SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 50,000 Max Cl/Cd: 33.15 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6060-il-50000.txt Download as CSV file: xf-sd6060-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3452 0.10456 0.09831 -0.0139 1.0000 0.2587
-9.250 -0.3493 0.10132 0.09513 -0.0145 1.0000 0.2681
-9.000 -0.3619 0.09911 0.09301 -0.0152 1.0000 0.2796
-8.750 -0.3439 0.09436 0.08826 -0.0145 1.0000 0.2920
-8.500 -0.3351 0.09027 0.08420 -0.0142 1.0000 0.3027
-8.250 -0.3320 0.08666 0.08064 -0.0139 1.0000 0.3169
-8.000 -0.3302 0.08324 0.07728 -0.0134 1.0000 0.3331
-7.750 -0.3378 0.08040 0.07454 -0.0128 1.0000 0.3507
-7.500 -0.3364 0.07679 0.07098 -0.0120 1.0000 0.3669
-7.250 -0.4106 0.08297 0.07675 -0.0063 1.0000 0.3736
-6.250 -0.5271 0.05627 0.04943 -0.0333 1.0000 0.1362
-6.000 -0.5247 0.05172 0.04448 -0.0317 1.0000 0.1219
-5.750 -0.5170 0.04802 0.04067 -0.0297 1.0000 0.1165
-5.500 -0.5119 0.04432 0.03617 -0.0275 1.0000 0.1080
-5.250 -0.5005 0.04113 0.03272 -0.0256 1.0000 0.1059
-5.000 -0.4874 0.03822 0.02940 -0.0237 1.0000 0.1042
-4.750 -0.4722 0.03570 0.02640 -0.0218 1.0000 0.1059
-4.500 -0.4550 0.03346 0.02357 -0.0200 1.0000 0.1097
-4.250 -0.4359 0.03120 0.02125 -0.0187 1.0000 0.1151
-4.000 -0.4144 0.02930 0.01890 -0.0171 1.0000 0.1219
-3.750 -0.3934 0.02759 0.01707 -0.0158 1.0000 0.1377
-3.500 -0.3715 0.02588 0.01544 -0.0144 1.0000 0.1627
-3.250 -0.3490 0.02405 0.01393 -0.0131 1.0000 0.2141
-3.000 -0.0985 0.02117 0.01309 -0.0364 1.0000 1.0000
-2.750 -0.1126 0.02098 0.01283 -0.0320 1.0000 1.0000
-2.500 -0.1251 0.02082 0.01257 -0.0275 1.0000 1.0000
-2.250 -0.1354 0.02069 0.01231 -0.0232 1.0000 1.0000
-2.000 -0.1427 0.02058 0.01206 -0.0191 1.0000 1.0000
-1.750 -0.1463 0.02051 0.01183 -0.0155 1.0000 1.0000
-1.500 -0.1455 0.02051 0.01164 -0.0125 1.0000 1.0000
-1.250 -0.1411 0.02059 0.01147 -0.0099 1.0000 1.0000
-1.000 -0.1332 0.02074 0.01141 -0.0079 1.0000 1.0000
-0.750 -0.1224 0.02095 0.01141 -0.0063 1.0000 1.0000
-0.500 -0.1097 0.02123 0.01149 -0.0051 1.0000 1.0000
-0.250 -0.0957 0.02156 0.01164 -0.0041 1.0000 1.0000
0.000 -0.0808 0.02195 0.01183 -0.0032 1.0000 1.0000
0.250 -0.0653 0.02238 0.01210 -0.0025 1.0000 1.0000
0.500 -0.0493 0.02285 0.01244 -0.0020 1.0000 1.0000
0.750 -0.0101 0.02385 0.01329 -0.0059 0.9905 1.0000
1.000 0.0329 0.02496 0.01425 -0.0104 0.9783 1.0000
1.250 0.0743 0.02603 0.01522 -0.0145 0.9655 1.0000
