AirfoilShapes

Document Sample
AirfoilShapes Powered By Docstoc
					  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00270 0.00733   0.00000 -0.00017
0.00990 0.01572   0.00297 -0.00614
0.02171 0.02442   0.01222 -0.01126
0.03807 0.03324   0.02709 -0.01610
0.05881 0.04194   0.04741 -0.02056
0.08375 0.05034   0.07289 -0.02472
0.11264 0.05830   0.10317 -0.02859
                                                                          S805 Airfoil
0.14520 0.06567   0.13783 -0.03215         0.2
0.18106 0.07233   0.17642 -0.03537
0.21985 0.07814   0.21848 -0.03821
0.26114 0.08298   0.26348 -0.04061
0.30449 0.08671   0.31089 -0.04251         0.1
0.34943 0.08921   0.36019 -0.04387
0.39546 0.09034   0.41082 -0.04464
0.44206 0.08993   0.46221 -0.04478


                                     y/c
0.48868 0.08752   0.51378 -0.04427         0.0
0.53555 0.08243   0.56495 -0.04305
0.58348 0.07514   0.61515 -0.04109
0.63223 0.06698   0.66379 -0.03823
0.68075 0.05869   0.71050 -0.03427         -0.1
0.72813 0.05057   0.75510 -0.02913
0.77354 0.04283   0.79762 -0.02282
0.81621 0.03557   0.83830 -0.01599
0.85544 0.02882   0.87666 -0.00978         -0.2
0.89061 0.02253   0.91159 -0.00492                0.0   0.1   0.2   0.3   0.4
0.92134 0.01649   0.94199 -0.00164
0.94764 0.01078   0.96683 0.00005
0.96934 0.00590   0.98516 0.00046
0.98588 0.00240   0.99629 0.00020
0.99638 0.00053   1.00000 0.00000
1.00000 0.00000
S805 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00037 0.00275   0.00140 -0.00498
0.00575 0.01166   0.00933 -0.01272
0.01626 0.02133   0.02321 -0.02162
0.03158 0.03136   0.04223 -0.03144
0.05147 0.04143   0.06579 -0.04199
0.07568 0.05132   0.09325 -0.05301
0.10390 0.06082   0.12397 -0.06408
                                                                          S809 Airfoil
0.13580 0.06972   0.15752 -0.07467         0.2
0.17103 0.07786   0.19362 -0.08447
0.20920 0.08505   0.23175 -0.09326
0.24987 0.09113   0.27129 -0.10060
0.29259 0.09594   0.31188 -0.10589         0.1
0.33689 0.09933   0.35328 -0.10866
0.38223 0.10109   0.39541 -0.10842
0.42809 0.10101   0.43832 -0.10484


                                     y/c
0.47384 0.09843   0.48234 -0.09756         0.0
0.52005 0.09237   0.52837 -0.08697
0.56801 0.08356   0.57663 -0.07442
0.61747 0.07379   0.62649 -0.06112
0.66718 0.06403   0.67710 -0.04792         -0.1
0.71606 0.05462   0.72752 -0.03558
0.76314 0.04578   0.77668 -0.02466
0.80756 0.03761   0.82348 -0.01559
0.84854 0.03017   0.86677 -0.00859         -0.2
0.88537 0.02335   0.90545 -0.00370                0.0   0.1   0.2   0.3   0.4
0.91763 0.01694   0.93852 -0.00075
0.94523 0.01101   0.96509 0.00054
0.96799 0.00600   0.98446 0.00065
0.98528 0.00245   0.99612 0.00024
0.99623 0.00054   1.00000 0.00000
1.00000 0.00000
S809 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00116 0.00703   0.00048 -0.00470
0.00830 0.01892   0.00607 -0.01746
0.02064 0.03130   0.01644 -0.03159
0.03771 0.04378   0.03097 -0.04646
0.05918 0.05608   0.04923 -0.06162
0.08475 0.06791   0.07077 -0.07662
0.11409 0.07903   0.09515 -0.09096
                                                                          S814 Airfoil
0.14685 0.08921   0.12193 -0.10412         0.2
0.18266 0.09821   0.15072 -0.11545
0.22111 0.10580   0.18122 -0.12425
0.26177 0.11175   0.21322 -0.12971
0.30418 0.11564   0.24712 -0.13079         0.1
0.34829 0.11696   0.28389 -0.12736
0.39439 0.11573   0.32394 -0.11990
0.44237 0.11251   0.36753 -0.10887


