{
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  "name": "路德维希·普朗特",
  "version": "V2研究贡献账",
  "updatedAt": "2026-09-15",
  "formula": {
    "q": "Q = 10^(M/2) − 1",
    "light": "Lᵢ = aᵢ × Qᵢ",
    "total": "L = Σ Lᵢ",
    "score": "S = 2 × log₁₀(1 + L)"
  },
  "scopeNote": "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。",
  "exclusions": [
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      "id": "PRANDTL-AVA-RESEARCH-PROGRAM-1907-1945",
      "title": "1907–1945 MVA/AVA实验研究组织与两次世界大战军用连续性",
      "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。"
    },
    {
      "id": "PRANDTL-TEACHING-AND-SCHOOL-SERVICE",
      "title": "教学与哥廷根学派培养服务",
      "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。"
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      "title": "边界层分解与真实黏性流动的可计算框架",
      "year": "1904",
      "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。",
      "mReason": "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。",
      "aReason": "Prandtl .34，学生实验团队 .16，流体力学前史 .22，机构 .08，未解析 .20。",
      "sources": [
        {
          "label": "论文、专利与机构资料：www1.grc.nasa.gov",
          "url": "https://www1.grc.nasa.gov/beginners-guide-to-aeronautics/boundary-layer/"
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          "label": "论文、专利与机构资料：ntrs.nasa.gov",
          "url": "https://ntrs.nasa.gov/citations/20150019333"
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        {
          "label": "论文、专利与机构资料：www.ds.mpg.de",
          "url": "https://www.ds.mpg.de/history"
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      "missing": "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。",
      "status": "缺证暂估",
      "overlapNote": "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。",
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      "id": "OUT-SL0078-1918-1933-LIFTING-LINE-AND-INDUCED-DRAG-THEORY",
      "title": "有限翼升力线、诱导阻力与最小阻力分析",
      "year": "1918",
      "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。",
      "mReason": "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。",
      "aReason": "Prandtl .25，Munk/Betz .20，团队 .13，前史 .22，机构 .06，未解析 .14。",
      "sources": [
        {
          "label": "论文、专利与机构资料：ntrs.nasa.gov",
          "url": "https://ntrs.nasa.gov/citations/19930080806"
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          "label": "论文、专利与机构资料：ntrs.nasa.gov",
          "url": "https://ntrs.nasa.gov/citations/19930091180"
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      "status": "缺证暂估",
      "overlapNote": "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。",
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        {
          "actor": "Max Munk与Albert Betz",
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        {
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          "actorId": "LUDWIG-PRANDTL::LANCHESTER-KUTTA-JOUKOWSKI-AND-VORTEX-THEORY-PREDECESSORS",
          "type": "PREDECESSOR_POOL",
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        },
        {
          "actor": "哥廷根AVA与NACA出版机构",
          "actorId": "LUDWIG-PRANDTL::GOTTINGEN-AVA-AND-NACA-PUBLICATION-INSTITUTIONS",
          "type": "INSTITUTION",
          "share": "0.06"
        },
        {
          "actor": "未解析的Prandtl翼理论贡献",
          "actorId": "LUDWIG-PRANDTL::UNRESOLVED-PRANDTL-WING-THEORY-ATTRIBUTION",
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    {
      "id": "OUT-SL0078-1925-1945-TURBULENCE-MIXING-LENGTH-MODEL",
      "title": "湍流混合长的工程闭合模型",
      "year": "1925",
      "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。",
      "mReason": "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。",
      "aReason": "Prandtl .31，团队 .18，前史 .24，机构 .07，未解析 .20。",
      "sources": [
        {
          "label": "论文、专利与机构资料：ntrs.nasa.gov",
          "url": "https://ntrs.nasa.gov/api/citations/19900010222/downloads/19900010222.pdf"
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        {
          "label": "论文、专利与机构资料：onlinelibrary.wiley.com",
          "url": "https://onlinelibrary.wiley.com/doi/10.1002/zamm.19250050212"
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      "missing": "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。",
      "status": "缺证暂估",
      "overlapNote": "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。",
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