SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 50,000 Max Cl/Cd: 37.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2030-il-50000.txt Download as CSV file: xf-sd2030-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD2030-086-88
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4314 0.09183 0.08523 -0.0160 1.0000 0.2924
-7.250 -0.4568 0.09137 0.08496 -0.0138 1.0000 0.3035
-7.000 -0.4599 0.08885 0.08253 -0.0114 1.0000 0.3180
-6.750 -0.4336 0.08420 0.07785 -0.0093 1.0000 0.3384
-6.500 -0.4377 0.08198 0.07570 -0.0062 1.0000 0.3570
-6.250 -0.4576 0.08077 0.07465 -0.0029 1.0000 0.3756
-6.000 -0.4450 0.07763 0.07154 0.0008 1.0000 0.4026
-4.750 -0.4407 0.04869 0.04111 -0.0331 1.0000 0.1577
-4.500 -0.4201 0.04415 0.03610 -0.0336 1.0000 0.1418
-4.250 -0.3998 0.04057 0.03211 -0.0334 1.0000 0.1363
-4.000 -0.3749 0.03726 0.02796 -0.0334 1.0000 0.1288
-3.750 -0.3516 0.03439 0.02472 -0.0329 1.0000 0.1261
-3.500 -0.3267 0.03191 0.02177 -0.0323 1.0000 0.1247
-3.250 -0.3011 0.02981 0.01922 -0.0315 1.0000 0.1257
-3.000 -0.2754 0.02807 0.01705 -0.0307 1.0000 0.1318
-2.750 -0.2507 0.02665 0.01546 -0.0298 1.0000 0.1431
-2.500 -0.2254 0.02513 0.01386 -0.0288 1.0000 0.1565
-2.250 -0.2006 0.02376 0.01256 -0.0276 1.0000 0.1890
-2.000 -0.1758 0.02174 0.01124 -0.0268 1.0000 0.2918
-1.750 -0.1387 0.01842 0.01028 -0.0243 1.0000 1.0000
-1.500 -0.1198 0.01850 0.00986 -0.0231 1.0000 1.0000
-1.250 -0.1006 0.01863 0.00959 -0.0221 1.0000 1.0000
-1.000 -0.0810 0.01879 0.00943 -0.0212 1.0000 1.0000
-0.750 -0.0612 0.01898 0.00933 -0.0204 1.0000 1.0000
-0.500 -0.0412 0.01920 0.00929 -0.0196 1.0000 1.0000
-0.250 -0.0212 0.01946 0.00933 -0.0189 1.0000 1.0000
0.000 -0.0011 0.01975 0.00943 -0.0183 1.0000 1.0000
0.250 0.0189 0.02008 0.00958 -0.0177 1.0000 1.0000
0.500 0.0388 0.02044 0.00980 -0.0171 1.0000 1.0000
0.750 0.0586 0.02083 0.01006 -0.0166 1.0000 1.0000
1.000 0.0782 0.02127 0.01039 -0.0161 1.0000 1.0000
1.250 0.0976 0.02174 0.01078 -0.0157 1.0000 1.0000
1.500 0.1167 0.02226 0.01123 -0.0153 1.0000 1.0000
1.750 0.1355 0.02283 0.01174 -0.0149 1.0000 1.0000
2.000 0.1539 0.02345 0.01233 -0.0146 1.0000 1.0000
2.250 0.1720 0.02413 0.01300 -0.0143 1.0000 1.0000
2.500 0.1895 0.02488 0.01374 -0.0141 1.0000 1.0000
2.750 0.2065 0.02570 0.01457 -0.0140 1.0000 1.0000
3.000 0.2369 0.02696 0.01588 -0.0165 0.9937 1.0000
3.250 0.2998 0.02880 0.01783 -0.0249 0.9682 1.0000
3.500 0.3598 0.03023 0.01943 -0.0321 0.9417 1.0000
3.750 0.4171 0.03121 0.02060 -0.0382 0.9141 1.0000
4.000 0.4706 0.03174 0.02135 -0.0429 0.8848 1.0000
4.250 0.5236 0.03188 0.02178 -0.0467 0.8538 1.0000
4.500 0.5809 0.03147 0.02168 -0.0503 0.8218 1.0000
4.750 0.6514 0.02997 0.02065 -0.0543 0.7893 1.0000
5.000 0.7124 0.02791 0.01900 -0.0556 0.7518 1.0000
5.250 0.7741 0.02511 0.01663 -0.0555 0.7056 1.0000
5.500 0.8185 0.02310 0.01472 -0.0532 0.6393 1.0000
5.750 0.8487 0.02258 0.01385 -0.0499 0.5515 1.0000
6.000 0.8686 0.02346 0.01414 -0.0466 0.4644 1.0000
6.250 0.8863 0.02492 0.01511 -0.0439 0.3907 1.0000
6.500 0.9056 0.02661 0.01636 -0.0419 0.3310 1.0000
6.750 0.9272 0.02847 0.01795 -0.0404 0.2844 1.0000
7.000 0.9485 0.03030 0.01965 -0.0391 0.2476 1.0000
7.250 0.9724 0.03244 0.02179 -0.0381 0.2205 1.0000
7.500 0.9944 0.03454 0.02395 -0.0370 0.1981 1.0000
7.750 1.0167 0.03714 0.02679 -0.0359 0.1824 1.0000
8.000 1.0352 0.03954 0.02942 -0.0344 0.1671 1.0000
8.250 1.0540 0.04259 0.03273 -0.0330 0.1566 1.0000
8.500 1.0721 0.04556 0.03581 -0.0317 0.1451 1.0000
8.750 1.0766 0.04884 0.03980 -0.0286 0.1378 1.0000
9.000 1.0897 0.05260 0.04371 -0.0270 0.1306 1.0000
9.250 1.0846 0.05651 0.04833 -0.0237 0.1265 1.0000
9.500 1.1014 0.06027 0.05199 -0.0228 0.1182 1.0000
9.750 1.0900 0.06470 0.05696 -0.0196 0.1174 1.0000
10.000 1.0747 0.06926 0.06195 -0.0168 0.1169 1.0000
10.250 1.0580 0.07392 0.06689 -0.0145 0.1170 1.0000
10.500 1.0396 0.07853 0.07169 -0.0126 0.1174 1.0000
10.750 1.0199 0.08327 0.07656 -0.0111 0.1179 1.0000
11.000 1.0045 0.08851 0.08188 -0.0107 0.1184 1.0000
11.250 0.9064 0.10452 0.09793 -0.0230 0.1470 1.0000
11.500 0.9078 0.11047 0.10390 -0.0240 0.1458 1.0000
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Polar data table (+)
Polar graphs
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