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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...
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{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 ./ ...
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{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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