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PERSON · STARLIGHT
Ludwig Prandtl
Recorded name: 路德维希·普朗特
Ludwig Prandtl was a German researcher in fluid mechanics and aerodynamics who held a long-term post in Göttingen.
Original Chinese introduction
路德维希·普朗特是德国流体力学与空气动力学研究者，长期任职于哥廷根。
Prandtl was a researcher in fluid mechanics and aerodynamics who organized theory and experiments in Göttingen over a long period. He used the boundary-layer concept to explain viscous-flow and drag problems, and also participated in the development of finite-wing theory, turbulence models, and wind-tunnel research. The results of Göttingen AVA came from the joint labor of scientists, engineers, technicians, and publishing staff; these institutions also participated in Germany's wartime aviation research.
Original Chinese context
普朗特是流体力学与空气动力学研究者，长期在哥廷根组织理论和实验。他以边界层思路解释黏性流动与阻力问题，也参与有限翼理论、湍流模型和风洞研究的发展。哥廷根 AVA 的成果来自科学家、工程师、技术员与出版人员的共同劳动，这些机构也参与了德国的战时航空研究。
Introduction sources
- Max Planck Institute for Dynamics and Self-Organization: History ↗Original Chinese label · 马克斯·普朗克动力学与自组织研究所：历史
- Göttingen University Press: AVA Research Results ↗Original Chinese label · 哥廷根大学出版社：AVA研究成果
- DLR: Historical Documents on the Göttingen AVA ↗Original Chinese label · DLR：哥廷根AVA历史文献
Derived from the current score.
Contribution groups assessed so far; coverage is still being expanded.
ASSESSMENT SCOPEWhat this score covers
All included contribution titles and notes are available in English. The complete original text remains available in Chinese; both editions use the same scores and source links.
Uncovered contributions and unresolved harms are not treated as zero. This is not a complete assessment of a lifetime.
3 included contributions have incomplete evidence; the relevant gap appears with that contribution.
Original scope note
This research record currently includes 3 outcomes within a limited scope; M and attribution shares are revisable judgments. Uncovered content and negative effects not yet clarified are not treated as zero; specific gaps appear in the item-by-item explanations.
Original Chinese scope
本轮当前已列3项有限研究账；M与归功份额为可修订判断。未覆盖内容和未核清的负面作用不按零处理，具体缺口见逐项说明。
CALCULATIONHow the score is calculated
Q = 10^(M/2) − 1; Lᵢ = aᵢ × Qᵢ; L = Σ Lᵢ; S = 2 × log₁₀(1 + L).
M is an outcome’s assessed magnitude and a is the person’s allocated share. A standalone score is only a per-item reference; the attributed light from distinct contributions is what can be combined.
SCORE DETAILS
3 evaluated contributions
M is the assessed magnitude of an outcome; attribution is the person’s share of credit. Attributed light can be added. The standalone score is only a per-item reference and must not be added across rows.
Scroll sideways for scores and attribution.
| Outcome | M | Attribution share | Attributed light | Standalone score | Share of total | Status |
|---|---|---|---|---|---|---|
| 01Boundary-Layer Decomposition and a Computable Framework for Real Viscous Flow边界层分解与真实黏性流动的可计算框架OUT-SL0078-1904-1920-BOUNDARY-LAYER-FLUID-MECHANICS · 1904 | 6.6 | 34% | 678.049187 | 5.66 | 54.7493% | Provisional estimate · incomplete evidence |
| 02Finite-Wing Lift-Line, Induced Drag, and Minimum-Drag Analysis有限翼升力线、诱导阻力与最小阻力分析OUT-SL0078-1918-1933-LIFTING-LINE-AND-INDUCED-DRAG-THEORY · 1918 | 6.2 | 25% | 314.481353 | 5.00 | 25.3929% | Provisional estimate · incomplete evidence |
| 03Engineering Closure Model for Turbulent Mixing Length湍流混合长的工程闭合模型OUT-SL0078-1925-1945-TURBULENCE-MIXING-LENGTH-MODEL · 1925 | 5.8 | 31% | 245.931753 | 4.79 | 19.8578% | Provisional estimate · incomplete evidence |
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NOTES AND SOURCES
Contribution notes and source links
English translations of the included notes appear below, with their Chinese originals available for comparison.
