S5020 (s5020-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 200,000 Max Cl/Cd: 64.43 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5020-il-200000.txt Download as CSV file: xf-s5020-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S5020
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5167 0.09860 0.09559 0.0199 1.0000 0.0324
-8.000 -0.5170 0.09515 0.09221 0.0151 1.0000 0.0331
-7.750 -0.5179 0.09158 0.08871 0.0100 1.0000 0.0334
-7.500 -0.5129 0.08719 0.08431 0.0032 1.0000 0.0336
-7.000 -0.4966 0.07686 0.07390 -0.0056 1.0000 0.0341
-6.750 -0.4907 0.07164 0.06879 -0.0044 1.0000 0.0353
-6.500 -0.4778 0.06844 0.06563 -0.0048 1.0000 0.0367
-6.250 -0.4619 0.06462 0.06180 -0.0077 1.0000 0.0386
-6.000 -0.4410 0.06024 0.05734 -0.0124 1.0000 0.0421
-5.750 -0.4056 0.05783 0.05415 -0.0189 0.9253 0.0456
-5.500 -0.4017 0.05058 0.04699 -0.0189 0.9021 0.0472
-5.250 -0.3896 0.04803 0.04440 -0.0177 0.8828 0.0489
-5.000 -0.3742 0.04552 0.04172 -0.0171 0.8660 0.0514
-4.750 -0.3532 0.04303 0.03888 -0.0168 0.8516 0.0567
-4.500 -0.3344 0.03932 0.03466 -0.0166 0.8391 0.0607
-4.250 -0.3159 0.03670 0.03203 -0.0161 0.8271 0.0634
-3.750 -0.2715 0.03197 0.02671 -0.0150 0.8042 0.0768
-3.500 -0.2479 0.03033 0.02467 -0.0144 0.7934 0.0891
-3.250 -0.2254 0.02862 0.02276 -0.0139 0.7832 0.1035
-3.000 -0.2023 0.02687 0.02084 -0.0133 0.7733 0.1182
-2.750 -0.1783 0.02506 0.01897 -0.0130 0.7627 0.1342
-2.500 -0.1376 0.02033 0.01302 -0.0097 0.7554 0.0520
-2.250 -0.1080 0.01927 0.01149 -0.0084 0.7458 0.0450
-2.000 -0.0806 0.01756 0.00959 -0.0077 0.7360 0.0440
-1.750 -0.0533 0.01698 0.00878 -0.0070 0.7270 0.0458
-1.500 -0.0262 0.01581 0.00751 -0.0064 0.7174 0.0460
-1.250 0.0004 0.01477 0.00644 -0.0057 0.7077 0.0464
-1.000 0.0259 0.01389 0.00553 -0.0049 0.6993 0.0482
-0.750 0.0522 0.01334 0.00495 -0.0044 0.6893 0.0517
-0.500 0.0792 0.01298 0.00451 -0.0039 0.6797 0.0581
-0.250 0.1501 0.00942 0.00383 -0.0122 0.6697 1.0000
0.000 0.1759 0.00948 0.00367 -0.0116 0.6597 1.0000
0.250 0.2019 0.00954 0.00358 -0.0111 0.6495 1.0000
0.500 0.2277 0.00961 0.00349 -0.0105 0.6400 1.0000
0.750 0.2535 0.00968 0.00340 -0.0099 0.6302 1.0000
1.000 0.2798 0.00975 0.00338 -0.0094 0.6195 1.0000
1.250 0.3059 0.00983 0.00335 -0.0089 0.6095 1.0000
1.500 0.3317 0.00992 0.00330 -0.0083 0.6001 1.0000
1.750 0.3581 0.01000 0.00332 -0.0079 0.5888 1.0000
2.000 0.3845 0.01009 0.00334 -0.0075 0.5779 1.0000
2.250 0.4107 0.01018 0.00335 -0.0070 0.5674 1.0000
2.500 0.4367 0.01029 0.00336 -0.0065 0.5570 1.0000
2.750 0.4632 0.01037 0.00341 -0.0061 0.5449 1.0000
3.000 0.4897 0.01048 0.00348 -0.0058 0.5329 1.0000
3.250 0.5161 0.01059 0.00355 -0.0054 0.5206 1.0000
3.500 0.5425 0.01071 0.00364 -0.0050 0.5082 1.0000
3.750 0.5688 0.01084 0.00373 -0.0046 0.4955 1.0000
4.000 0.5952 0.01098 0.00383 -0.0043 0.4823 1.0000
4.250 0.6216 0.01112 0.00395 -0.0039 0.4686 1.0000
4.500 0.6480 0.01128 0.00410 -0.0036 0.4541 1.0000
