NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 200,000 Max Cl/Cd: 46.19 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20606-il-200000-n5.txt Download as CSV file: xf-sc20606-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0606 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6194 0.08566 0.08201 -0.0137 1.0000 0.0160
-9.250 -0.6225 0.08048 0.07688 -0.0169 1.0000 0.0160
-9.000 -0.6276 0.07474 0.07119 -0.0214 1.0000 0.0159
-8.750 -0.6288 0.06713 0.06354 -0.0305 1.0000 0.0157
-8.500 -0.6281 0.06065 0.05694 -0.0357 1.0000 0.0156
-8.250 -0.6237 0.05446 0.05056 -0.0395 1.0000 0.0153
-8.000 -0.6145 0.04832 0.04414 -0.0428 1.0000 0.0151
-7.750 -0.5998 0.04219 0.03762 -0.0456 1.0000 0.0148
-7.500 -0.5796 0.03623 0.03116 -0.0482 1.0000 0.0146
-7.250 -0.5544 0.03086 0.02519 -0.0505 1.0000 0.0146
-7.000 -0.5265 0.02659 0.02031 -0.0522 1.0000 0.0149
-6.750 -0.4978 0.02346 0.01664 -0.0532 1.0000 0.0154
-6.500 -0.4696 0.02121 0.01397 -0.0538 1.0000 0.0160
-6.250 -0.4423 0.02007 0.01252 -0.0539 1.0000 0.0170
-6.000 -0.4146 0.01804 0.01030 -0.0546 1.0000 0.0188
-5.750 -0.3870 0.01678 0.00890 -0.0548 1.0000 0.0195
-5.500 -0.3590 0.01569 0.00771 -0.0551 1.0000 0.0206
-5.250 -0.3303 0.01474 0.00668 -0.0556 1.0000 0.0222
-5.000 -0.3011 0.01394 0.00577 -0.0562 1.0000 0.0244
-4.750 -0.2708 0.01313 0.00485 -0.0570 1.0000 0.0287
-4.500 -0.2421 0.01269 0.00439 -0.0575 1.0000 0.0381
-4.250 -0.2122 0.01214 0.00385 -0.0583 1.0000 0.0533
-4.000 -0.1822 0.01162 0.00347 -0.0592 1.0000 0.0847
-3.750 -0.1498 0.01084 0.00309 -0.0609 1.0000 0.1838
-3.500 -0.1147 0.00985 0.00280 -0.0636 1.0000 0.3687
-3.250 -0.0826 0.00922 0.00285 -0.0649 1.0000 0.5519
-3.000 -0.0553 0.00910 0.00291 -0.0648 1.0000 0.6180
-2.750 -0.0288 0.00907 0.00297 -0.0643 1.0000 0.6653
-2.500 -0.0031 0.00909 0.00307 -0.0636 1.0000 0.7013
-2.250 0.0229 0.00913 0.00314 -0.0631 1.0000 0.7240
-2.000 0.0490 0.00917 0.00321 -0.0626 1.0000 0.7411
-1.750 0.0744 0.00922 0.00331 -0.0620 1.0000 0.7578
-1.500 0.1004 0.00927 0.00338 -0.0615 1.0000 0.7713
-1.250 0.1274 0.00932 0.00345 -0.0613 1.0000 0.7823
-1.000 0.1534 0.00936 0.00355 -0.0609 1.0000 0.7902
-0.750 0.1800 0.00942 0.00366 -0.0607 1.0000 0.7989
-0.500 0.2069 0.00949 0.00379 -0.0606 1.0000 0.8076
-0.250 0.2330 0.00955 0.00395 -0.0603 1.0000 0.8146
0.000 0.2600 0.00964 0.00412 -0.0602 1.0000 0.8228
0.250 0.3104 0.00942 0.00403 -0.0649 0.9837 0.8280
0.500 0.3649 0.00893 0.00367 -0.0699 0.9365 0.8339
0.750 0.4217 0.00913 0.00311 -0.0743 0.6775 0.8386
1.000 0.4360 0.01077 0.00344 -0.0715 0.3810 0.8457
1.250 0.4578 0.01185 0.00383 -0.0707 0.1983 0.8529
1.500 0.4813 0.01273 0.00421 -0.0701 0.0891 0.8606
1.750 0.5062 0.01325 0.00460 -0.0696 0.0549 0.8680
2.000 0.5318 0.01375 0.00508 -0.0690 0.0397 0.8761
2.250 0.5563 0.01419 0.00557 -0.0682 0.0297 0.8836
2.500 0.5810 0.01493 0.00635 -0.0675 0.0247 0.8919
2.750 0.6047 0.01557 0.00716 -0.0664 0.0225 0.9003
3.000 0.6282 0.01637 0.00806 -0.0653 0.0208 0.9096
3.250 0.6519 0.01728 0.00908 -0.0643 0.0196 0.9196
3.500 0.6750 0.01830 0.01022 -0.0631 0.0188 0.9304
3.750 0.6982 0.01943 0.01149 -0.0619 0.0181 0.9441
4.000 0.7206 0.02133 0.01363 -0.0608 0.0164 0.9675
4.250 0.7491 0.02253 0.01512 -0.0608 0.0155 1.0000
4.500 0.7763 0.02477 0.01775 -0.0605 0.0149 1.0000
4.750 0.8018 0.02766 0.02115 -0.0599 0.0144 1.0000
5.000 0.8248 0.03132 0.02537 -0.0588 0.0142 1.0000
5.250 0.8449 0.03577 0.03038 -0.0575 0.0141 1.0000
5.500 0.8620 0.04076 0.03590 -0.0561 0.0143 1.0000
5.750 0.8764 0.04612 0.04171 -0.0549 0.0145 1.0000
6.000 0.8882 0.05168 0.04766 -0.0539 0.0147 1.0000
6.250 0.8986 0.05755 0.05388 -0.0533 0.0143 1.0000
6.500 0.9068 0.06351 0.06014 -0.0534 0.0135 1.0000
6.750 0.9119 0.06936 0.06621 -0.0541 0.0130 1.0000
7.000 0.9126 0.07569 0.07271 -0.0555 0.0131 1.0000
7.250 0.9101 0.08211 0.07927 -0.0578 0.0133 1.0000
7.500 0.9046 0.08845 0.08568 -0.0610 0.0135 1.0000
7.750 0.8948 0.09445 0.09171 -0.0648 0.0137 1.0000
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Polar data table (+)
Polar graphs
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