S1223 RTL (s1223rtl-il)
S1223 RTL - Richard T. LaSalle modification of the S1223 to S1223RTL
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(s1223rtl-il) S1223 RTL Richard T. LaSalle modification of the S1223 to S1223RTL Max thickness 13.5% at 19.9% chord. Max camber 8.3% at 55.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S1223 RTL
1.000000 0.000000
0.993582 0.005174
0.984237 0.012721
0.973452 0.019959
0.960621 0.026718
0.945173 0.033431
0.926643 0.040426
0.904880 0.047739
0.880167 0.055249
0.853151 0.062781
0.824589 0.070170
0.795130 0.077285
0.765239 0.084030
0.735204 0.090329
0.705148 0.096131
0.675070 0.101410
0.644888 0.106168
0.614467 0.110429
0.583656 0.114241
0.552304 0.117672
0.520314 0.120811
0.487697 0.123750
0.454605 0.126565
0.421337 0.129290
0.388325 0.131899
0.356059 0.134296
0.325061 0.136339
0.295869 0.137848
0.268821 0.138607
0.243816 0.138418
0.220493 0.137168
0.198517 0.134818
0.177661 0.131353
0.157772 0.126772
0.138774 0.121094
0.120658 0.114364
0.103478 0.106654
0.087347 0.098106
0.072460 0.088966
0.059065 0.079596
0.047376 0.070398
0.037469 0.061702
0.029259 0.053661
0.022548 0.046281
0.017103 0.039506
0.012701 0.033277
0.009153 0.027538
0.006314 0.022235
0.004076 0.017315
0.002365 0.012727
0.001128 0.008432
0.000338 0.004397
-0.000008 0.000603
0.000140 -0.003015
0.001040 -0.006532
0.003093 -0.009594
0.006271 -0.011793
0.010197 -0.013209
0.014706 -0.014130
0.019836 -0.014738
0.025728 -0.015128
0.032603 -0.015340
0.040784 -0.015363
0.050745 -0.015157
0.063160 -0.014648
0.078892 -0.013726
0.098681 -0.012263
0.122421 -0.010129
0.149036 -0.007205
0.177612 -0.003422
0.207911 0.001142
0.239707 0.006251
0.272500 0.011665
0.305752 0.017205
0.338930 0.022704
0.371726 0.028030
0.404038 0.033089
0.435847 0.037798
0.467163 0.042089
0.498031 0.045901
0.528494 0.049183
0.558616 0.051898
0.588443 0.054011
0.618027 0.055499
0.647402 0.056339
0.676616 0.056516
0.705687 0.056018
0.734636 0.054839
0.763438 0.052976
0.792049 0.050432
0.820340 0.047218
0.848075 0.043370
0.874835 0.038946
0.900011 0.034060
0.922918 0.028856
0.943064 0.023463
0.960352 0.017954
0.975001 0.012374
0.987341 0.006802
1.000000 0.000000
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for S1223 RTL (s1223rtl-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1223rtl-il | 50,000 | 9 | 31.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 50,000 | 5 | 35.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 100,000 | 9 | 43.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 100,000 | 5 | 49.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 200,000 | 9 | 98 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 200,000 | 5 | 64.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 500,000 | 9 | 84 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 500,000 | 5 | 85.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 1,000,000 | 9 | 106.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 1,000,000 | 5 | 106.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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