ADS NOT DISPLAYED TO REGISTERED USERS.
+ Reply to Thread
Results 1 to 6 of 6

Need Ki84 HAYATE's data!

Flight Test Data Discuss Need Ki84 HAYATE's data! in the Technical forums; Hello guys. I need some data to analyse the aircraft's ability. Actually, that is my final exam report I have ...

  1. #1
    Member Steven Que's Avatar
    Join Date
    Oct 2007
    Location
    Taiwan
    Posts
    38
    Country
    Taiwan

    Question Need Ki84 HAYATE's data!

    Hello guys.
    I need some data to analyse the aircraft's ability.
    Actually, that is my final exam report I have to prepare.
    Then I choose Ki84 Hayate to do my report.

    data in detail.
    about the gravity center's location. Aerodynamic center's location
    The airfoil's shape "NACA XXXX" or "NACA XXXXX"...



    Thanks. I hope someone will share me these data!

  2. #2
    Junior Member
    Join Date
    Mar 2007
    Location
    Brisbane
    Posts
    29
    Country
    Australia
    Airfoil was NN-21, work I have done in finding a NACA equivalent is based on data for NN series from Ki-27 maru book. Whilst not definitive it is the best I have been able to achieve given the few clues in text.

    Root was 16.5%, tip 8% NN-21.

    GoG / MAC location unknown at this time.

    Estimated shape is:-

    NN-21 16.5%
    1.00000 0.00172
    0.99679 0.00253
    0.99071 0.00401
    0.98314 0.00584
    0.97449 0.00790
    0.96538 0.01005
    0.95615 0.01220
    0.94683 0.01435
    0.93747 0.01648
    0.92812 0.01858
    0.91877 0.02066
    0.90939 0.02272
    0.89998 0.02475
    0.89057 0.02677
    0.88117 0.02876
    0.87178 0.03073
    0.86238 0.03267
    0.85295 0.03459
    0.84352 0.03649
    0.83409 0.03836
    0.82465 0.04021
    0.81520 0.04205
    0.80577 0.04386
    0.79638 0.04564
    0.78698 0.04738
    0.77755 0.04912
    0.76814 0.05084
    0.75871 0.05252
    0.74925 0.05419
    0.73981 0.05585
    0.73040 0.05746
    0.72089 0.05907
    0.71141 0.06066
    0.70198 0.06221
    0.69247 0.06373
    0.68294 0.06526
    0.67352 0.06675
    0.66416 0.06818
    0.65477 0.06961
    0.64537 0.07101
    0.63590 0.07240
    0.62641 0.07376
    0.61691 0.07510
    0.60749 0.07640
    0.59798 0.07768
    0.58850 0.07895
    0.57905 0.08017
    0.56952 0.08137
    0.56003 0.08254
    0.55052 0.08368
    0.54098 0.08481
    0.53154 0.08588
    0.52202 0.08693
    0.51254 0.08795
    0.50303 0.08893
    0.49348 0.08990
    0.48403 0.09082
    0.47453 0.09170
    0.46506 0.09255
    0.45559 0.09336
    0.44611 0.09412
    0.43660 0.09486
    0.42711 0.09556
    0.41767 0.09621
    0.40821 0.09682
    0.39873 0.09739
    0.38925 0.09792
    0.37985 0.09840
    0.37043 0.09882
    0.36097 0.09920
    0.35149 0.09954
    0.34213 0.09983
    0.33269 0.10006
    0.32330 0.10024
    0.31393 0.10037
    0.30457 0.10043
    0.29518 0.10043
    0.28585 0.10038
    0.27655 0.10026
    0.26722 0.10007
    0.25793 0.09982
    0.24866 0.09950
    0.23943 0.09911
    0.23019 0.09863
    0.22099 0.09808
    0.21177 0.09746
    0.20266 0.09677
    0.19369 0.09600
    0.18496 0.09513
    0.17634 0.09411
    0.16779 0.09294
    0.15925 0.09162
    0.15082 0.09016
    0.14246 0.08853
    0.13411 0.08674
    0.12585 0.08480
    0.11770 0.08271
    0.10964 0.08045
    0.10170 0.07804
    0.09386 0.07545
    0.08616 0.07270
    0.07858 0.06977
    0.07119 0.06669
    0.06401 0.06345
    0.05701 0.06004
    0.05030 0.05650
    0.04386 0.05283
    0.03780 0.04904
    0.03209 0.04517
    0.02688 0.04127
    0.02217 0.03740
    0.01806 0.03366
    0.01456 0.03013
    0.01169 0.02688
    0.00935 0.02395
    0.00749 0.02136
    0.00599 0.01908
    0.00481 0.01708
    0.00393 0.01525
    0.00319 0.01361
    0.00245 0.01219
    0.00187 0.01087
    0.00152 0.00957
    0.00125 0.00834
    0.00099 0.00719
    0.00051 0.00621
    0.00031 0.00513
    0.00023 0.00400
    0.00014 0.00289
    0.00008 0.00178
    0.00003 0.00069
    0.00001 -0.00036
    0.00006 -0.00142
    0.00012 -0.00250
    0.00020 -0.00358
    0.00027 -0.00466
    0.00036 -0.00573
    0.00075 -0.00667
    0.00113 -0.00765
    0.00137 -0.00877
    0.00166 -0.00995
    0.00207 -0.01114
    0.00274 -0.01231
    0.00345 -0.01361
    0.00419 -0.01507
    0.00511 -0.01662
    0.00631 -0.01824
    0.00780 -0.02002
    0.00959 -0.02193
    0.01179 -0.02397
    0.01444 -0.02613
    0.01762 -0.02837
    0.02141 -0.03069
    0.02581 -0.03303
    0.03088 -0.03536
    0.03657 -0.03762
    0.04287 -0.03979
    0.04970 -0.04185
    0.05698 -0.04377
    0.06462 -0.04553
    0.07264 -0.04716
    0.08091 -0.04866
    0.08946 -0.05004
    0.09817 -0.05130
    0.10707 -0.05248
    0.11605 -0.05356
    0.12525 -0.05457
    0.13453 -0.05553
    0.14382 -0.05643
    0.15325 -0.05727
    0.16278 -0.05810
    0.17235 -0.05891
    0.18195 -0.05970
    0.19149 -0.06047
    0.20091 -0.06120
    0.21018 -0.06186
    0.21938 -0.06242
    0.22863 -0.06291
    0.23794 -0.06333
    0.24722 -0.06368
    0.25661 -0.06397
    0.26596 -0.06420
    0.27534 -0.06438
    0.28471 -0.06449
    0.29412 -0.06455
    0.30359 -0.06457
    0.31302 -0.06454
    0.32245 -0.06445
    0.33199 -0.06432
    0.34146 -0.06416
    0.35091 -0.06395
    0.36044 -0.06369
    0.36994 -0.06341
    0.37946 -0.06308
    0.38898 -0.06272
    0.39854 -0.06232
    0.40809 -0.06189
    0.41763 -0.06143
    0.42719 -0.06094
    0.43676 -0.06042
    0.44635 -0.05987
    0.45590 -0.05930
    0.46550 -0.05869
    0.47511 -0.05807
    0.48468 -0.05743
    0.49427 -0.05676
    0.50379 -0.05607
    0.51337 -0.05535
    0.52296 -0.05462
    0.53256 -0.05387
    0.54218 -0.05310
    0.55179 -0.05231
    0.56139 -0.05150
    0.57100 -0.05068
    0.58055 -0.04985
    0.59010 -0.04900
    0.59964 -0.04814
    0.60925 -0.04725
    0.61886 -0.04635
    0.62849 -0.04544
    0.63810 -0.04451
    0.64774 -0.04357
    0.65740 -0.04262
    0.66704 -0.04166
    0.67666 -0.04068
    0.68629 -0.03970
    0.69587 -0.03870
    0.70543 -0.03769
    0.71499 -0.03669
    0.72460 -0.03566
    0.73424 -0.03461
    0.74388 -0.03356
    0.75349 -0.03250
    0.76310 -0.03142
    0.77272 -0.03035
    0.78226 -0.02927
    0.79176 -0.02817
    0.80124 -0.02709
    0.81079 -0.02597
    0.82042 -0.02484
    0.83003 -0.02371
    0.83962 -0.02255
    0.84921 -0.02140
    0.85877 -0.02023
    0.86836 -0.01905
    0.87795 -0.01787
    0.88755 -0.01666
    0.89718 -0.01545
    0.90681 -0.01422
    0.91641 -0.01299
    0.92602 -0.01174
    0.93563 -0.01048
    0.94524 -0.00921
    0.95478 -0.00794
    0.96423 -0.00667
    0.97360 -0.00539
    0.98257 -0.00415
    0.99042 -0.00307
    0.99670 -0.00220
    1.00000 -0.00174
    Last edited by peril; 04-29-2009 at 05:38 AM.

