S6062 8% (s6062-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S6062 8% (s6062-il) Reynolds number: 50,000 Max Cl/Cd: 35.56 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6062-il-50000-n5.txt Download as CSV file: xf-s6062-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6062 8%
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 -0.5306 0.10333 0.09642 -0.0123 1.0000 0.0464
-9.000 -0.5207 0.09970 0.09280 -0.0114 1.0000 0.0447
-8.750 -0.5175 0.09567 0.08881 -0.0129 1.0000 0.0436
-8.500 -0.5162 0.09143 0.08464 -0.0149 1.0000 0.0424
-8.250 -0.5166 0.08703 0.08031 -0.0175 1.0000 0.0414
-8.000 -0.5184 0.08251 0.07587 -0.0206 1.0000 0.0404
-7.750 -0.5206 0.07736 0.07079 -0.0248 1.0000 0.0394
-7.500 -0.5213 0.07194 0.06535 -0.0288 1.0000 0.0383
-7.250 -0.5213 0.06639 0.05972 -0.0322 1.0000 0.0371
-7.000 -0.5202 0.06064 0.05377 -0.0351 1.0000 0.0359
-6.750 -0.5163 0.05508 0.04781 -0.0372 1.0000 0.0348
-6.500 -0.5061 0.05088 0.04322 -0.0377 1.0000 0.0342
-6.250 -0.4936 0.04708 0.03902 -0.0377 1.0000 0.0339
-6.000 -0.4794 0.04345 0.03498 -0.0373 1.0000 0.0338
-5.750 -0.4638 0.03999 0.03109 -0.0368 1.0000 0.0339
-5.500 -0.4469 0.03667 0.02737 -0.0360 1.0000 0.0342
-5.250 -0.4286 0.03381 0.02416 -0.0351 1.0000 0.0350
-5.000 -0.4096 0.03162 0.02167 -0.0342 1.0000 0.0373
-4.750 -0.3891 0.02971 0.01946 -0.0331 1.0000 0.0407
-4.500 -0.3672 0.02776 0.01713 -0.0318 1.0000 0.0438
-4.250 -0.3449 0.02598 0.01500 -0.0303 1.0000 0.0461
-4.000 -0.3243 0.02435 0.01331 -0.0288 1.0000 0.0496
-3.750 -0.3033 0.02305 0.01184 -0.0274 1.0000 0.0558
-3.500 -0.2821 0.02183 0.01057 -0.0262 1.0000 0.0729
-3.250 -0.2612 0.02031 0.00933 -0.0254 1.0000 0.1264
-3.000 -0.2430 0.01839 0.00841 -0.0246 1.0000 0.2842
-2.750 -0.2289 0.01698 0.00804 -0.0223 1.0000 0.4939
-2.500 -0.2183 0.01619 0.00804 -0.0174 1.0000 0.6962
-2.250 -0.1888 0.01592 0.00791 -0.0153 1.0000 0.8796
-2.000 -0.1131 0.01576 0.00713 -0.0242 1.0000 1.0000
-1.750 -0.1030 0.01576 0.00685 -0.0219 1.0000 1.0000
-1.500 -0.0899 0.01581 0.00663 -0.0200 1.0000 1.0000
-1.250 -0.0748 0.01590 0.00648 -0.0186 1.0000 1.0000
-1.000 -0.0583 0.01603 0.00635 -0.0173 1.0000 1.0000
-0.750 -0.0258 0.01626 0.00634 -0.0192 0.9927 1.0000
-0.500 0.0158 0.01655 0.00639 -0.0226 0.9812 1.0000
-0.250 0.0579 0.01683 0.00649 -0.0261 0.9699 1.0000
0.000 0.0993 0.01708 0.00658 -0.0293 0.9580 1.0000
0.250 0.1395 0.01731 0.00670 -0.0322 0.9455 1.0000