                                     y/c
0.49169 0.10775   0.41483 -0.09511         0.0
0.54177 0.10173   0.46552 -0.07962
0.59199 0.09473   0.51909 -0.06328
0.64174 0.08698   0.57485 -0.04703
0.69037 0.07873   0.63189 -0.03173         -0.1
0.73723 0.07016   0.68912 -0.01818
0.78169 0.06146   0.74529 -0.00701
0.82312 0.05276   0.79901 0.00134
0.86095 0.04417   0.84887 0.00671          -0.2
0.89460 0.03567   0.89348 0.00917                 0.0   0.1   0.2   0.3   0.4
0.92380 0.02706   0.93154 0.00910
0.94879 0.01848   0.96197 0.00701
0.96963 0.01071   0.98364 0.00377
0.98582 0.00470   0.99606 0.00102
0.99632 0.00112   1.00000 0.00000
1.00000 0.00000
S814 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00057 0.00537   0.00110 -0.00764
0.00658 0.01777   0.00741 -0.02242
0.01821 0.03072   0.01808 -0.03839
0.03475 0.04381   0.03268 -0.05497
0.05579 0.05671   0.05083 -0.07167
0.08099 0.06913   0.07213 -0.08804
0.11003 0.08082   0.09618 -0.10358
                                                                          S815 Airfoil
0.14253 0.09152   0.12257 -0.11776         0.2
0.17811 0.10101   0.15092 -0.12995
0.21637 0.10902   0.18094 -0.13947
0.25688 0.11531   0.21239 -0.14548
0.29916 0.11947   0.24569 -0.14690         0.1
0.34317 0.12093   0.28191 -0.14360
0.38927 0.11972   0.32148 -0.13627
0.43735 0.11645   0.36439 -0.12537


                                     y/c
0.48685 0.11157   0.41069 -0.11151         0.0
0.53719 0.10540   0.46020 -0.09549
0.58773 0.09821   0.51257 -0.07811
0.63784 0.09024   0.56728 -0.06032
0.68686 0.08175   0.62362 -0.04304         -0.1
0.73414 0.07294   0.68061 -0.02724
0.77902 0.06397   0.73706 -0.01371
0.82087 0.05500   0.79160 -0.00312
0.85909 0.04613   0.84270 0.00417          -0.2
0.89307 0.03733   0.88881 0.00809                 0.0   0.1   0.2   0.3   0.4
0.92258 0.02838   0.92844 0.00894
0.94785 0.01943   0.96029 0.00725
0.96899 0.01127   0.98298 0.00400
0.98548 0.00495   0.99592 0.00109
0.99623 0.00118   1.00000 0.00000
1.00000 0.00000
S815 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00000 0.00009   0.00019 -0.00158
0.00023 0.00198   0.00093 -0.00314
0.00302 0.00863   0.00220 -0.00475
0.01099 0.01818   0.00368 -0.00620
0.02379 0.02836   0.01412 -0.01294
0.04125 0.03888   0.03050 -0.01988
0.06315 0.04950   0.05260 -0.02698
                                                                          S816 Airfoil
0.08920 0.06005   0.08019 -0.03456         0.2
0.11901 0.07033   0.11247 -0.04309
0.15222 0.08009   0.14831 -0.05249
0.18843 0.08912   0.18682 -0.06232
0.22723 0.09720   0.22730 -0.07231         0.1
0.26818 0.10411   0.26846 -0.08222
0.31082 0.10965   0.30881 -0.09050
0.35467 0.11360   0.34877 -0.09483