  3. #3
    Senior Member Shinpachi's Avatar
    Join Date
    Feb 2008
    Location
    Osaka
    Posts
    3,361
    Country
    Japan
    Hi peril!
    The coordinates you have provided are applied on my CAD software.
    Thanks for such a fantastic data.
    Attached Thumbnails Attached Thumbnails Need Ki84 HAYATE's data!-nn-21.jpg  

  4. #4
    Senior Member
    Join Date
    Oct 2006
    Posts
    1,766
    Hi Peril,

    Have you managed to genrate a polar from the coordinates? I've been toying around with Javafoil, but without results :-/

    Regards,

    Henning (HoHun)

  5. #5
    Junior Member
    Join Date
    Mar 2007
    Location
    Brisbane
    Posts
    29
    Country
    Australia
    I set Javafoil polars to transition model 'xfoil after 1991'.

    I usually have no problems getting results, ensure closed trailing edge.

    If still having issues play with reducing max number of plotted points.

  6. #6
    Member Steven Que's Avatar
    Join Date
    Oct 2007
    Location
    Taiwan
    Posts
    38
    Country
    Taiwan
    HI Peril,
    I wonder the coefficient of lift with NN-21 when AOA is 0 degree
    I can not find out the data from my program
    which have more than 300 airfoil's data
    But have no data of NN-21...

    Thanks

+ Reply to Thread

Bookmarks

Posting Permissions

  • You may not post new threads
  • You may not post replies
  • You may not post attachments
  • You may not edit your posts

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86