0.500 0.1796 0.01753 0.00685 -0.0350 0.9330 1.0000
0.750 0.2196 0.01773 0.00702 -0.0376 0.9202 1.0000
1.000 0.2574 0.01791 0.00718 -0.0397 0.9066 1.0000
1.250 0.2935 0.01808 0.00736 -0.0413 0.8924 1.0000
1.500 0.3280 0.01822 0.00756 -0.0425 0.8775 1.0000
1.750 0.3612 0.01835 0.00773 -0.0433 0.8621 1.0000
2.000 0.3931 0.01846 0.00789 -0.0438 0.8462 1.0000
2.250 0.4217 0.01859 0.00809 -0.0435 0.8286 1.0000
2.500 0.4491 0.01871 0.00833 -0.0430 0.8099 1.0000
2.750 0.4771 0.01878 0.00849 -0.0424 0.7914 1.0000
3.000 0.5032 0.01887 0.00868 -0.0414 0.7711 1.0000
3.250 0.5291 0.01894 0.00885 -0.0403 0.7499 1.0000
3.500 0.5539 0.01903 0.00911 -0.0390 0.7268 1.0000
3.750 0.5791 0.01909 0.00927 -0.0376 0.7029 1.0000
4.000 0.6038 0.01917 0.00946 -0.0361 0.6767 1.0000
4.250 0.6276 0.01930 0.00970 -0.0346 0.6473 1.0000
4.500 0.6509 0.01946 0.01003 -0.0330 0.6145 1.0000
4.750 0.6743 0.01963 0.01027 -0.0312 0.5791 1.0000
5.000 0.6966 0.01991 0.01060 -0.0295 0.5381 1.0000
5.250 0.7181 0.02027 0.01101 -0.0277 0.4914 1.0000
5.500 0.7386 0.02077 0.01147 -0.0259 0.4389 1.0000
5.750 0.7570 0.02147 0.01212 -0.0240 0.3740 1.0000
6.000 0.7711 0.02261 0.01279 -0.0220 0.2804 1.0000
6.250 0.7824 0.02448 0.01384 -0.0205 0.1656 1.0000
6.500 0.7959 0.02672 0.01550 -0.0193 0.0934 1.0000
6.750 0.8114 0.02878 0.01739 -0.0181 0.0662 1.0000
7.000 0.8280 0.03066 0.01931 -0.0167 0.0569 1.0000
7.250 0.8464 0.03244 0.02130 -0.0153 0.0515 1.0000
7.500 0.8647 0.03438 0.02332 -0.0141 0.0480 1.0000
7.750 0.8868 0.03657 0.02581 -0.0129 0.0457 1.0000
8.000 0.9099 0.03898 0.02859 -0.0119 0.0437 1.0000
8.250 0.9302 0.04154 0.03151 -0.0109 0.0412 1.0000
8.500 0.9467 0.04403 0.03430 -0.0100 0.0385 1.0000
8.750 0.9608 0.04681 0.03730 -0.0091 0.0366 1.0000
9.000 0.9724 0.05051 0.04129 -0.0082 0.0356 1.0000
9.250 0.9795 0.05423 0.04541 -0.0070 0.0353 1.0000
9.500 0.9819 0.05804 0.04967 -0.0058 0.0352 1.0000
9.750 0.9793 0.06199 0.05401 -0.0046 0.0351 1.0000
10.000 0.9720 0.06599 0.05833 -0.0037 0.0351 1.0000
10.250 0.9592 0.06985 0.06243 -0.0027 0.0351 1.0000
10.500 0.9438 0.07404 0.06682 -0.0027 0.0352 1.0000
10.750 0.9277 0.07876 0.07170 -0.0040 0.0353 1.0000
11.000 0.9109 0.08419 0.07726 -0.0066 0.0355 1.0000
11.250 0.8915 0.09064 0.08389 -0.0111 0.0358 1.0000
11.500 0.8626 0.10098 0.09436 -0.0195 0.0368 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S6062 8% (s6062-il)