S2048 (s2048-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 50,000 Max Cl/Cd: 37.24 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2048-il-50000.txt Download as CSV file: xf-s2048-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S2048
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4320 0.09582 0.08903 -0.0135 1.0000 0.2998
-7.750 -0.4322 0.09323 0.08648 -0.0124 1.0000 0.3163
-7.500 -0.4402 0.09133 0.08471 -0.0110 1.0000 0.3330
-7.250 -0.4348 0.08813 0.08156 -0.0092 1.0000 0.3502
-7.000 -0.4320 0.08577 0.07927 -0.0066 1.0000 0.3751
-6.750 -0.4238 0.08297 0.07651 -0.0039 1.0000 0.4030
-6.500 -0.4176 0.08034 0.07394 -0.0010 1.0000 0.4314
-6.250 -0.4026 0.07681 0.07043 0.0010 1.0000 0.4557
-5.250 -0.4562 0.04630 0.03847 -0.0417 1.0000 0.1352
-5.000 -0.4384 0.04251 0.03441 -0.0414 1.0000 0.1322
-4.750 -0.4178 0.03888 0.03024 -0.0414 1.0000 0.1287
-4.500 -0.3923 0.03570 0.02603 -0.0413 1.0000 0.1225
-4.250 -0.3687 0.03284 0.02281 -0.0407 1.0000 0.1215
-4.000 -0.3437 0.03044 0.01995 -0.0399 1.0000 0.1220
-3.750 -0.3195 0.02819 0.01751 -0.0391 1.0000 0.1261
-3.500 -0.2950 0.02668 0.01568 -0.0381 1.0000 0.1370
-3.250 -0.2710 0.02498 0.01397 -0.0369 1.0000 0.1488
-3.000 -0.2470 0.02335 0.01235 -0.0353 1.0000 0.1672
-2.750 -0.2232 0.02154 0.01089 -0.0344 1.0000 0.2252
-2.250 -0.1441 0.01829 0.01040 -0.0275 1.0000 1.0000
-2.000 -0.1485 0.01784 0.00976 -0.0239 1.0000 1.0000
-1.750 -0.1388 0.01761 0.00919 -0.0224 1.0000 1.0000
-1.500 -0.1209 0.01755 0.00879 -0.0220 1.0000 1.0000
-1.250 -0.1000 0.01759 0.00850 -0.0220 1.0000 1.0000
-1.000 -0.0781 0.01770 0.00832 -0.0219 1.0000 1.0000
-0.750 -0.0559 0.01786 0.00822 -0.0219 1.0000 1.0000
-0.500 -0.0337 0.01806 0.00815 -0.0218 1.0000 1.0000
-0.250 -0.0115 0.01830 0.00819 -0.0217 1.0000 1.0000
0.000 0.0105 0.01858 0.00829 -0.0216 1.0000 1.0000
0.250 0.0323 0.01889 0.00845 -0.0214 1.0000 1.0000
0.500 0.0538 0.01923 0.00865 -0.0213 1.0000 1.0000
0.750 0.0751 0.01961 0.00892 -0.0211 1.0000 1.0000
1.000 0.0961 0.02003 0.00925 -0.0210 1.0000 1.0000
1.250 0.1168 0.02049 0.00964 -0.0208 1.0000 1.0000
1.500 0.1372 0.02100 0.01010 -0.0207 1.0000 1.0000
1.750 0.1572 0.02155 0.01061 -0.0206 1.0000 1.0000
2.000 0.1767 0.02215 0.01120 -0.0205 1.0000 1.0000
2.250 0.1958 0.02282 0.01187 -0.0204 1.0000 1.0000
2.500 0.2142 0.02355 0.01262 -0.0204 1.0000 1.0000
2.750 0.2321 0.02437 0.01348 -0.0205 1.0000 1.0000
3.000 0.2769 0.02581 0.01503 -0.0258 0.9859 1.0000
3.250 0.3477 0.02744 0.01684 -0.0352 0.9569 1.0000
3.500 0.4097 0.02840 0.01805 -0.0422 0.9266 1.0000
3.750 0.4672 0.02889 0.01881 -0.0476 0.8948 1.0000
4.000 0.5310 0.02890 0.01919 -0.0531 0.8623 1.0000
4.250 0.5933 0.02831 0.01900 -0.0573 0.8276 1.0000
4.500 0.6654 0.02674 0.01790 -0.0613 0.7914 1.0000
4.750 0.7259 0.02484 0.01646 -0.0622 0.7485 1.0000
5.000 0.7716 0.02325 0.01511 -0.0607 0.6935 1.0000
5.250 0.8050 0.02237 0.01420 -0.0578 0.6268 1.0000
5.500 0.8308 0.02231 0.01393 -0.0546 0.5561 1.0000
5.750 0.8517 0.02297 0.01423 -0.0517 0.4885 1.0000
6.000 0.8708 0.02407 0.01492 -0.0491 0.4239 1.0000
6.250 0.8870 0.02549 0.01604 -0.0465 0.3585 1.0000
6.500 0.9024 0.02730 0.01745 -0.0439 0.2915 1.0000
6.750 0.9204 0.02943 0.01925 -0.0418 0.2353 1.0000
7.000 0.9419 0.03170 0.02141 -0.0403 0.1966 1.0000
7.250 0.9627 0.03388 0.02359 -0.0389 0.1685 1.0000
7.500 0.9857 0.03652 0.02637 -0.0377 0.1492 1.0000
7.750 1.0075 0.03918 0.02893 -0.0367 0.1320 1.0000
8.000 1.0246 0.04239 0.03275 -0.0347 0.1221 1.0000
8.250 1.0378 0.04607 0.03691 -0.0328 0.1141 1.0000
8.500 1.0551 0.04949 0.04032 -0.0317 0.1051 1.0000
8.750 1.0588 0.05400 0.04555 -0.0290 0.1037 1.0000
9.000 1.0577 0.05862 0.05076 -0.0265 0.1025 1.0000
9.250 1.0515 0.06334 0.05596 -0.0242 0.1018 1.0000
9.500 1.0406 0.06813 0.06113 -0.0221 0.1016 1.0000
9.750 1.0264 0.07302 0.06631 -0.0205 0.1022 1.0000
10.000 1.0098 0.07783 0.07131 -0.0192 0.1031 1.0000
10.250 0.9933 0.08260 0.07618 -0.0183 0.1041 1.0000
10.500 0.9799 0.08777 0.08142 -0.0183 0.1049 1.0000
10.750 0.9701 0.09341 0.08713 -0.0190 0.1056 1.0000
11.000 0.9249 0.10409 0.09786 -0.0258 0.1187 1.0000
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Polar data table (+)
Polar graphs
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