SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 500,000 Max Cl/Cd: 72.01 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca09-il-500000.txt Download as CSV file: xf-ssca09-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SSC-A09 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4882 0.08500 0.08309 -0.0054 1.0000 0.0178
-9.000 -0.4911 0.08004 0.07813 -0.0077 1.0000 0.0181
-8.750 -0.4963 0.07451 0.07263 -0.0106 1.0000 0.0184
-8.500 -0.5050 0.06818 0.06631 -0.0149 1.0000 0.0185
-8.250 -0.6342 0.06453 0.06226 -0.0222 1.0000 0.0165
-8.000 -0.6281 0.06115 0.05884 -0.0236 1.0000 0.0168
-7.750 -0.6179 0.05827 0.05589 -0.0250 1.0000 0.0172
-7.500 -0.6060 0.05508 0.05261 -0.0264 1.0000 0.0178
-7.250 -0.5916 0.05129 0.04866 -0.0281 0.9952 0.0187
-7.000 -0.5717 0.04647 0.04356 -0.0300 0.9887 0.0204
-6.750 -0.5466 0.04367 0.04020 -0.0299 0.9824 0.0217
-6.500 -0.5434 0.03615 0.03235 -0.0297 0.9745 0.0227
-6.250 -0.5258 0.03414 0.03029 -0.0292 0.9684 0.0234
-6.000 -0.5086 0.03241 0.02843 -0.0282 0.9629 0.0243
-5.750 -0.4883 0.03051 0.02633 -0.0274 0.9580 0.0258
-5.500 -0.4615 0.03145 0.02694 -0.0258 0.9530 0.0291
-5.250 -0.4500 0.02602 0.02107 -0.0242 0.9484 0.0309
-5.000 -0.4253 0.02425 0.01925 -0.0243 0.9444 0.0320
-4.750 -0.4018 0.02286 0.01774 -0.0237 0.9403 0.0336
-4.500 -0.3755 0.01863 0.01280 -0.0207 0.9369 0.0207
-4.250 -0.3508 0.01605 0.00995 -0.0196 0.9335 0.0184
-4.000 -0.3240 0.01454 0.00827 -0.0190 0.9297 0.0178
-3.750 -0.2992 0.01364 0.00731 -0.0182 0.9259 0.0181
-3.500 -0.2757 0.01297 0.00659 -0.0171 0.9226 0.0188
-3.250 -0.2496 0.01237 0.00595 -0.0167 0.9191 0.0199
-3.000 -0.2222 0.01185 0.00539 -0.0166 0.9151 0.0211
-2.750 -0.1969 0.01117 0.00466 -0.0160 0.9114 0.0231
-2.500 -0.1721 0.01081 0.00430 -0.0153 0.9082 0.0269
-2.250 -0.1446 0.01040 0.00385 -0.0151 0.9046 0.0322
-2.000 -0.1166 0.00997 0.00346 -0.0152 0.9003 0.0495
-1.750 -0.0959 0.00780 0.00293 -0.0149 0.8953 0.4833
-1.500 -0.0743 0.00688 0.00283 -0.0135 0.8881 0.7076
-1.250 -0.0539 0.00658 0.00267 -0.0111 0.8784 0.7714
-1.000 -0.0308 0.00636 0.00252 -0.0095 0.8663 0.8136
-0.750 -0.0092 0.00622 0.00250 -0.0073 0.8569 0.8598
-0.500 0.0098 0.00621 0.00256 -0.0045 0.8501 0.8978
-0.250 0.0317 0.00622 0.00258 -0.0025 0.8428 0.9178
0.000 0.0557 0.00620 0.00251 -0.0013 0.8360 0.9297
0.250 0.0800 0.00616 0.00245 -0.0002 0.8277 0.9389
0.500 0.1040 0.00611 0.00234 0.0010 0.8192 0.9487
0.750 0.1298 0.00605 0.00226 0.0017 0.8089 0.9590
1.000 0.1567 0.00598 0.00216 0.0022 0.7987 0.9679
1.250 0.1867 0.00592 0.00206 0.0019 0.7869 0.9759
1.500 0.2194 0.00588 0.00198 0.0010 0.7710 0.9830
1.750 0.2556 0.00587 0.00191 -0.0007 0.7479 0.9872
2.000 0.2918 0.00591 0.00184 -0.0024 0.7121 0.9914
2.250 0.3276 0.00612 0.00177 -0.0042 0.6413 0.9948
2.500 0.3641 0.00671 0.00185 -0.0065 0.5267 0.9972
2.750 0.3996 0.00747 0.00205 -0.0088 0.3999 1.0000
