SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.97 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca09-il-1000000.txt Download as CSV file: xf-ssca09-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6458 0.08173 0.08034 0.0011 0.9695 0.0093
-8.500 -0.6661 0.07398 0.07252 -0.0065 0.9570 0.0092
-8.250 -0.6721 0.06906 0.06751 -0.0087 0.9498 0.0093
-8.000 -0.6712 0.06443 0.06278 -0.0106 0.9441 0.0095
-7.750 -0.6679 0.06011 0.05834 -0.0116 0.9388 0.0097
-7.500 -0.6624 0.05571 0.05378 -0.0121 0.9344 0.0101
-7.250 -0.6527 0.05063 0.04851 -0.0126 0.9298 0.0108
-7.000 -0.5975 0.03054 0.02816 -0.0143 0.9174 0.0119
-6.750 -0.6072 0.02081 0.01794 -0.0128 0.9129 0.0123
-6.500 -0.5898 0.01917 0.01622 -0.0124 0.9095 0.0127
-6.250 -0.5711 0.01759 0.01453 -0.0120 0.9064 0.0131
-6.000 -0.5504 0.01580 0.01261 -0.0118 0.9030 0.0140
-5.750 -0.5236 0.01507 0.01158 -0.0106 0.8996 0.0160
-5.500 -0.5033 0.01297 0.00917 -0.0097 0.8963 0.0161
-4.750 -0.4573 0.01548 0.01023 -0.0054 0.8949 0.0122
-4.500 -0.4311 0.01428 0.00894 -0.0050 0.8920 0.0116
-4.250 -0.4040 0.01275 0.00729 -0.0048 0.8888 0.0113
-4.000 -0.3771 0.01173 0.00618 -0.0046 0.8853 0.0112
-3.750 -0.3503 0.01095 0.00533 -0.0043 0.8820 0.0113
-3.500 -0.3233 0.01037 0.00468 -0.0041 0.8789 0.0115
-3.250 -0.2951 0.00999 0.00425 -0.0041 0.8757 0.0119
-3.000 -0.2672 0.00920 0.00341 -0.0042 0.8722 0.0132
-2.750 -0.2388 0.00893 0.00312 -0.0043 0.8687 0.0146
-2.500 -0.2107 0.00869 0.00285 -0.0043 0.8651 0.0159
-2.250 -0.1823 0.00834 0.00247 -0.0043 0.8596 0.0189
-2.000 -0.1543 0.00812 0.00222 -0.0042 0.8514 0.0223
-1.750 -0.1263 0.00782 0.00193 -0.0041 0.8398 0.0348
-1.500 -0.0986 0.00715 0.00167 -0.0043 0.8287 0.1598
-1.250 -0.0711 0.00578 0.00138 -0.0052 0.8210 0.4805
-1.000 -0.0426 0.00512 0.00130 -0.0056 0.8150 0.6532
-0.750 -0.0140 0.00487 0.00128 -0.0058 0.8085 0.7292
-0.500 0.0144 0.00474 0.00127 -0.0057 0.8010 0.7782
-0.250 0.0422 0.00462 0.00127 -0.0055 0.7926 0.8249
0.000 0.0695 0.00455 0.00129 -0.0051 0.7845 0.8581
0.250 0.0965 0.00453 0.00130 -0.0047 0.7750 0.8791
0.500 0.1249 0.00452 0.00128 -0.0047 0.7629 0.8904
0.750 0.1534 0.00454 0.00126 -0.0047 0.7462 0.9008
1.000 0.1810 0.00458 0.00125 -0.0045 0.7205 0.9097
1.250 0.2093 0.00470 0.00123 -0.0045 0.6778 0.9185
1.500 0.2375 0.00498 0.00126 -0.0046 0.6100 0.9270
1.750 0.2654 0.00537 0.00134 -0.0048 0.5274 0.9346
2.000 0.2931 0.00584 0.00146 -0.0051 0.4356 0.9427
2.250 0.3192 0.00624 0.00158 -0.0049 0.3604 0.9501
2.500 0.3457 0.00657 0.00169 -0.0048 0.3064 0.9583
2.750 0.3704 0.00678 0.00175 -0.0042 0.2682 0.9662
3.000 0.3964 0.00696 0.00182 -0.0039 0.2405 0.9745
3.250 0.4238 0.00713 0.00189 -0.0039 0.2186 0.9826
3.500 0.4557 0.00730 0.00199 -0.0049 0.2008 0.9881
3.750 0.4886 0.00747 0.00210 -0.0062 0.1866 0.9933
4.000 0.5225 0.00767 0.00224 -0.0077 0.1742 0.9981
