SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Reynolds number: 50,000 Max Cl/Cd: 28.34 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ssca07-il-50000-n5.txt Download as CSV file: xf-ssca07-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SSC-A07 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6256 0.11669 0.11022 0.0165 1.0000 0.1095
-9.000 -0.6188 0.11294 0.10648 0.0161 1.0000 0.1167
-8.750 -0.6327 0.10978 0.10344 0.0090 1.0000 0.1204
-8.250 -0.6253 0.10140 0.09516 0.0063 1.0000 0.1336
-8.000 -0.6165 0.09681 0.09055 0.0067 1.0000 0.1383
-7.750 -0.6142 0.09281 0.08659 0.0042 1.0000 0.1444
-7.500 -0.6143 0.08831 0.08213 0.0005 1.0000 0.1520
-7.000 -0.5923 0.07342 0.06684 -0.0135 1.0000 0.0741
-6.750 -0.5817 0.06687 0.05958 -0.0191 1.0000 0.0528
-6.500 -0.5679 0.06205 0.05487 -0.0187 1.0000 0.0500
-6.250 -0.5545 0.05763 0.05024 -0.0196 1.0000 0.0476
-6.000 -0.5392 0.05317 0.04545 -0.0204 1.0000 0.0452
-5.750 -0.5213 0.04872 0.04050 -0.0209 1.0000 0.0427
-5.500 -0.4996 0.04511 0.03611 -0.0206 1.0000 0.0405
-5.250 -0.4776 0.04215 0.03267 -0.0202 1.0000 0.0398
-5.000 -0.4561 0.03887 0.02901 -0.0198 1.0000 0.0396
-4.750 -0.4330 0.03604 0.02573 -0.0193 1.0000 0.0397
-4.500 -0.4108 0.03304 0.02246 -0.0189 1.0000 0.0415
-4.250 -0.3876 0.03090 0.02013 -0.0184 1.0000 0.0445
-4.000 -0.3626 0.02888 0.01772 -0.0176 1.0000 0.0462
-3.750 -0.3372 0.02698 0.01553 -0.0166 1.0000 0.0473
-3.500 -0.3119 0.02534 0.01366 -0.0154 1.0000 0.0489
-3.250 -0.2872 0.02399 0.01208 -0.0140 1.0000 0.0515
-3.000 -0.2643 0.02272 0.01076 -0.0129 1.0000 0.0582
-2.750 -0.2412 0.02172 0.00955 -0.0118 1.0000 0.0650
-2.500 -0.2199 0.02066 0.00837 -0.0106 1.0000 0.0727
-2.250 -0.1123 0.01598 0.00715 -0.0195 1.0000 1.0000
-2.000 -0.0964 0.01580 0.00664 -0.0181 1.0000 1.0000
-1.750 -0.0828 0.01566 0.00624 -0.0161 1.0000 1.0000
-1.500 -0.0712 0.01557 0.00589 -0.0138 1.0000 1.0000
-1.250 -0.0606 0.01551 0.00564 -0.0112 1.0000 1.0000
-1.000 -0.0493 0.01548 0.00543 -0.0088 1.0000 1.0000
-0.750 -0.0362 0.01548 0.00526 -0.0066 1.0000 1.0000
-0.500 -0.0210 0.01552 0.00513 -0.0048 1.0000 1.0000
-0.250 -0.0040 0.01558 0.00504 -0.0034 1.0000 1.0000
0.000 0.0145 0.01567 0.00498 -0.0022 1.0000 1.0000
0.250 0.0340 0.01579 0.00499 -0.0012 1.0000 1.0000
0.500 0.0543 0.01593 0.00505 -0.0005 1.0000 1.0000
0.750 0.0751 0.01610 0.00516 0.0002 1.0000 1.0000
1.000 0.0964 0.01630 0.00532 0.0007 1.0000 1.0000
1.250 0.1180 0.01653 0.00553 0.0012 1.0000 1.0000
1.500 0.1412 0.01679 0.00580 0.0012 0.9992 1.0000
1.750 0.2192 0.01728 0.00641 -0.0090 0.9706 1.0000
2.000 0.2859 0.01749 0.00682 -0.0163 0.9405 1.0000
2.250 0.3312 0.01758 0.00707 -0.0191 0.9128 1.0000
2.500 0.3663 0.01756 0.00722 -0.0197 0.8833 1.0000
2.750 0.3961 0.01747 0.00734 -0.0190 0.8512 1.0000
3.000 0.4215 0.01736 0.00738 -0.0173 0.8126 1.0000
3.250 0.4452 0.01723 0.00738 -0.0152 0.7626 1.0000
3.500 0.4677 0.01711 0.00729 -0.0126 0.6839 1.0000
3.750 0.4886 0.01724 0.00695 -0.0089 0.5587 1.0000
4.000 0.5067 0.01813 0.00721 -0.0063 0.4406 1.0000
4.250 0.5272 0.01917 0.00782 -0.0050 0.3710 1.0000
4.500 0.5495 0.02013 0.00857 -0.0042 0.3279 1.0000
4.750 0.5734 0.02105 0.00941 -0.0037 0.2965 1.0000
5.000 0.5980 0.02196 0.01030 -0.0032 0.2696 1.0000
5.250 0.6227 0.02285 0.01130 -0.0028 0.2431 1.0000
5.500 0.6470 0.02373 0.01223 -0.0024 0.2152 1.0000
5.750 0.6709 0.02463 0.01322 -0.0020 0.1872 1.0000
6.000 0.6944 0.02561 0.01428 -0.0016 0.1579 1.0000
6.250 0.7176 0.02679 0.01551 -0.0011 0.1295 1.0000
6.500 0.7409 0.02806 0.01695 -0.0006 0.1041 1.0000
6.750 0.7637 0.02958 0.01848 0.0000 0.0877 1.0000
7.000 0.7865 0.03117 0.02026 0.0005 0.0739 1.0000
7.250 0.8098 0.03344 0.02288 0.0013 0.0665 1.0000
7.500 0.8311 0.03583 0.02552 0.0019 0.0603 1.0000
7.750 0.8510 0.03807 0.02811 0.0025 0.0537 1.0000
8.000 0.8690 0.04102 0.03124 0.0030 0.0507 1.0000
8.250 0.8836 0.04523 0.03628 0.0038 0.0491 1.0000
8.500 0.8928 0.04997 0.04169 0.0045 0.0478 1.0000
8.750 0.8960 0.05503 0.04733 0.0048 0.0467 1.0000
9.000 0.8937 0.06022 0.05299 0.0047 0.0457 1.0000
9.250 0.8858 0.06562 0.05874 0.0041 0.0451 1.0000
9.500 0.8716 0.07144 0.06481 0.0026 0.0452 1.0000
9.750 0.8514 0.07764 0.07113 0.0000 0.0460 1.0000
10.000 0.8327 0.08501 0.07853 -0.0051 0.0470 1.0000
10.250 0.8191 0.09366 0.08710 -0.0117 0.0479 1.0000
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Polar data table (+)
Polar graphs
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