                                     y/c
0.39923 0.11569   0.39005 -0.09470         0.0
0.44398 0.11547   0.43340 -0.09089
0.48900 0.11217   0.47890 -0.08411
0.53503 0.10591   0.52644 -0.07515
0.58217 0.09767   0.57555 -0.06477         -0.1
0.62982 0.08824   0.62567 -0.05360
0.67730 0.07811   0.67615 -0.04229
0.72392 0.06774   0.72622 -0.03146
0.76893 0.05749   0.77501 -0.02165         -0.2
0.81158 0.04763   0.82154 -0.01331                0.0   0.1   0.2   0.3   0.4
0.85113 0.03838   0.86477 -0.00676
0.88685 0.02976   0.90364 -0.00216
0.91827 0.02165   0.93713 0.00052
0.94534 0.01412   0.96426 0.00150
0.96784 0.00776   0.98412 0.00118
0.98512 0.00320   0.99605 0.00038
0.99617 0.00072       1        0
    1        0
S816 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00010 0.00117   0.00001 -0.00038
0.00036 0.00243   0.00029 -0.00169
0.00443 0.01001   0.00107 -0.00285
0.01313 0.01841   0.00235 -0.00398
0.02661 0.02718   0.00925 -0.00755
0.04479 0.03620   0.02330 -0.01157
0.06748 0.04533   0.04329 -0.01517
                                                                          S817 Airfoil
0.09441 0.05445   0.06911 -0.01857         0.2
0.12517 0.06342   0.10030 -0.02217
0.15941 0.07203   0.13611 -0.02613
0.19672 0.08010   0.17584 -0.03033
0.23667 0.08746   0.21884 -0.03464         0.1
0.27883 0.09392   0.26447 -0.03891
0.32273 0.09934   0.31211 -0.04294
0.36790 0.10355   0.36113 -0.04655


                                     y/c
0.41384 0.10640   0.41092 -0.04952         0.0
0.46005 0.10771   0.46088 -0.05162
0.50602 0.10727   0.51041 -0.05260
0.55134 0.10473   0.55893 -0.05200
0.59585 0.09969   0.60634 -0.04913         -0.1
0.63984 0.09191   0.65317 -0.04392
0.68387 0.08192   0.69967 -0.03701
0.72779 0.07087   0.74564 -0.02924
0.77085 0.05960   0.79051 -0.02150         -0.2
0.81221 0.04865   0.83342 -0.01447                0.0   0.1   0.2   0.3   0.4
0.85106 0.03842   0.87341 -0.00861
0.88653 0.02908   0.90948 -0.00420
0.91803 0.02060   0.94065 -0.00132
0.94528 0.01309   0.96599 0.00013
0.96792 0.00701   0.98470 0.00046
0.98522 0.00281   0.99615   0.0002
0.99621 0.00061       1        0
    1        0
S817 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00002 0.00077   0.00006 -0.00125
0.00101 0.00556   0.00056 -0.00298
0.00673 0.01572   0.00177 -0.00455
0.01719 0.02663   0.00372 -0.00622
0.03213 0.03768   0.00891 -0.00986
0.05143 0.04852   0.02445 -0.02021
0.07486 0.05890   0.04415 -0.03323
                                                                          S819 Airfoil
0.10216 0.06858   0.06692 -0.04746         0.2
0.13302 0.07733   0.09234 -0.06201
0.16709 0.08491   0.11997 -0.07614
0.20398 0.09099   0.14948 -0.08914
0.24355 0.09516   0.18049 -0.10033         0.1
0.28581 0.09736   0.21265 -0.10864
0.33053 0.09777   0.24658 -0.11280
0.37732 0.09651   0.28355 -0.11284


                                     y/c
0.42580 0.09369   0.32385 -0.10966         0.0
0.47552 0.08949   0.36718 -0.10375
0.52602 0.08411   0.41332 -0.09557
0.57678 0.07780   0.46189 -0.08562
0.62723 0.07078   0.51244 -0.07440         -0.1
0.67679 0.06331   0.56446 -0.06247
0.72481 0.05561   0.61728 -0.05039
0.77067 0.04792   0.67018 -0.03869
0.81370 0.04039   0.72231 -0.02789         -0.2
0.85327 0.03316   0.77274 -0.01843                0.0   0.1   0.2   0.3   0.4
0.88875 0.02622   0.82050 -0.01064
0.91979 0.01940   0.86454 -0.00473
0.94642 0.01282   0.90387 -0.00075
0.96851 0.00712   0.93753 0.00141
0.98545 0.00295   0.96464 0.00197
0.99626 0.00066   0.98437 0.00136
    1        0    0.99613 0.00042
                      1        0
S819 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00013 0.00133   0.00001 -0.00041
0.00364 0.00910   0.00032 -0.00178
0.01172 0.01811   0.00117 -0.00300
0.02425 0.02758   0.00258 -0.00423
0.04120 0.03708   0.01207 -0.00946
0.06255 0.04637   0.02754 -0.01514
0.08815 0.05531   0.04834 -0.02097
                                                                          S820 Airfoil
0.11774 0.06379   0.07403 -0.02684         0.2
0.15102 0.07167   0.10419 -0.03260
0.18764 0.07884   0.13841 -0.03813
0.22719 0.08520   0.17622 -0.04330
0.26923 0.09063   0.21715 -0.04798         0.1
0.31330 0.09501   0.26072 -0.05203
0.35891 0.09825   0.30638 -0.05533
0.40555 0.10022   0.35360 -0.05772