4.250 0.5522 0.00785 0.00236 -0.0083 0.1640 1.0000
4.500 0.5806 0.00800 0.00250 -0.0087 0.1573 1.0000
4.750 0.6093 0.00818 0.00264 -0.0091 0.1509 1.0000
5.000 0.6381 0.00836 0.00282 -0.0095 0.1451 1.0000
5.250 0.6670 0.00852 0.00297 -0.0099 0.1403 1.0000
5.500 0.6956 0.00875 0.00317 -0.0103 0.1334 1.0000
5.750 0.7245 0.00888 0.00333 -0.0107 0.1295 1.0000
6.000 0.7531 0.00907 0.00350 -0.0111 0.1233 1.0000
6.250 0.7817 0.00926 0.00369 -0.0115 0.1171 1.0000
6.500 0.8100 0.00947 0.00386 -0.0118 0.1085 1.0000
6.750 0.8383 0.00968 0.00407 -0.0122 0.0999 1.0000
7.000 0.8662 0.00996 0.00431 -0.0125 0.0882 1.0000
7.250 0.8934 0.01038 0.00461 -0.0127 0.0698 1.0000
7.500 0.9203 0.01084 0.00499 -0.0129 0.0554 1.0000
7.750 0.9471 0.01129 0.00542 -0.0131 0.0457 1.0000
8.000 0.9737 0.01177 0.00586 -0.0133 0.0377 1.0000
8.250 1.0004 0.01218 0.00627 -0.0134 0.0323 1.0000
8.500 1.0266 0.01268 0.00677 -0.0135 0.0268 1.0000
8.750 1.0524 0.01323 0.00731 -0.0135 0.0227 1.0000
9.000 1.0782 0.01376 0.00788 -0.0135 0.0202 1.0000
9.250 1.1041 0.01423 0.00840 -0.0134 0.0186 1.0000
9.500 1.1288 0.01490 0.00909 -0.0133 0.0168 1.0000
9.750 1.1520 0.01579 0.01010 -0.0130 0.0155 1.0000
10.000 1.1769 0.01631 0.01070 -0.0129 0.0151 1.0000
10.250 1.2016 0.01682 0.01127 -0.0128 0.0144 1.0000
10.500 1.2259 0.01734 0.01184 -0.0126 0.0136 1.0000
10.750 1.2495 0.01794 0.01248 -0.0124 0.0129 1.0000
11.000 1.2709 0.01884 0.01345 -0.0120 0.0121 1.0000
11.250 1.2877 0.02029 0.01506 -0.0110 0.0114 1.0000
11.500 1.3102 0.02089 0.01574 -0.0107 0.0112 1.0000
11.750 1.3316 0.02157 0.01651 -0.0102 0.0109 1.0000
12.000 1.3518 0.02233 0.01736 -0.0096 0.0105 1.0000
12.250 1.3711 0.02315 0.01827 -0.0090 0.0101 1.0000
12.500 1.3895 0.02400 0.01920 -0.0083 0.0098 1.0000
12.750 1.4071 0.02486 0.02013 -0.0075 0.0094 1.0000
13.000 1.4225 0.02585 0.02121 -0.0065 0.0090 1.0000
13.250 1.4314 0.02723 0.02269 -0.0049 0.0087 1.0000
13.500 1.4264 0.02938 0.02501 -0.0020 0.0083 1.0000
13.750 1.4243 0.03151 0.02730 0.0002 0.0081 1.0000
14.000 1.4354 0.03265 0.02853 0.0011 0.0079 1.0000
14.250 1.4442 0.03403 0.03002 0.0019 0.0077 1.0000
14.500 1.4512 0.03564 0.03174 0.0027 0.0075 1.0000
14.750 1.4568 0.03748 0.03368 0.0032 0.0072 1.0000
15.000 1.4606 0.03959 0.03589 0.0035 0.0069 1.0000
15.250 1.4632 0.04195 0.03835 0.0035 0.0067 1.0000
15.500 1.4637 0.04474 0.04123 0.0031 0.0064 1.0000
15.750 1.4562 0.04880 0.04542 0.0018 0.0063 1.0000
16.000 1.4420 0.05444 0.05121 -0.0009 0.0062 1.0000
16.250 1.4207 0.06221 0.05916 -0.0056 0.0062 1.0000
16.500 1.3889 0.07319 0.07038 -0.0127 0.0063 1.0000
16.750 1.3336 0.08869 0.08615 -0.0214 0.0066 1.0000
17.000 1.2743 0.10381 0.10147 -0.0291 0.0070 1.0000
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Polar data table (+)
Polar graphs
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