01Boundary-Layer Decomposition and a Computable Framework for Real Viscous Flow边界层分解与真实黏性流动的可计算框架OUT-SL0078-1904-1920-BOUNDARY-LAYER-FLUID-MECHANICS
Record year1904
Original Chinese · record year
1904
summaryRecognizing that viscous effects are concentrated in a thin near-wall region, allowing outer flow and the boundary layer to be separated and analyzed in a coupled manner, forming a computable path connecting theoretical equations and experimental flows.
Original Chinese · summary
识别黏性效应集中在薄近壁区域，使外流与边界层可分而耦合分析，形成连接理论方程与实验流动的可计算路径。
M rationaleNASA historical records confirm that the 1904 paper proposed a two-region coupled solution to the drag paradox and gave the boundary-layer equations; MPI confirms its central status. It is assigned M6.6 for foundational method, computability, and broad reuse.
Original Chinese · M rationale
NASA历史资料明确1904论文针对阻力悖论提出两区耦合解并给边界层方程，MPI确认其核心地位。按基础方法、可计算性和广泛复用取M6.6。
attribution rationalePrandtl .34, student experimental team .16, prehistory of fluid mechanics .22, institutions .08, unresolved .20.
Original Chinese · attribution rationale
Prandtl .34，学生实验团队 .16，流体力学前史 .22，机构 .08，未解析 .20。
overlap boundaryThe boundary-layer approximation proposed in 1904 and subsequently developed through research in Göttingen: coupling the near-wall viscous region with externally approximately inviscid flow to explain real flow such as drag and separation; it does not claim all modern fluid mechanics, numerical simulation, or engineering applications.
Original Chinese · overlap boundary
1904提出、随后由哥廷根研究展开的边界层近似：把近壁黏性区域与外部近似无黏流动耦合，以解释阻力、分离等真实流动；不领取所有现代流体力学、数值模拟或工程应用。
Evidence gapsThe specific assumptions in the original 1904 paper and contemporary preceding concepts still require paragraph-by-paragraph verification; the individual division of work in students' early solutions and experimental verification remains unresolved.
Original Chinese · evidence gaps
1904原文的具体假设与同期先行概念仍需逐段核。；学生早期解和实验验证的个人分工未闭合。
Full attribution budget
Every recorded actor remains visible. Share (0–1) retains the ledger’s exact decimal value.
- 0.34Ludwig PrandtlOriginal Chinese · 路德维希·普朗特Person
- 0.16Göttingen boundary-layer students and experimental personnelOriginal Chinese · 哥廷根边界层学生与实验人员Team
- 0.22Navier–Stokes viscosity and precursors to d'Alembert's paradoxOriginal Chinese · Navier–Stokes黏性与达朗贝尔悖论前驱Predecessor pool
- 0.08University of Göttingen and fluid-flow research institutionsOriginal Chinese · 哥廷根大学与流动研究机构Institution
- 0.2Unresolved Prandtl boundary-layer contributionsOriginal Chinese · 未解析的Prandtl边界层贡献Unallocated
Source links
- Papers, patents, and institutional records: www1.grc.nasa.gov ↗Original Chinese label · 论文、专利与机构资料：www1.grc.nasa.gov
- Papers, patents, and institutional records: ntrs.nasa.gov ↗Original Chinese label · 论文、专利与机构资料：ntrs.nasa.gov
- Papers, patents, and institutional records: www.ds.mpg.de ↗Original Chinese label · 论文、专利与机构资料：www.ds.mpg.de
02Finite-Wing Lift-Line, Induced Drag, and Minimum-Drag Analysis有限翼升力线、诱导阻力与最小阻力分析OUT-SL0078-1918-1933-LIFTING-LINE-AND-INDUCED-DRAG-THEORY
Record year1918
Original Chinese · record year
1918
summaryIntegrating the finite-wing concept into a complete mathematical model, enabling calculation of spanwise lift distribution, induced drag, and optimization conditions, and combining it with experimental research.