                                     y/c
0.45272 0.10079   0.40183 -0.05903         0.0
0.49988 0.09978   0.45050 -0.05900
0.54666 0.09688   0.49923 -0.05721
0.59300 0.09196   0.54807 -0.05340
0.63875 0.08518   0.59707 -0.04785         -0.1
0.68373 0.07668   0.64604 -0.04093
0.72795 0.06688   0.69476 -0.03316
0.77109 0.05656   0.74277 -0.02532
0.81244 0.04635   0.78923 -0.01803         -0.2
0.85123 0.03666   0.83325 -0.01172                0.0   0.1   0.2   0.3   0.4
0.88668 0.02775   0.87388 -0.00668
0.91818 0.01962   0.91020 -0.00304
0.94544 0.01242   0.94132 -0.00077
0.96806 0.00661   0.96644 0.00029
0.98531 0.00263   0.98490 0.00047
0.99624 0.00057    0.9962   0.0002
    1        0        1        0
S820 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
 Upper Surface     Lower Surface
 x/c       y/c     x/c       y/c
0.00004 0.00203   0.00001 -0.00076
0.00037 0.00550   0.00243 -0.01654
0.00110 0.00874   0.00887 -0.03393
0.00234 0.01186   0.01876 -0.05219
0.00405 0.01499   0.03170 -0.07058
0.01212 0.02520   0.04745 -0.08838
0.02684 0.03773   0.06576 -0.10493
                                                                          S821 Airfoil
0.04636 0.04980   0.08643 -0.11944         0.2
0.07040 0.06118   0.10959 -0.13110
0.09865 0.07171   0.13548 -0.13943
0.13075 0.08122   0.16433 -0.14399
0.16633 0.08955   0.19663 -0.14462         0.1
0.20495 0.09652   0.23262 -0.14170
0.24618 0.10190   0.27216 -0.13552
0.28970 0.10538   0.31514 -0.12635


                                     y/c
0.33539 0.10684   0.36142 -0.11455         0.0
0.38300 0.10642   0.41081 -0.10062
0.43214 0.10431   0.46300 -0.08518
0.48234 0.10066   0.51756 -0.06893
0.53312 0.09566   0.57389 -0.05266         -0.1
0.58396 0.08955   0.63119 -0.03717
0.63429 0.08254   0.68850 -0.02322
0.68353 0.07489   0.74465 -0.01147
0.73105 0.06680   0.79836 -0.00239         -0.2
0.77624 0.05851   0.84823 0.00376                 0.0   0.1   0.2   0.3   0.4
0.81848 0.05016   0.89291 0.00700
0.85715 0.04192   0.93109 0.00763
0.89164 0.03377   0.96165 0.00615
0.92166 0.02552   0.98346 0.00340
0.94740 0.01733   0.99601 0.00093
0.96886 0.00996   1.00000 0.00000
0.98550 0.00432
0.99625 0.00102
1.00000 0.00000
S821 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00012 0.00132   0.00002 -0.00057
0.00064 0.00336   0.00042 -0.00244
0.00176 0.00603   0.00126 -0.00440
0.00861 0.01510   0.00530 -0.01010
0.02029 0.02464   0.01536 -0.01866
0.03661 0.03425   0.03018 -0.02713
0.05742 0.04366   0.04956 -0.03517
                                                                          S822 Airfoil
0.08254 0.05271   0.07336 -0.04253         0.2
0.11172 0.06122   0.10140 -0.04903
0.14466 0.06904   0.13345 -0.05456
0.18104 0.07607   0.16927 -0.05902
0.22050 0.08218   0.20852 -0.06236         0.1
0.26262 0.08729   0.25087 -0.06455
0.30696 0.09133   0.29590 -0.06560
0.35305 0.09423   0.34317 -0.06553


