SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 500,000 Max Cl/Cd: 80.67 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6060-il-500000-n5.txt Download as CSV file: xf-sd6060-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD6060-104-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5249 0.08420 0.08202 -0.0244 1.0000 0.0056
-9.750 -0.5337 0.07743 0.07529 -0.0281 1.0000 0.0054
-9.500 -0.5453 0.06999 0.06789 -0.0330 1.0000 0.0053
-9.250 -0.5570 0.06144 0.05933 -0.0414 1.0000 0.0052
-9.000 -0.5834 0.05394 0.05173 -0.0452 1.0000 0.0051
-8.750 -0.6106 0.04621 0.04380 -0.0453 1.0000 0.0050
-8.500 -0.6249 0.03782 0.03494 -0.0462 0.9809 0.0049
-8.250 -0.6196 0.03128 0.02780 -0.0473 0.9598 0.0048
-8.000 -0.6101 0.02711 0.02309 -0.0463 0.9437 0.0048
-7.750 -0.5973 0.02430 0.01984 -0.0446 0.9300 0.0049
-7.500 -0.5814 0.02214 0.01729 -0.0431 0.9182 0.0049
-7.250 -0.5628 0.02039 0.01521 -0.0418 0.9079 0.0050
-7.000 -0.5426 0.01892 0.01345 -0.0407 0.8985 0.0050
-6.750 -0.5206 0.01778 0.01207 -0.0397 0.8892 0.0051
-6.500 -0.4985 0.01655 0.01062 -0.0388 0.8805 0.0053
-6.250 -0.4777 0.01507 0.00892 -0.0376 0.8720 0.0056
-6.000 -0.4544 0.01421 0.00793 -0.0369 0.8631 0.0059
-5.750 -0.4303 0.01356 0.00716 -0.0363 0.8551 0.0062
-5.500 -0.4055 0.01302 0.00652 -0.0358 0.8466 0.0066
-5.250 -0.3805 0.01248 0.00589 -0.0353 0.8384 0.0070
-5.000 -0.3551 0.01209 0.00541 -0.0349 0.8304 0.0077
-4.750 -0.3291 0.01172 0.00495 -0.0346 0.8219 0.0083
-4.500 -0.3036 0.01126 0.00439 -0.0341 0.8139 0.0089
-4.250 -0.2778 0.01082 0.00383 -0.0337 0.8055 0.0102
-4.000 -0.2514 0.01052 0.00346 -0.0334 0.7974 0.0118
-3.750 -0.2249 0.01022 0.00312 -0.0331 0.7891 0.0159
-3.500 -0.1987 0.00987 0.00282 -0.0329 0.7808 0.0324
-3.250 -0.1725 0.00958 0.00257 -0.0326 0.7728 0.0565
-3.000 -0.1460 0.00927 0.00236 -0.0325 0.7641 0.0885
-2.750 -0.1197 0.00898 0.00217 -0.0323 0.7560 0.1271
-2.500 -0.0942 0.00855 0.00199 -0.0321 0.7475 0.2000
-2.250 -0.0685 0.00815 0.00183 -0.0320 0.7392 0.2765
-1.750 -0.0178 0.00733 0.00155 -0.0314 0.7222 0.4580
-1.500 0.0073 0.00697 0.00145 -0.0310 0.7140 0.5492
-1.250 0.0326 0.00670 0.00140 -0.0305 0.7052 0.6281
-1.000 0.0584 0.00653 0.00138 -0.0301 0.6966 0.6863
-0.500 0.1113 0.00638 0.00136 -0.0293 0.6787 0.7613
-0.250 0.1378 0.00635 0.00136 -0.0289 0.6695 0.7899
0.000 0.1645 0.00635 0.00137 -0.0285 0.6601 0.8138
0.250 0.1911 0.00634 0.00139 -0.0281 0.6504 0.8351
0.500 0.2176 0.00637 0.00142 -0.0277 0.6412 0.8553
1.000 0.2705 0.00643 0.00148 -0.0268 0.6216 0.8870
1.250 0.2971 0.00648 0.00151 -0.0264 0.6115 0.9002
1.500 0.3236 0.00654 0.00156 -0.0260 0.6009 0.9117
1.750 0.3504 0.00661 0.00160 -0.0257 0.5897 0.9218
2.000 0.3776 0.00667 0.00164 -0.0255 0.5773 0.9313
2.250 0.4051 0.00675 0.00170 -0.0254 0.5642 0.9406
2.500 0.4339 0.00684 0.00175 -0.0256 0.5497 0.9484
2.750 0.4623 0.00694 0.00181 -0.0258 0.5336 0.9568
3.000 0.4936 0.00706 0.00189 -0.0266 0.5149 0.9628
3.250 0.5230 0.00721 0.00198 -0.0270 0.4937 0.9701
3.500 0.5558 0.00739 0.00209 -0.0283 0.4691 0.9745
3.750 0.5870 0.00760 0.00221 -0.0292 0.4421 0.9800