4.750 0.6744 0.01145 0.00426 -0.0033 0.4390 1.0000
5.000 0.7007 0.01163 0.00443 -0.0030 0.4231 1.0000
5.250 0.7270 0.01184 0.00463 -0.0028 0.4068 1.0000
5.500 0.7530 0.01207 0.00486 -0.0025 0.3899 1.0000
5.750 0.7790 0.01234 0.00508 -0.0022 0.3730 1.0000
6.000 0.8050 0.01262 0.00538 -0.0020 0.3547 1.0000
6.250 0.8308 0.01293 0.00569 -0.0018 0.3362 1.0000
6.500 0.8563 0.01329 0.00604 -0.0015 0.3179 1.0000
6.750 0.8816 0.01369 0.00643 -0.0013 0.2996 1.0000
7.000 0.9069 0.01410 0.00686 -0.0011 0.2804 1.0000
7.250 0.9316 0.01458 0.00731 -0.0009 0.2621 1.0000
7.500 0.9561 0.01510 0.00784 -0.0007 0.2439 1.0000
7.750 0.9805 0.01562 0.00840 -0.0005 0.2256 1.0000
8.000 1.0043 0.01621 0.00899 -0.0002 0.2079 1.0000
8.250 1.0274 0.01688 0.00963 0.0000 0.1913 1.0000
8.500 1.0503 0.01758 0.01035 0.0004 0.1752 1.0000
8.750 1.0728 0.01829 0.01113 0.0007 0.1593 1.0000
9.000 1.0946 0.01909 0.01197 0.0010 0.1448 1.0000
9.250 1.1157 0.01989 0.01282 0.0014 0.1301 1.0000
9.500 1.1364 0.02065 0.01361 0.0017 0.1147 1.0000
9.750 1.1562 0.02147 0.01447 0.0021 0.1006 1.0000
10.000 1.1752 0.02234 0.01540 0.0025 0.0873 1.0000
10.250 1.1932 0.02329 0.01641 0.0029 0.0755 1.0000
10.500 1.2096 0.02437 0.01756 0.0035 0.0637 1.0000
10.750 1.2202 0.02599 0.01916 0.0044 0.0453 1.0000
11.000 1.2198 0.02848 0.02161 0.0058 0.0313 1.0000
11.250 1.2139 0.03088 0.02408 0.0074 0.0267 1.0000
11.500 1.2131 0.03313 0.02642 0.0081 0.0236 1.0000
11.750 1.2056 0.03629 0.02965 0.0082 0.0219 1.0000
12.000 1.1988 0.03961 0.03305 0.0082 0.0211 1.0000
12.250 1.1985 0.04246 0.03608 0.0080 0.0199 1.0000
12.500 1.1961 0.04560 0.03936 0.0077 0.0190 1.0000
12.750 1.1942 0.04875 0.04264 0.0073 0.0184 1.0000
13.000 1.1916 0.05208 0.04609 0.0067 0.0178 1.0000
13.250 1.1888 0.05552 0.04968 0.0061 0.0174 1.0000
13.500 1.1849 0.05919 0.05344 0.0051 0.0168 1.0000
13.750 1.1816 0.06284 0.05722 0.0042 0.0166 1.0000
14.000 1.1769 0.06677 0.06127 0.0032 0.0162 1.0000
14.250 1.1718 0.07089 0.06551 0.0020 0.0160 1.0000
14.500 1.1649 0.07541 0.07017 0.0006 0.0157 1.0000
14.750 1.1568 0.08039 0.07531 -0.0013 0.0156 1.0000
15.000 1.1484 0.08562 0.08071 -0.0036 0.0156 1.0000
15.250 1.1385 0.09134 0.08661 -0.0064 0.0156 1.0000
15.500 1.1264 0.09774 0.09319 -0.0098 0.0156 1.0000
15.750 1.1136 0.10455 0.10018 -0.0136 0.0156 1.0000
16.000 1.0995 0.11196 0.10777 -0.0180 0.0157 1.0000
16.250 1.0826 0.12038 0.11639 -0.0231 0.0159 1.0000
16.500 1.0615 0.13032 0.12653 -0.0293 0.0161 1.0000
16.750 1.0189 0.14714 0.14364 -0.0398 0.0171 1.0000
17.000 0.9378 0.17961 0.17612 -0.0570 0.0202 1.0000
17.250 0.9296 0.18889 0.18536 -0.0612 0.0208 1.0000
17.500 0.9280 0.19570 0.19214 -0.0643 0.0211 1.0000
17.750 0.7252 0.19082 0.18768 -0.0582 0.0275 1.0000
18.000 0.7301 0.19412 0.19100 -0.0591 0.0288 1.0000
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Polar data table (+)
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