                                     y/c
0.40035 0.09591   0.39222 -0.06437         0.0
0.44835 0.09628   0.44252 -0.06218
0.49650 0.09518   0.49354 -0.05900
0.54446 0.09236   0.54470 -0.05484
0.59211 0.08784   0.59560 -0.04961         -0.1
0.63910 0.08191   0.64598 -0.04352
0.68492 0.07470   0.69534 -0.03695
0.72923 0.06619   0.74302 -0.03012
0.77203 0.05665   0.78856 -0.02310         -0.2
0.81306 0.04674   0.83169 -0.01624                0.0   0.1   0.2   0.3   0.4
0.85171 0.03708   0.87185 -0.01019
0.88727 0.02810   0.90813 -0.00543
0.91903 0.02015   0.93957 -0.00215
0.94621 0.01336   0.96523 -0.00032
0.96834 0.00765   0.98428 0.00031
0.98521 0.00326   0.99603 0.00018
0.99615 0.00074       1        0
    1        0
S822 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00003 0.00081   0.00014 -0.00185
0.00052 0.00340   0.00077 -0.00476
0.00153 0.00610   0.00235 -0.00931
0.00585 0.01332   0.00997 -0.02397
0.01696 0.02508   0.02096 -0.04105
0.03294 0.03694   0.03398 -0.05895
0.05346 0.04855   0.04870 -0.07607
                                                                          S823 Airfoil
0.07823 0.05963   0.06519 -0.09082         0.2
0.10699 0.06996   0.08455 -0.10183
0.13942 0.07934   0.10818 -0.10927
0.17517 0.08761   0.13619 -0.11396
0.21386 0.09460   0.16818 -0.11608         0.1
0.25507 0.10012   0.20392 -0.11564
0.29844 0.10396   0.24321 -0.11269
0.34365 0.10598   0.28583 -0.10736


                                     y/c
0.39036 0.10609   0.33155 -0.09985         0.0
0.43836 0.10427   0.38011 -0.09045
0.48734 0.10071   0.43115 -0.07953
0.53687 0.09561   0.48426 -0.06755
0.58650 0.08921   0.53893 -0.05503         -0.1
0.63576 0.08174   0.59453 -0.04251
0.68411 0.07347   0.65031 -0.03058
0.73103 0.06471   0.70542 -0.01977
0.77594 0.05573   0.75888 -0.01054         -0.2
0.81824 0.04683   0.80962 -0.00327                0.0   0.1   0.2   0.3   0.4
0.85734 0.03824   0.85655 0.00182
0.89261 0.03018   0.89852 0.00469
0.92348 0.02280   0.93446 0.00545
0.94935 0.01608   0.96322 0.00441
0.97006 0.00985   0.98383 0.00244
0.98585 0.00451    0.996   0.00069
0.99627 0.00109       1        0
    1        0
S823 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00001 0.00030   0.00014 -0.00143
0.00028 0.00224   0.00081 -0.00307
0.00129 0.00543   0.00197 -0.00477
0.00721 0.01481   0.00650 -0.00920
0.01766 0.02500   0.01819 -0.01650
0.03250 0.03549   0.03502 -0.02381
0.05161 0.04596   0.05670 -0.03093
                                                                          S825 Airfoil
0.07479 0.05616   0.08297 -0.03780         0.2
0.10185 0.06588   0.11351 -0.04443
0.13251 0.07494   0.14790 -0.05114
0.16643 0.08315   0.18480 -0.05834
0.20324 0.09032   0.22231 -0.06499         0.1
0.24253 0.09625   0.25997 -0.06891
0.28387 0.10060   0.29879 -0.06869
0.32709 0.10296   0.34011 -0.06415