Original Chinese · summary
把有限翼概念吸收到完整数学模型，可计算翼展升力分布、诱导阻力及优化条件，并与实验研究结合。
M rationaleNASA's original technical-report catalogue and historical review identify Prandtl's published lifting-surface model, while emphasizing Lanchester's prior work and the important contributions of Munk and Betz. It is assigned M6.2 for independent mathematical integration, computable outputs, and lasting utility.
Original Chinese · M rationale
NASA原始技术报告目录和历史回顾明确Prandtl公开升力面模型，同时强调Lanchester前史及Munk、Betz重要贡献。按独立数学整合、可计算输出和持久工具性取M6.2。
attribution rationalePrandtl .25, Munk/Betz .20, team .13, prehistory .22, institutions .06, unresolved .14.
Original Chinese · attribution rationale
Prandtl .25，Munk/Betz .20，团队 .13，前史 .22，机构 .06，未解析 .14。
overlap boundaryThe 1918–1933 finite-wing lift-line model, induced-drag calculation, and minimum-induced-drag wing-loading analysis; M is not duplicated by paper, airfoil, or aircraft project, and the boundary layer's near-wall viscous framework is not repeated.
Original Chinese · overlap boundary
1918–1933有限翼升力线模型、诱导阻力计算与最小诱导阻力翼载分析；不按论文、翼型或飞机项目复制，也不重复边界层的近壁黏性框架。
Evidence gapsThe specific shares of Prandtl, Munk, and Betz in the various theorems and calculations require further decomposition from original historical sources; the mutually exclusive increment between the 1933 second minimum-drag scheme and the 1920 model has not been calibrated separately.
Original Chinese · evidence gaps
Prandtl、Munk、Betz在各定理和计算中的具体份额需原文史进一步分解。；1933第二最小阻力方案与1920模型的互斥增量尚未单独校准。
Full attribution budget
Every recorded actor remains visible. Share (0–1) retains the ledger’s exact decimal value.
- 0.25Ludwig PrandtlOriginal Chinese · 路德维希·普朗特Person
- 0.2Max Munk and Albert BetzOriginal Chinese · Max Munk与Albert BetzTeam
- 0.13Göttingen wing-theory and experimental teamOriginal Chinese · 哥廷根翼理论与实验团队Team
- 0.22Lanchester, Kutta, Joukowski, and vortex-theory precursorsOriginal Chinese · Lanchester、Kutta、Joukowski与涡理论前驱Predecessor pool
- 0.06Göttingen AVA and NACA publishing institutionsOriginal Chinese · 哥廷根AVA与NACA出版机构Institution
- 0.14Unresolved Prandtl wing-theory contributionsOriginal Chinese · 未解析的Prandtl翼理论贡献Unallocated
Source links
- Papers, patents, and institutional records: ntrs.nasa.gov ↗Original Chinese label · 论文、专利与机构资料：ntrs.nasa.gov
- Papers, patents, and institutional records: ntrs.nasa.gov ↗Original Chinese label · 论文、专利与机构资料：ntrs.nasa.gov
- Papers, patents, and institutional records: ntrs.nasa.gov ↗Original Chinese label · 论文、专利与机构资料：ntrs.nasa.gov
03Engineering Closure Model for Turbulent Mixing Length湍流混合长的工程闭合模型OUT-SL0078-1925-1945-TURBULENCE-MIXING-LENGTH-MODEL
Record year1925
summaryUsing a macroscopic mixing distance to link unresolved turbulent transport with mean velocity gradients, providing a simple but empirically dependent closure approximation.
Original Chinese · summary
用宏观混合距离把未解析湍流输运与平均速度梯度联系，提供简单但经验依赖的闭合近似。
M rationaleNASA's technical review identifies the 1925 mixing-length model as an early successful zero-equation model and records its empirical dependence and range of use. It is assigned M5.8 for a computable engineering model and lasting reuse; limitations are included in the scope rather than concealed.
Original Chinese · M rationale
NASA技术回顾明确1925混合长模型是早期成功零方程模型并记录其经验依赖和使用范围。按可计算工程模型与持久复用取M5.8，局限进入范围而非隐去。
attribution rationalePrandtl .31, team .18, prehistory .24, institutions .07, unresolved .20.
Original Chinese · attribution rationale
Prandtl .31，团队 .18，前史 .24，机构 .07，未解析 .20。
overlap boundaryThe 1925 mixing-length idea and its established form as an approximate closure model for shear turbulence; only the high-level model and engineering computability are counted, without claiming all turbulence theory, empirical constants, or modern CFD.
