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NASA RC(5)-10 AIRFOIL (rc510-il)

NASA RC(5)-10 AIRFOIL - NASA/Langley RC(5)-10 rotorcraft airfoil


Airfoil rc510-il
Details Dat file Parser  
(rc510-il) NASA RC(5)-10 AIRFOIL
NASA/Langley RC(5)-10 rotorcraft airfoil
Max thickness 10% at 40.1% chord.
Max camber 2.2% at 25.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NASA RC(5)-10 AIRFOIL
       41.       43.

 0.0       0.0
 0.0028699 0.0086493
 0.0093564 0.0167131
 0.0235851 0.0279240
 0.0473197 0.0400544
 0.0736415 0.0489540
 0.0999394 0.0550586
 0.1257977 0.0593046
 0.1514405 0.0623730
 0.1768159 0.0646707
 0.2021529 0.0664675
 0.2273750 0.0678983
 0.2525969 0.0690471
 0.3028524 0.0706359
 0.3529137 0.0712934
 0.3779400 0.0712125
 0.4031252 0.0707934
 0.4282423 0.0699861
 0.4535508 0.0687381
 0.4787810 0.0670466
 0.5036672 0.0649649
 0.5286227 0.0625196
 0.5535420 0.0597777
 0.5784435 0.0567727
 0.6033537 0.0535177
 0.6282811 0.0500196
 0.6531860 0.0463035
 0.6780995 0.0424016
 0.7029201 0.0383913
 0.7276346 0.0343608
 0.7524412 0.0303697
 0.7771370 0.0265333
 0.8016555 0.0229112
 0.8262545 0.0194796
 0.8509200 0.0162354
 0.8756557 0.0131708
 0.9004740 0.0102825
 0.9253236 0.0075900
 0.9501698 0.0051105
 0.9750257 0.0028500
 1.0000000 0.0007915

 0.0       0.0
 0.0034372 -.0075914
 0.0118775 -.0123999
 0.0140497 -.0131715
 0.0225541 -.0154813
 0.0333092 -.0174415
 0.0594707 -.0200039
 0.0830337 -.0209595
 0.1066037 -.0213593
 0.1305989 -.0216152
 0.1548014 -.0219837
 0.1792631 -.0225632
 0.2037586 -.0233070
 0.2283655 -.0241226
 0.2529693 -.0249422
 0.3023628 -.0265038
 0.3519449 -.0278438
 0.3767368 -.0283788
 0.4013711 -.0287866
 0.4260693 -.0290409
 0.4505748 -.0291107
 0.4751559 -.0289921
 0.5000805 -.0286501
 0.5249348 -.0281196
 0.5498234 -.0274273
 0.5747297 -.0266091
 0.5996258 -.0256969
 0.6245024 -.0247285
 0.6494011 -.0237263
 0.6742911 -.0227151
 0.6992709 -.0216984
 0.7243580 -.0206727
 0.7493522 -.0196272
 0.7744606 -.0185186
 0.7997481 -.0173013
 0.8249566 -.0159384
 0.8501026 -.0143781
 0.8751813 -.0125892
 0.9001801 -.0105498
 0.9251504 -.0084511
 0.9501257 -.0063184
 0.9750936 -.0039747
 1.0000000 -.0007915
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Lednicer format dat file
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Polars for NASA RC(5)-10 AIRFOIL (rc510-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rc510-il50,000931.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rc510-il50,000532.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rc510-il100,000946.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rc510-il100,000543.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rc510-il200,000960.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rc510-il200,000554.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rc510-il500,000976.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rc510-il500,000575.7 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   rc510-il1,000,000994.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rc510-il1,000,000592.4 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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