                                     y/c
0.37230 0.10329   0.38475 -0.05600         0.0
0.41930 0.10195   0.43307 -0.04520
0.46763 0.09920   0.48499 -0.03306
0.51676 0.09525   0.53974 -0.02082
0.56616 0.09029   0.59631 -0.00935         -0.1
0.61526 0.08450   0.65355 0.00060
0.66350 0.07806   0.71026 0.00854
0.71028 0.07112   0.76514 0.01410
0.75503 0.06385   0.81692 0.01713          -0.2
0.79720 0.05636   0.86437 0.01757                 0.0   0.1   0.2   0.3   0.4
0.83624 0.04878   0.90608 0.01553
0.87165 0.04117   0.94062 0.01168
0.90294 0.03351   0.96717 0.00727
0.92994 0.02560   0.98566 0.00342
0.95294 0.01758   0.99646 0.00088
0.97208 0.01022   1.00000 0.00000
0.98695 0.00450
0.99661 0.00108
1.00000 0.00000
S825 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00018 0.00159   0.00000 -0.00005
0.00255 0.00748   0.00021 -0.00146
0.00954 0.01638   0.00093 -0.00274
0.02088 0.02596   0.00216 -0.00403
0.03651 0.03580   0.00367 -0.00525
0.05636 0.04562   0.01367 -0.01035
0.08026 0.05519   0.02920 -0.01518
                                                                          S825 Airfoil
0.10801 0.06434   0.04998 -0.01960         0.2
0.13934 0.07288   0.07580 -0.02362
0.17395 0.08068   0.10637 -0.02729
0.21146 0.08758   0.14133 -0.03091
0.25149 0.09343   0.17965 -0.03486         0.1
0.29361 0.09807   0.21987 -0.03855
0.33736 0.10133   0.26153 -0.04064
0.38228 0.10294   0.30497 -0.04051


                                     y/c
0.42820 0.10249   0.35027 -0.03794         0.0
0.47526 0.10005   0.39779 -0.03280
0.52324 0.09607   0.44785 -0.02563
0.57161 0.09094   0.50032 -0.01720
0.61980 0.08489   0.55484 -0.00841         -0.1
0.66724 0.07816   0.61055 -0.00015
0.71333 0.07095   0.66644 0.00699
0.75749 0.06341   0.72142 0.01254
0.79915 0.05572   0.77434 0.01621          -0.2
0.83778 0.04798   0.82409 0.01784                 0.0   0.1   0.2   0.3   0.4
0.87287 0.04029   0.86953 0.01741
0.90391 0.03262   0.90945 0.01498
0.93072 0.02479   0.94257 0.01113
0.95355 0.01695   0.96813 0.00689
0.97251 0.00982   0.98604 0.00324
0.98719 0.00431   0.99655 0.00084
0.99668 0.00103   1.00000 0.00000
1.00000 0.00000
S825 Airfoil




     0.00000   0.00000
     1.00000   0.00000




        0.5       0.6    0.7   0.8   0.9   1.0
        x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00001 0.00049   0.00012 -0.00131
0.00034 0.00248   0.00076 -0.00303
0.00453 0.01108   0.00190 -0.00483
0.01355 0.02098   0.01052 -0.01279
0.02714 0.03124   0.02434 -0.02082                                           S901 Airfoil
0.04515 0.04146   0.04326 -0.02896
                                           0.2
0.06748 0.05138   0.06860 -0.03717
0.09397 0.06078   0.09465 -0.04528
0.12441 0.06957   0.12617 -0.05306
0.15846 0.07770   0.16096 -0.06027         0.1
0.19566 0.08502   0.19856 -0.06668
0.23555 0.09136   0.23847 -0.07203
0.27765 0.09644   0.28020 -0.07602




                                     y/c
0.32163 0.09997   0.32320 -0.07825         0.0                            0.00000
0.36732 0.10179   0.36724 -0.07811                                        1.00000
0.41445 0.10198   0.41244 -0.07527
0.46261 0.10064   0.45892 -0.06978
0.51138 0.09785   0.50649 -0.06182         -0.1
0.56031 0.09376   0.55579 -0.05174
0.60895 0.08850   0.60617 -0.04017
0.65679 0.08227   0.65768 -0.02792
0.70333 0.07526   0.70987 -0.01610         -0.2
0.74806 0.06766   0.76174 -0.00586                0.0   0.1   0.2   0.3      0.4
0.79043 0.05968   0.81195 0.00201
0.82993 0.05149   0.85905 0.00698
0.86601 0.04326   0.90138 0.00879
0.89814 0.03501   0.93711 0.00788
0.92609 0.02656   0.96500 0.00544
0.95009 0.01809   0.98464 0.00275
0.97025 0.01039   0.99620 0.00074
0.98604 0.00449   1.00000 0.00000
0.99637 0.00105
1.00000 0.00000
S901 Airfoil