4.000 0.6184 0.00785 0.00237 -0.0302 0.4122 0.9848
4.250 0.6510 0.00815 0.00255 -0.0316 0.3802 0.9887
4.500 0.6823 0.00847 0.00275 -0.0327 0.3472 0.9932
4.750 0.7139 0.00885 0.00299 -0.0339 0.3104 0.9975
5.000 0.7394 0.00935 0.00329 -0.0340 0.2639 1.0000
5.250 0.7580 0.00987 0.00359 -0.0326 0.2175 1.0000
5.500 0.7774 0.01037 0.00390 -0.0313 0.1800 1.0000
5.750 0.7985 0.01077 0.00420 -0.0303 0.1553 1.0000
6.000 0.8204 0.01115 0.00450 -0.0295 0.1343 1.0000
6.250 0.8416 0.01163 0.00488 -0.0285 0.1084 1.0000
6.500 0.8633 0.01210 0.00525 -0.0277 0.0878 1.0000
6.750 0.8846 0.01261 0.00567 -0.0269 0.0666 1.0000
7.000 0.9058 0.01315 0.00612 -0.0260 0.0476 1.0000
7.250 0.9260 0.01378 0.00666 -0.0250 0.0290 1.0000
7.500 0.9467 0.01437 0.00719 -0.0241 0.0197 1.0000
7.750 0.9679 0.01490 0.00776 -0.0232 0.0164 1.0000
8.000 0.9896 0.01538 0.00830 -0.0224 0.0152 1.0000
8.250 1.0109 0.01587 0.00887 -0.0215 0.0145 1.0000
8.500 1.0315 0.01642 0.00949 -0.0205 0.0137 1.0000
8.750 1.0513 0.01700 0.01015 -0.0195 0.0130 1.0000
9.000 1.0701 0.01764 0.01083 -0.0184 0.0120 1.0000
9.250 1.0863 0.01846 0.01173 -0.0169 0.0112 1.0000
9.500 1.0997 0.01944 0.01283 -0.0151 0.0105 1.0000
9.750 1.1179 0.02000 0.01347 -0.0139 0.0101 1.0000
10.000 1.1336 0.02061 0.01416 -0.0124 0.0095 1.0000
10.250 1.1452 0.02139 0.01503 -0.0102 0.0091 1.0000
10.500 1.1561 0.02221 0.01593 -0.0081 0.0086 1.0000
10.750 1.1671 0.02307 0.01687 -0.0062 0.0082 1.0000
11.000 1.1774 0.02402 0.01789 -0.0044 0.0077 1.0000
11.250 1.1854 0.02515 0.01909 -0.0026 0.0072 1.0000
11.500 1.1869 0.02684 0.02091 -0.0003 0.0069 1.0000
11.750 1.1996 0.02774 0.02191 0.0007 0.0065 1.0000
12.000 1.2081 0.02901 0.02329 0.0021 0.0062 1.0000
12.250 1.2173 0.03026 0.02465 0.0031 0.0058 1.0000
12.500 1.2237 0.03182 0.02631 0.0043 0.0055 1.0000
12.750 1.2292 0.03351 0.02811 0.0052 0.0052 1.0000
13.000 1.2378 0.03496 0.02964 0.0058 0.0048 1.0000
13.250 1.2410 0.03700 0.03179 0.0065 0.0047 1.0000
13.500 1.2450 0.03904 0.03392 0.0068 0.0045 1.0000
13.750 1.2431 0.04180 0.03679 0.0071 0.0043 1.0000
14.000 1.2389 0.04495 0.04007 0.0071 0.0042 1.0000
14.250 1.2340 0.04833 0.04360 0.0067 0.0042 1.0000
14.500 1.2345 0.05124 0.04666 0.0063 0.0040 1.0000
14.750 1.2301 0.05489 0.05047 0.0054 0.0038 1.0000
15.000 1.2220 0.05921 0.05496 0.0041 0.0039 1.0000
15.250 1.2177 0.06326 0.05915 0.0026 0.0037 1.0000
15.500 1.2087 0.06819 0.06424 0.0006 0.0036 1.0000
15.750 1.1985 0.07362 0.06983 -0.0019 0.0035 1.0000
16.000 1.1845 0.07994 0.07631 -0.0049 0.0036 1.0000
16.250 1.1712 0.08647 0.08301 -0.0083 0.0035 1.0000
16.500 1.1580 0.09329 0.08997 -0.0119 0.0035 1.0000
16.750 1.1414 0.10100 0.09783 -0.0162 0.0035 1.0000
17.000 1.1254 0.10886 0.10584 -0.0205 0.0035 1.0000
17.250 1.1081 0.11726 0.11439 -0.0252 0.0035 1.0000
17.500 1.0913 0.12587 0.12313 -0.0301 0.0034 1.0000
17.750 1.0732 0.13505 0.13244 -0.0354 0.0034 1.0000
18.000 1.0545 0.14459 0.14211 -0.0408 0.0035 1.0000
18.250 1.0343 0.15496 0.15259 -0.0467 0.0035 1.0000
18.500 1.0114 0.16662 0.16436 -0.0534 0.0037 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SD6060-104-88 (sd6060-il)