S9033 (7.5%) (s9033-il)
S9033 (7.5%) - Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane
| Details | Dat file | Parser | |
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(s9033-il) S9033 (7.5%) Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S9033 (7.5%)
1.000000 0.000000
0.999190 0.000010
0.996780 0.000080
0.992820 0.000250
0.987340 0.000530
0.980410 0.000940
0.972090 0.001470
0.962420 0.002090
0.951430 0.002770
0.939140 0.003490
0.925570 0.004260
0.910760 0.005090
0.894750 0.005980
0.877590 0.006930
0.859340 0.007950
0.840060 0.009030
0.819800 0.010170
0.798640 0.011370
0.776630 0.012630
0.753840 0.013930
0.730340 0.015290
0.706200 0.016690
0.681510 0.018150
0.656340 0.019630
0.630780 0.021130
0.604910 0.022640
0.578780 0.024130
0.552490 0.025600
0.526090 0.027050
0.499690 0.028440
0.473330 0.029780
0.447100 0.031050
0.421080 0.032240
0.395330 0.033340
0.369930 0.034330
0.344930 0.035210
0.320420 0.035970
0.296470 0.036590
0.273120 0.037050
0.250430 0.037350
0.228470 0.037490
0.207300 0.037460
0.186970 0.037220
0.167510 0.036800
0.148980 0.036180
0.131440 0.035360
0.114900 0.034300
0.099390 0.033020
0.084930 0.031540
0.071590 0.029840
0.059370 0.027900
0.048240 0.025760
0.038250 0.023440
0.029450 0.020940
0.021820 0.018210
0.015280 0.015320
0.009880 0.012350
0.005680 0.009340
0.002690 0.006180
0.000760 0.002990
0.000000 0.000000
0.000760 -0.002990
0.002690 -0.006180
0.005680 -0.009340
0.009880 -0.012350
0.015280 -0.015320
0.021820 -0.018210
0.029450 -0.020940
0.038250 -0.023440
0.048240 -0.025760
0.059370 -0.027900
0.071590 -0.029840
0.084930 -0.031540
0.099390 -0.033020
0.114900 -0.034300
0.131440 -0.035360
0.148980 -0.036180
0.167510 -0.036800
0.186970 -0.037220
0.207300 -0.037460
0.228470 -0.037490
0.250430 -0.037350
0.273120 -0.037050
0.296470 -0.036590
0.320420 -0.035970
0.344930 -0.035210
0.369930 -0.034330
0.395330 -0.033340
0.421080 -0.032240
0.447100 -0.031050
0.473330 -0.029780
0.499690 -0.028440
0.526090 -0.027050
0.552490 -0.025600
0.578780 -0.024130
0.604910 -0.022640
0.630780 -0.021130
0.656340 -0.019630
0.681510 -0.018150
0.706200 -0.016690
0.730340 -0.015290
0.753840 -0.013930
0.776630 -0.012630
0.798640 -0.011370
0.819800 -0.010170
0.840060 -0.009030
0.859340 -0.007950
0.877590 -0.006930
0.894750 -0.005980
0.910760 -0.005090
0.925570 -0.004260
0.939140 -0.003490
0.951430 -0.002770
0.962420 -0.002090
0.972090 -0.001470
0.980410 -0.000940
0.987340 -0.000530
0.992820 -0.000250
0.996780 -0.000080
0.999190 -0.000010
1.000000 0.000000
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Polars for S9033 (7.5%) (s9033-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s9033-il | 50,000 | 9 | 21.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 50,000 | 5 | 23.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 100,000 | 9 | 29.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 100,000 | 5 | 32.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 200,000 | 9 | 39.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 200,000 | 5 | 42.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 500,000 | 9 | 56.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 500,000 | 5 | 58.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 1,000,000 | 9 | 70.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 1,000,000 | 5 | 72 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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