NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 50,000 Max Cl/Cd: 24.61 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20610-il-50000-n5.txt Download as CSV file: xf-sc20610-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0610 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6210 0.09866 0.09051 -0.0345 1.0000 0.0608
-11.000 -0.6326 0.09153 0.08342 -0.0388 1.0000 0.0606
-10.750 -0.6489 0.08486 0.07675 -0.0428 1.0000 0.0603
-10.500 -0.6683 0.07899 0.07087 -0.0457 1.0000 0.0600
-10.250 -0.6902 0.07413 0.06599 -0.0470 1.0000 0.0597
-10.000 -0.7102 0.06947 0.06123 -0.0483 1.0000 0.0596
-9.750 -0.7250 0.06486 0.05642 -0.0493 1.0000 0.0598
-9.500 -0.7342 0.06038 0.05162 -0.0499 1.0000 0.0602
-9.250 -0.7371 0.05596 0.04676 -0.0505 1.0000 0.0609
-9.000 -0.7312 0.05212 0.04260 -0.0506 1.0000 0.0617
-8.750 -0.7193 0.04900 0.03928 -0.0505 1.0000 0.0627
-8.500 -0.7048 0.04616 0.03618 -0.0504 1.0000 0.0641
-8.250 -0.6883 0.04371 0.03350 -0.0503 1.0000 0.0665
-8.000 -0.6700 0.04110 0.03049 -0.0504 1.0000 0.0699
-7.750 -0.6493 0.03839 0.02717 -0.0504 1.0000 0.0729
-7.500 -0.6287 0.03628 0.02501 -0.0499 1.0000 0.0756
-7.250 -0.6073 0.03471 0.02330 -0.0494 1.0000 0.0802
-7.000 -0.5845 0.03303 0.02127 -0.0488 1.0000 0.0854
-6.750 -0.5631 0.03154 0.01978 -0.0477 1.0000 0.0899
-6.500 -0.5411 0.03038 0.01851 -0.0467 1.0000 0.0969
-6.250 -0.5199 0.02922 0.01727 -0.0451 1.0000 0.1031
-6.000 -0.4986 0.02828 0.01630 -0.0437 1.0000 0.1117
-5.750 -0.4776 0.02731 0.01537 -0.0424 1.0000 0.1207
-5.500 -0.4559 0.02641 0.01444 -0.0413 1.0000 0.1322
-5.250 -0.4334 0.02545 0.01353 -0.0407 1.0000 0.1476
-5.000 -0.4096 0.02440 0.01265 -0.0408 1.0000 0.1698
-4.750 -0.3840 0.02312 0.01170 -0.0415 1.0000 0.2098
-4.500 -0.3542 0.02115 0.01077 -0.0441 1.0000 0.3407
-4.250 -0.3498 0.02127 0.01208 -0.0370 1.0000 0.5103
-4.000 -0.3319 0.02192 0.01271 -0.0336 1.0000 0.6087
-3.750 -0.3106 0.02254 0.01316 -0.0315 1.0000 0.6592
-3.500 -0.2948 0.02322 0.01375 -0.0277 1.0000 0.6920
-3.250 -0.2797 0.02385 0.01426 -0.0239 1.0000 0.7225
-3.000 -0.2710 0.02436 0.01475 -0.0182 1.0000 0.7474
-2.750 -0.2589 0.02468 0.01500 -0.0138 1.0000 0.7739
-2.500 -0.2483 0.02474 0.01502 -0.0092 1.0000 0.7958
-2.250 -0.2324 0.02463 0.01481 -0.0063 1.0000 0.8143
-2.000 -0.2144 0.02439 0.01449 -0.0043 1.0000 0.8277
-1.750 -0.1929 0.02414 0.01415 -0.0034 1.0000 0.8380
-1.500 -0.1679 0.02395 0.01388 -0.0034 1.0000 0.8475
-1.250 -0.1462 0.02368 0.01354 -0.0026 1.0000 0.8551
-1.000 -0.1195 0.02355 0.01335 -0.0032 1.0000 0.8628
-0.750 -0.0967 0.02332 0.01309 -0.0027 1.0000 0.8691
-0.500 -0.0702 0.02322 0.01296 -0.0033 1.0000 0.8750
-0.250 -0.0437 0.02314 0.01287 -0.0039 1.0000 0.8801
0.000 -0.0185 0.02305 0.01279 -0.0042 1.0000 0.8852
0.250 0.0090 0.02307 0.01284 -0.0051 1.0000 0.8903
0.500 0.0349 0.02307 0.01288 -0.0055 1.0000 0.8951
0.750 0.0607 0.02310 0.01298 -0.0061 1.0000 0.8999
1.000 0.0881 0.02323 0.01319 -0.0070 1.0000 0.9048
1.250 0.1139 0.02335 0.01340 -0.0076 1.0000 0.9093
1.500 0.1395 0.02351 0.01368 -0.0083 1.0000 0.9140
1.750 0.1826 0.02383 0.01416 -0.0123 0.9890 0.9177
2.000 0.2368 0.02412 0.01465 -0.0180 0.9717 0.9207
2.250 0.2891 0.02401 0.01477 -0.0226 0.9461 0.9236
2.500 0.3460 0.02329 0.01434 -0.0268 0.9061 0.9258
2.750 0.3969 0.02212 0.01343 -0.0287 0.8559 0.9281
3.000 0.4318 0.02115 0.01269 -0.0278 0.7926 0.9315
3.250 0.4958 0.02015 0.01091 -0.0294 0.5320 0.9321
3.500 0.5100 0.02185 0.01121 -0.0268 0.3133 0.9361
3.750 0.5289 0.02327 0.01197 -0.0259 0.2161 0.9410
4.000 0.5529 0.02445 0.01282 -0.0258 0.1734 0.9460
4.250 0.5797 0.02541 0.01370 -0.0259 0.1478 0.9509
4.500 0.6086 0.02643 0.01469 -0.0264 0.1310 0.9559
5.000 0.6732 0.02872 0.01712 -0.0282 0.1068 0.9664
5.750 0.7697 0.03322 0.02184 -0.0315 0.0838 1.0000
6.000 0.8008 0.03531 0.02437 -0.0322 0.0787 1.0000
6.250 0.8289 0.03720 0.02651 -0.0329 0.0735 1.0000
6.500 0.8565 0.03956 0.02892 -0.0338 0.0703 1.0000
6.750 0.8804 0.04248 0.03249 -0.0336 0.0675 1.0000
7.000 0.9016 0.04536 0.03588 -0.0335 0.0642 1.0000
7.250 0.9217 0.04812 0.03897 -0.0334 0.0616 1.0000
7.500 0.9400 0.05124 0.04244 -0.0333 0.0603 1.0000
7.750 0.9554 0.05468 0.04618 -0.0331 0.0593 1.0000
8.000 0.9669 0.05856 0.05035 -0.0327 0.0584 1.0000
8.250 0.9678 0.06317 0.05555 -0.0315 0.0577 1.0000
8.500 0.9632 0.06804 0.06093 -0.0305 0.0570 1.0000
8.750 0.9535 0.07307 0.06636 -0.0297 0.0566 1.0000
9.000 0.9385 0.07823 0.07182 -0.0294 0.0564 1.0000
9.250 0.9193 0.08340 0.07721 -0.0296 0.0565 1.0000
9.500 0.8993 0.08946 0.08342 -0.0317 0.0568 1.0000
9.750 0.8811 0.09645 0.09053 -0.0359 0.0571 1.0000
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Polar data table (+)
Polar graphs
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