3.000 0.4244 0.00797 0.00220 -0.0089 0.3243 1.0000
3.250 0.4488 0.00835 0.00235 -0.0087 0.2769 1.0000
3.500 0.4734 0.00865 0.00250 -0.0084 0.2462 1.0000
3.750 0.4990 0.00892 0.00267 -0.0083 0.2250 1.0000
4.000 0.5257 0.00918 0.00286 -0.0083 0.2097 1.0000
4.250 0.5529 0.00944 0.00306 -0.0085 0.1981 1.0000
4.500 0.5805 0.00971 0.00327 -0.0087 0.1875 1.0000
4.750 0.6082 0.00996 0.00347 -0.0089 0.1778 1.0000
5.000 0.6361 0.01018 0.00371 -0.0092 0.1703 1.0000
5.250 0.6639 0.01046 0.00396 -0.0094 0.1636 1.0000
5.500 0.6918 0.01069 0.00421 -0.0097 0.1575 1.0000
5.750 0.7196 0.01093 0.00446 -0.0099 0.1513 1.0000
6.000 0.7472 0.01122 0.00474 -0.0101 0.1450 1.0000
6.250 0.7752 0.01140 0.00496 -0.0104 0.1384 1.0000
6.500 0.8026 0.01169 0.00524 -0.0106 0.1313 1.0000
6.750 0.8305 0.01187 0.00546 -0.0108 0.1234 1.0000
7.000 0.8580 0.01210 0.00571 -0.0110 0.1146 1.0000
7.250 0.8854 0.01235 0.00595 -0.0112 0.1030 1.0000
7.500 0.9124 0.01267 0.00622 -0.0113 0.0867 1.0000
7.750 0.9382 0.01321 0.00666 -0.0114 0.0673 1.0000
8.000 0.9635 0.01384 0.00724 -0.0114 0.0541 1.0000
8.250 0.9883 0.01455 0.00793 -0.0113 0.0447 1.0000
8.500 1.0120 0.01546 0.00883 -0.0110 0.0367 1.0000
8.750 1.0375 0.01597 0.00944 -0.0109 0.0329 1.0000
9.000 1.0594 0.01709 0.01059 -0.0105 0.0283 1.0000
9.250 1.0840 0.01768 0.01128 -0.0103 0.0264 1.0000
9.500 1.1076 0.01840 0.01207 -0.0100 0.0244 1.0000
9.750 1.1295 0.01932 0.01305 -0.0096 0.0228 1.0000
10.000 1.1448 0.02123 0.01510 -0.0084 0.0211 1.0000
10.250 1.1665 0.02206 0.01606 -0.0079 0.0206 1.0000
10.500 1.1866 0.02308 0.01722 -0.0072 0.0200 1.0000
10.750 1.2053 0.02423 0.01852 -0.0064 0.0193 1.0000
11.000 1.2237 0.02531 0.01971 -0.0056 0.0185 1.0000
11.250 1.2421 0.02622 0.02070 -0.0049 0.0176 1.0000
11.500 1.2577 0.02737 0.02193 -0.0040 0.0168 1.0000
11.750 1.2637 0.02971 0.02442 -0.0022 0.0160 1.0000
12.000 1.2676 0.03200 0.02695 -0.0002 0.0155 1.0000
12.250 1.2768 0.03314 0.02824 0.0014 0.0152 1.0000
12.500 1.2835 0.03459 0.02985 0.0029 0.0147 1.0000
12.750 1.2888 0.03621 0.03162 0.0043 0.0142 1.0000
13.000 1.2919 0.03811 0.03367 0.0054 0.0138 1.0000
13.250 1.2943 0.04014 0.03583 0.0062 0.0133 1.0000
13.500 1.2950 0.04249 0.03831 0.0067 0.0130 1.0000
13.750 1.2933 0.04526 0.04120 0.0067 0.0127 1.0000
14.000 1.2895 0.04850 0.04456 0.0063 0.0124 1.0000
14.250 1.2819 0.05253 0.04873 0.0051 0.0122 1.0000
14.500 1.2702 0.05759 0.05396 0.0029 0.0120 1.0000
14.750 1.2549 0.06381 0.06036 -0.0005 0.0119 1.0000
15.000 1.2375 0.07103 0.06776 -0.0050 0.0118 1.0000
15.250 1.2192 0.07903 0.07594 -0.0101 0.0118 1.0000
15.500 1.1993 0.08757 0.08464 -0.0155 0.0118 1.0000
15.750 1.1784 0.09649 0.09371 -0.0209 0.0119 1.0000
16.000 1.1548 0.10597 0.10335 -0.0264 0.0120 1.0000
16.250 1.1126 0.11995 0.11757 -0.0344 0.0124 1.0000
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