Original Chinese · overlap boundary
1925混合长思想及其作为剪切湍流近似闭合模型的知识终态；只计高层模型和工程可计算性，不领取全部湍流理论、经验常数或现代CFD。
Evidence gapsThe 1925 original text has not yet been read paragraph by paragraph, and the model idea and team experimental inputs still require disaggregation; success and failure ranges for different flow types have not been systematically evaluated.
Original Chinese · evidence gaps
1925原文尚未逐段审读，模型思想与团队实验输入仍需细分。；不同流动类型的成功/失败范围未系统评价。
Full attribution budget
Every recorded actor remains visible. Share (0–1) retains the ledger’s exact decimal value.
- 0.31Ludwig PrandtlOriginal Chinese · 路德维希·普朗特Person
- 0.18Göttingen turbulence experimental and theoretical teamOriginal Chinese · 哥廷根湍流实验与理论团队Team
- 0.24Boussinesq, Reynolds, and turbulence-theory precursorsOriginal Chinese · Boussinesq、Reynolds与湍流理论前驱Predecessor pool
- 0.07Göttingen flow-research institutionsOriginal Chinese · 哥廷根流动研究机构Institution
- 0.2Unresolved Prandtl turbulence contributionsOriginal Chinese · 未解析的Prandtl湍流贡献Unallocated
Source links
- Papers, patents, and institutional records: ntrs.nasa.gov ↗Original Chinese label · 论文、专利与机构资料：ntrs.nasa.gov
- Papers, patents, and institutional records: ntrs.nasa.gov ↗Original Chinese label · 论文、专利与机构资料：ntrs.nasa.gov
- Papers, patents, and institutional materials: onlinelibrary.wiley.com ↗Original Chinese label · 论文、专利与机构资料：onlinelibrary.wiley.com
BOUNDARIES NOT COUNTED
Not included in this score
These subjects are recorded as exclusions and are not silently treated as zero or as part of the included outcomes.
1907–1945 MVA/AVA Experimental Research Organization and Military Continuity through Two World Wars
1907–1945 MVA/AVA实验研究组织与两次世界大战军用连续性
Reason The original candidate called 1907–1932 “pre-war” and excluded only 1939–45, an untenable time boundary. Official DLR history records that MVA expansion was decided in 1915 to meet growing wartime demand and a new wind tunnel began operation in 1917; the 2026 historical review further defines 1918–33 as military-civil aviation research and rearmament continuity. MPI history further states that after 1933 Prandtl gradually directed the institute's basic research toward military applications. Experimental facilities, lift-and-drag data, institutional organization, and military contracts form one continuous MVA/AVA results chain. Existing materials cannot reliably separate divisible net civilian benefit from military deliveries in the two wars; therefore the entire organizational-service entry does not enter positive brightness pending verification of net positive benefit and individual responsibility. The original M5.5 and budget remain only as a withdrawn candidate and are not for adoption.
Original Chinese reason
原候选把1907–1932称“战前”并仅排除1939–45，时间边界不成立。DLR官方史记载1915为满足战争增长需求决定扩建MVA、1917新风洞投用；2026历史重审又将1918–33明确界为军民航空研究及再武装连续性。MPI史进一步称1933后Prandtl逐渐把研究所基础研究导向军事应用。实验设施、升阻数据、机构组织与军用合同在同一MVA/AVA连续成果链中，现有资料不能把可分的民用净受益从两次战争军用交付可靠剥离，故整个组织服务点不进入正向亮度，待核净正与个人责任。原M5.5及预算仅保留为撤回前候选，不供采用。
Teaching and Göttingen-School Training Service
教学与哥廷根学派培养服务
Reason Student contributions have already entered the budgets for specific theory/institution entries, but position and school reputation cannot substitute for evidence of curriculum, guidance, or institutional delivery.
Original Chinese reason
学生贡献已进入具体理论/机构点预算，但职位和学派声誉不能替代课程、指导或制度交付证据。
How to read this score
Scores can change when evidence is reviewed. The method page explains how magnitude, attribution, and included results relate to the displayed score.
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