SG6041 (sg6041-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SG6041 (sg6041-il) Reynolds number: 50,000 Max Cl/Cd: 35.45 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6041-il-50000.txt Download as CSV file: xf-sg6041-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SG6041
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4144 0.10972 0.10264 -0.0221 1.0000 0.2413
-9.000 -0.4361 0.10911 0.10219 -0.0229 1.0000 0.2510
-8.750 -0.4205 0.10488 0.09798 -0.0213 1.0000 0.2647
-8.500 -0.4115 0.10128 0.09441 -0.0200 1.0000 0.2776
-8.250 -0.4078 0.09824 0.09144 -0.0189 1.0000 0.2908
-8.000 -0.4065 0.09544 0.08871 -0.0175 1.0000 0.3051
-7.750 -0.4071 0.09288 0.08623 -0.0159 1.0000 0.3217
-7.500 -0.4179 0.09109 0.08457 -0.0139 1.0000 0.3400
-7.250 -0.4021 0.08751 0.08102 -0.0114 1.0000 0.3631
-7.000 -0.4168 0.08630 0.07995 -0.0082 1.0000 0.3857
-6.750 -0.4150 0.08406 0.07779 -0.0045 1.0000 0.4163
-6.500 -0.4094 0.08166 0.07546 -0.0010 1.0000 0.4465
-5.250 -0.5020 0.05150 0.04403 -0.0291 1.0000 0.1452
-5.000 -0.4861 0.04695 0.03899 -0.0287 1.0000 0.1296
-4.750 -0.4701 0.04340 0.03513 -0.0277 1.0000 0.1262
-4.500 -0.4516 0.04004 0.03122 -0.0269 1.0000 0.1229
-4.250 -0.4300 0.03703 0.02747 -0.0259 1.0000 0.1191
-4.000 -0.4071 0.03445 0.02431 -0.0247 1.0000 0.1183
-3.750 -0.3854 0.03224 0.02203 -0.0238 1.0000 0.1247
-3.500 -0.3607 0.03042 0.01965 -0.0226 1.0000 0.1313
-3.250 -0.3367 0.02848 0.01767 -0.0217 1.0000 0.1422
-3.000 -0.3120 0.02687 0.01589 -0.0205 1.0000 0.1588
-2.750 -0.2880 0.02535 0.01448 -0.0192 1.0000 0.1859
-2.500 -0.2642 0.02384 0.01317 -0.0179 1.0000 0.2322
-2.250 -0.1425 0.02093 0.01297 -0.0247 1.0000 1.0000
-2.000 -0.1436 0.02063 0.01246 -0.0210 1.0000 1.0000
-1.750 -0.1425 0.02038 0.01199 -0.0177 1.0000 1.0000
-1.500 -0.1379 0.02022 0.01159 -0.0148 1.0000 1.0000
-1.250 -0.1286 0.02016 0.01128 -0.0126 1.0000 1.0000
-1.000 -0.1155 0.02021 0.01108 -0.0111 1.0000 1.0000
-0.750 -0.1001 0.02033 0.01095 -0.0099 1.0000 1.0000
-0.500 -0.0834 0.02052 0.01092 -0.0089 1.0000 1.0000
-0.250 -0.0658 0.02077 0.01096 -0.0081 1.0000 1.0000
0.000 -0.0478 0.02107 0.01108 -0.0074 1.0000 1.0000
0.250 -0.0296 0.02141 0.01125 -0.0068 1.0000 1.0000
0.500 -0.0112 0.02181 0.01150 -0.0063 1.0000 1.0000
0.750 0.0071 0.02225 0.01182 -0.0058 1.0000 1.0000
1.000 0.0253 0.02274 0.01220 -0.0054 1.0000 1.0000
1.250 0.0433 0.02329 0.01265 -0.0050 1.0000 1.0000
1.500 0.0611 0.02389 0.01318 -0.0047 1.0000 1.0000
1.750 0.0785 0.02455 0.01378 -0.0044 1.0000 1.0000
2.000 0.0955 0.02527 0.01445 -0.0043 1.0000 1.0000
2.250 0.1122 0.02606 0.01521 -0.0041 1.0000 1.0000
2.500 0.1725 0.02792 0.01707 -0.0122 0.9781 1.0000
2.750 0.2304 0.02953 0.01871 -0.0193 0.9560 1.0000
3.000 0.2810 0.03067 0.01992 -0.0247 0.9319 1.0000
3.250 0.3300 0.03163 0.02097 -0.0294 0.9072 1.0000
3.500 0.3853 0.03238 0.02185 -0.0346 0.8825 1.0000
3.750 0.4366 0.03275 0.02237 -0.0385 0.8561 1.0000
4.000 0.4842 0.03282 0.02264 -0.0412 0.8284 1.0000
4.250 0.5353 0.03245 0.02247 -0.0438 0.8001 1.0000
4.500 0.5921 0.03142 0.02173 -0.0462 0.7713 1.0000
4.750 0.6557 0.02954 0.02016 -0.0484 0.7417 1.0000
5.000 0.7199 0.02701 0.01795 -0.0496 0.7088 1.0000
5.250 0.7687 0.02503 0.01612 -0.0487 0.6652 1.0000
5.500 0.8064 0.02387 0.01491 -0.0467 0.6090 1.0000
5.750 0.8373 0.02362 0.01437 -0.0445 0.5441 1.0000
6.000 0.8582 0.02431 0.01469 -0.0418 0.4809 1.0000
6.250 0.8795 0.02534 0.01529 -0.0397 0.4257 1.0000
6.500 0.8993 0.02663 0.01633 -0.0378 0.3796 1.0000
6.750 0.9196 0.02802 0.01757 -0.0362 0.3411 1.0000
7.000 0.9420 0.02953 0.01889 -0.0350 0.3092 1.0000
7.250 0.9632 0.03116 0.02052 -0.0338 0.2828 1.0000
7.500 0.9867 0.03296 0.02227 -0.0330 0.2609 1.0000
7.750 1.0057 0.03475 0.02422 -0.0316 0.2414 1.0000
8.000 1.0267 0.03692 0.02654 -0.0305 0.2264 1.0000
8.250 1.0449 0.03903 0.02882 -0.0291 0.2120 1.0000
8.500 1.0625 0.04143 0.03142 -0.0277 0.2003 1.0000
8.750 1.0823 0.04390 0.03397 -0.0267 0.1893 1.0000
9.000 1.0903 0.04646 0.03697 -0.0243 0.1798 1.0000
9.250 1.1008 0.04968 0.04049 -0.0224 0.1733 1.0000
9.500 1.1007 0.05304 0.04432 -0.0196 0.1676 1.0000
9.750 1.1140 0.05600 0.04735 -0.0182 0.1600 1.0000
10.000 1.1014 0.06010 0.05197 -0.0149 0.1578 1.0000
10.250 1.0856 0.06459 0.05685 -0.0119 0.1570 1.0000
10.500 1.0641 0.06931 0.06186 -0.0092 0.1573 1.0000
10.750 1.0366 0.07407 0.06681 -0.0066 0.1582 1.0000
11.000 1.0088 0.07928 0.07213 -0.0052 0.1595 1.0000
11.250 0.9853 0.08521 0.07813 -0.0054 0.1608 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SG6041 (sg6041-il)