12054421007633209, -0.06889689713716507, 0.06528446823358536, 0.0936586782336235, 0.07057888060808182, -0.02908996306359768, -0.012059650... | {1996: 21, 4834: 7, 2492: 3, 1999: 8, 28105: 5, 2099: 5, 1997: 4, 1037: 6, 15255: 3, 29329: 3, 1012: 11, 2023: 2, 3602: 1, 15841: 1, 2048: 1, 1011: 1, 8789: 1, 2648: 1, 17727: 2, 24038: 2, 5217: 2, 2009: 1, 2003: 1, 5071: 1, 2008: 1, 2038: 2, 5009: 1, 23334: 1, 2015: 1, 5412: 1, 8206: 1, 5216: 1, 2012: 3, 12177: 4, 100... |
19 | an investigation of the pressure distribution on conical bodies in
hypersonic flows . an investigation of the pressure distribution on conical bodies in
hypersonic flows .
a large amount of work on conical flow fields without axial symmetry
at supersonic speed is presently available . however, no apparent
hypersonic a... | [0.08930215984582901, -0.004034729674458504, 0.02720244601368904, -0.08317771553993225, -0.048084672540426254, -0.04705622419714928, 0.007407048717141151, -0.01603684388101101, -7.17477769285324e-06, 0.0013974541798233986, 0.0010056083556264639, -0.009181211702525616, -0.0482458733022213, -0.010076568461954594, 0.00348... | {2019: 2, 4812: 2, 1997: 3, 1996: 2, 3778: 2, 4353: 2, 2006: 4, 24750: 3, 4230: 2, 1999: 3, 23760: 4, 18585: 5, 6223: 2, 1012: 5, 1037: 2, 2312: 1, 3815: 1, 2147: 1, 4834: 1, 4249: 1, 2302: 1, 26819: 1, 14991: 1, 2012: 2, 3565: 1, 3177: 1, 2003: 2, 12825: 1, 2800: 1, 2174: 1, 1010: 2, 2053: 1, 6835: 1, 20167: 1, 2038: ... |
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