1.500 0.1143 0.02706 0.01619 -0.0182 0.9523 1.0000
1.750 0.1530 0.02807 0.01714 -0.0216 0.9384 1.0000
2.000 0.1902 0.02904 0.01809 -0.0245 0.9242 1.0000
2.250 0.2264 0.02997 0.01903 -0.0272 0.9093 1.0000
2.500 0.2616 0.03088 0.01996 -0.0296 0.8938 1.0000
2.750 0.2969 0.03177 0.02088 -0.0318 0.8779 1.0000
3.000 0.3334 0.03263 0.02181 -0.0341 0.8616 1.0000
3.250 0.3734 0.03344 0.02273 -0.0367 0.8449 1.0000
3.500 0.4093 0.03419 0.02357 -0.0384 0.8276 1.0000
3.750 0.4358 0.03492 0.02440 -0.0387 0.8088 1.0000
4.000 0.4738 0.03548 0.02510 -0.0403 0.7900 1.0000
4.250 0.5267 0.03565 0.02553 -0.0435 0.7718 1.0000
4.500 0.5455 0.03634 0.02633 -0.0421 0.7501 1.0000
4.750 0.5978 0.03600 0.02630 -0.0442 0.7305 1.0000
5.000 0.6256 0.03618 0.02665 -0.0432 0.7081 1.0000
5.250 0.6750 0.03512 0.02588 -0.0434 0.6878 1.0000
5.500 0.7035 0.03485 0.02582 -0.0416 0.6638 1.0000
5.750 0.7473 0.03338 0.02466 -0.0403 0.6408 1.0000
6.000 0.7898 0.03167 0.02319 -0.0384 0.6155 1.0000
6.250 0.8231 0.03044 0.02214 -0.0358 0.5860 1.0000
6.500 0.8484 0.02977 0.02166 -0.0329 0.5515 1.0000
6.750 0.8800 0.02854 0.02048 -0.0301 0.5135 1.0000
7.000 0.9042 0.02802 0.01992 -0.0270 0.4702 1.0000
7.250 0.9243 0.02802 0.01979 -0.0240 0.4227 1.0000
7.500 0.9425 0.02843 0.01996 -0.0210 0.3724 1.0000
7.750 0.9554 0.02949 0.02076 -0.0179 0.3211 1.0000
8.000 0.9647 0.03089 0.02186 -0.0148 0.2690 1.0000
8.250 0.9707 0.03249 0.02298 -0.0116 0.2186 1.0000
8.500 0.9777 0.03470 0.02493 -0.0088 0.1752 1.0000
8.750 0.9903 0.03724 0.02737 -0.0067 0.1433 1.0000
9.000 1.0150 0.04038 0.03038 -0.0059 0.1242 1.0000
9.250 1.0321 0.04327 0.03350 -0.0045 0.1122 1.0000
9.500 1.0447 0.04659 0.03728 -0.0028 0.1047 1.0000
9.750 1.0593 0.05014 0.04114 -0.0014 0.1002 1.0000
10.000 1.0768 0.05466 0.04572 -0.0008 0.0968 1.0000
10.250 1.0732 0.05852 0.05016 0.0017 0.0960 1.0000
10.500 1.0654 0.06251 0.05461 0.0040 0.0954 1.0000
10.750 1.0529 0.06652 0.05899 0.0062 0.0951 1.0000
11.000 1.0375 0.07060 0.06333 0.0082 0.0952 1.0000
11.250 1.0184 0.07464 0.06757 0.0098 0.0955 1.0000
11.500 0.9982 0.07919 0.07227 0.0103 0.0959 1.0000
11.750 0.9813 0.08424 0.07744 0.0099 0.0965 1.0000
12.000 0.8868 0.09688 0.09027 -0.0001 0.1072 1.0000
12.250 0.8492 0.10880 0.10216 -0.0085 0.1122 1.0000
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Polar data table (+)
Polar graphs
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