    0.00000
    0.00000




       0.5     0.6   0.7   0.8   0.9   1.0
       x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00001 0.00041   0.00007 -0.00098
0.00224 0.00717   0.00046 -0.00208
0.00856 0.01569   0.00134 -0.00296
0.01903 0.02489   0.00274 -0.00373
0.03372 0.03435   0.01286 -0.00627
0.05264 0.04375   0.02922 -0.00777
0.07573 0.05288   0.05180 -0.00876
                                                                             S902 Airfoil
0.10287 0.06158   0.08008 -0.00954         0.2
0.13387 0.06979   0.11354 -0.01018
0.16841 0.07750   0.15169 -0.01077
0.20603 0.08461   0.19395 -0.01135
0.24627 0.09096   0.23976 -0.01192         0.1
0.28868 0.09642   0.28852 -0.01249
0.33277 0.10081   0.33958 -0.01304
0.37806 0.10397   0.39232 -0.01354



                                     y/c
0.42409 0.10567   0.44607 -0.01397         0.0                            0.00000
0.47051 0.10571   0.50019 -0.01425                                        1.00000
0.51703 0.10400   0.55401 -0.01435
0.56335 0.10053   0.60688 -0.01416
0.60921 0.09535   0.65818 -0.01357         -0.1
0.65431 0.08857   0.70742 -0.01232
0.69839 0.08041   0.75434 -0.01032
0.74116 0.07112   0.79878 -0.00769
0.78234 0.06109   0.84045 -0.00480         -0.2
0.82155 0.05078   0.87892 -0.00210                0.0   0.1   0.2   0.3      0.4
0.85824 0.04067   0.91350 -0.00006
0.89179 0.03109   0.94332 0.00107
0.92146 0.02219   0.96752 0.00132
0.94760 0.01420   0.98537 0.00093
0.96923 0.00767   0.99631 0.00031
0.98581 0.00312   1.00000 0.00000
0.99636 0.00069
1.00000 0.00000
S902 Airfoil




    0.00000
    0.00000




        0.5    0.6   0.7   0.8   0.9   1.0
       x/c
  Upper Surface     Lower Surface
   x/c      y/c      x/c      y/c
0.00001 0.00035   0.00011 -0.00088
0.00032 0.00180   0.00072 -0.00201
0.00242 0.00608   0.00182 -0.00317
0.00942 0.01372   0.00411 -0.00490
0.02086 0.02187   0.01420 -0.00970
0.03671 0.03007   0.02963 -0.01426                                        S903 Air
0.05695 0.03802   0.05031 -0.01838
0.08152 0.04554   0.07601 -0.02209         0.2
0.11029 0.05253   0.10643 -0.02536
0.14306 0.05897   0.14123 -0.02820
0.17946 0.06490   0.18001 -0.03057
0.21899 0.07029   0.22234 -0.03247         0.1
0.26115 0.07502   0.26775 -0.03390
0.30544 0.07897   0.31573 -0.03486
0.35132 0.08201   0.36574 -0.03536




                                     y/c
0.39827 0.08397   0.41722 -0.03541         0.0
0.44581 0.08464   0.46959 -0.03502
0.49357 0.08384   0.52226 -0.03419
0.54122 0.08146   0.57462 -0.03295
                                           -0.1
0.58849 0.07752   0.62607 -0.03129
0.63507 0.07208   0.67602 -0.02922
0.68070 0.06529   0.72392 -0.02668
0.72507 0.05739   0.76934 -0.02360         -0.2
0.76790 0.04867   0.81194 -0.02009
                                                  0.0   0.1   0.2   0.3   0.4
0.80885 0.03953   0.85137 -0.01636
0.84753 0.03044   0.88711 -0.01255
0.88343 0.02189   0.91879 -0.00882
0.91595 0.01437   0.94609 -0.00537
0.94435 0.00830   0.96860 -0.00261
0.96779 0.00397   0.98563 -0.00087
0.98538 0.00138   0.99633 -0.00014
0.99630 0.00026   1.00000 0.00000
1.00000 0.00000
S903 Airfoil




  0.00000    0.00000
  1.00000    0.00000




0.4         0.5        0.6   0.7   0.8   0.9   1.0
            x/c

				
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posted:3/21/2013
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