SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 100,000 Max Cl/Cd: 38.75 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca09-il-100000.txt Download as CSV file: xf-ssca09-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4577 0.11741 0.11297 -0.0009 1.0000 0.0895
-10.250 -0.4742 0.11419 0.10980 -0.0052 1.0000 0.0909
-10.000 -0.4906 0.11049 0.10615 -0.0096 1.0000 0.0913
-9.750 -0.4532 0.10527 0.10089 -0.0037 1.0000 0.0965
-9.500 -0.4522 0.10148 0.09713 -0.0048 1.0000 0.1005
-9.250 -0.4650 0.09731 0.09300 -0.0085 1.0000 0.1041
-9.000 -0.4892 0.09266 0.08842 -0.0148 1.0000 0.1052
-8.750 -0.4641 0.08816 0.08390 -0.0103 1.0000 0.1094
-8.500 -0.4609 0.08430 0.08005 -0.0109 1.0000 0.1141
-8.250 -0.4774 0.07927 0.07508 -0.0157 1.0000 0.1180
-8.000 -0.5066 0.07354 0.06939 -0.0229 1.0000 0.1191
-7.750 -0.5387 0.06884 0.06451 -0.0276 1.0000 0.1199
-7.500 -0.4943 0.06486 0.06076 -0.0217 1.0000 0.1280
-7.250 -0.5192 0.05972 0.05548 -0.0265 1.0000 0.1333
-7.000 -0.5756 0.06687 0.06232 -0.0222 1.0000 0.1280
-6.750 -0.5739 0.06262 0.05788 -0.0246 1.0000 0.1374
-6.500 -0.5698 0.05974 0.05470 -0.0256 1.0000 0.1503
-6.250 -0.5533 0.05631 0.05145 -0.0240 1.0000 0.1582
-6.000 -0.5467 0.05334 0.04842 -0.0230 1.0000 0.1712
-5.750 -0.5414 0.05078 0.04580 -0.0212 1.0000 0.1861
-4.750 -0.4757 0.03466 0.02717 -0.0162 1.0000 0.0933
-4.500 -0.4519 0.03118 0.02320 -0.0142 1.0000 0.0741
-4.250 -0.4309 0.02871 0.02040 -0.0128 1.0000 0.0714
-4.000 -0.4074 0.02642 0.01762 -0.0113 1.0000 0.0679
-3.750 -0.3826 0.02510 0.01579 -0.0097 1.0000 0.0646
-3.500 -0.3584 0.02373 0.01420 -0.0086 1.0000 0.0640
-3.250 -0.3332 0.02185 0.01222 -0.0078 1.0000 0.0646
-3.000 -0.3089 0.02030 0.01076 -0.0072 1.0000 0.0688
-2.750 -0.2848 0.01938 0.00980 -0.0064 1.0000 0.0747
-2.500 -0.2604 0.01823 0.00870 -0.0056 1.0000 0.0799
-2.250 -0.2360 0.01735 0.00787 -0.0051 1.0000 0.0934
-2.000 -0.0636 0.01473 0.00832 -0.0212 1.0000 1.0000
-1.750 -0.0663 0.01459 0.00809 -0.0172 1.0000 1.0000
-1.500 -0.0695 0.01445 0.00786 -0.0130 1.0000 1.0000
-1.250 -0.0722 0.01430 0.00763 -0.0088 1.0000 1.0000
-1.000 -0.0731 0.01416 0.00742 -0.0049 1.0000 1.0000
-0.750 -0.0706 0.01407 0.00721 -0.0014 1.0000 1.0000
-0.500 -0.0618 0.01405 0.00709 0.0010 1.0000 1.0000
-0.250 -0.0465 0.01412 0.00705 0.0023 1.0000 1.0000
0.000 -0.0278 0.01426 0.00708 0.0030 1.0000 1.0000
0.250 -0.0072 0.01446 0.00718 0.0033 1.0000 1.0000
0.500 0.0144 0.01470 0.00735 0.0035 1.0000 1.0000
0.750 0.0969 0.01532 0.00789 -0.0076 0.9802 1.0000
1.000 0.1666 0.01569 0.00825 -0.0159 0.9636 1.0000
1.250 0.2336 0.01587 0.00846 -0.0234 0.9491 1.0000
1.500 0.2948 0.01588 0.00853 -0.0295 0.9344 1.0000
1.750 0.3381 0.01581 0.00853 -0.0320 0.9169 1.0000
2.000 0.3752 0.01563 0.00844 -0.0328 0.8983 1.0000
2.250 0.4063 0.01533 0.00820 -0.0321 0.8795 1.0000
2.500 0.4280 0.01499 0.00792 -0.0295 0.8576 1.0000
2.750 0.4486 0.01450 0.00747 -0.0263 0.8350 1.0000
3.000 0.4668 0.01402 0.00706 -0.0228 0.8067 1.0000
3.250 0.4849 0.01354 0.00661 -0.0193 0.7674 1.0000
3.500 0.5026 0.01303 0.00603 -0.0154 0.6915 1.0000
3.750 0.5157 0.01331 0.00531 -0.0102 0.5117 1.0000
4.000 0.5342 0.01457 0.00572 -0.0085 0.4002 1.0000
4.250 0.5570 0.01551 0.00626 -0.0078 0.3559 1.0000
4.500 0.5814 0.01632 0.00684 -0.0073 0.3288 1.0000
4.750 0.6064 0.01710 0.00744 -0.0069 0.3090 1.0000
5.000 0.6321 0.01788 0.00814 -0.0066 0.2936 1.0000
5.250 0.6582 0.01863 0.00887 -0.0064 0.2801 1.0000
5.500 0.6843 0.01939 0.00965 -0.0063 0.2674 1.0000
5.750 0.7103 0.02018 0.01047 -0.0061 0.2554 1.0000
6.000 0.7361 0.02097 0.01130 -0.0060 0.2429 1.0000
6.250 0.7618 0.02180 0.01213 -0.0058 0.2310 1.0000
6.500 0.7873 0.02268 0.01296 -0.0057 0.2189 1.0000
6.750 0.8124 0.02340 0.01384 -0.0055 0.2057 1.0000
7.000 0.8371 0.02422 0.01480 -0.0052 0.1918 1.0000
7.250 0.8612 0.02507 0.01570 -0.0049 0.1768 1.0000
7.500 0.8848 0.02606 0.01670 -0.0046 0.1609 1.0000
7.750 0.9072 0.02698 0.01787 -0.0041 0.1439 1.0000
8.000 0.9292 0.02792 0.01899 -0.0035 0.1277 1.0000
8.250 0.9511 0.02903 0.02023 -0.0028 0.1137 1.0000
8.500 0.9723 0.03010 0.02141 -0.0022 0.1014 1.0000
8.750 0.9940 0.03151 0.02279 -0.0016 0.0921 1.0000
9.000 1.0139 0.03285 0.02444 -0.0008 0.0834 1.0000
9.250 1.0322 0.03524 0.02715 0.0001 0.0772 1.0000
9.500 1.0496 0.03760 0.02983 0.0011 0.0726 1.0000
9.750 1.0666 0.04027 0.03252 0.0017 0.0686 1.0000
10.000 1.0724 0.04378 0.03677 0.0034 0.0657 1.0000
10.250 1.0751 0.04774 0.04125 0.0050 0.0637 1.0000
10.500 1.0709 0.05231 0.04631 0.0066 0.0628 1.0000
10.750 1.0565 0.05752 0.05197 0.0082 0.0627 1.0000
11.000 1.0295 0.06304 0.05785 0.0096 0.0633 1.0000
11.250 0.9959 0.06924 0.06430 0.0092 0.0643 1.0000
11.500 0.9601 0.07702 0.07226 0.0055 0.0656 1.0000
11.750 0.9260 0.08689 0.08223 -0.0013 0.0670 1.0000
12.000 0.9018 0.09718 0.09251 -0.0081 0.0683 1.0000
12.250 0.8877 0.10587 0.10117 -0.0124 0.0690 1.0000
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Polar data table (+)
Polar graphs
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