SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Reynolds number: 50,000 Max Cl/Cd: 26.73 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc1012r8-il-50000-n5.txt Download as CSV file: xf-sc1012r8-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1012R8 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3940 0.10854 0.10148 -0.0084 1.0000 0.1370
-8.500 -0.4227 0.10623 0.09930 -0.0157 1.0000 0.1425
-7.750 -0.4297 0.08421 0.07720 -0.0293 1.0000 0.0750
-7.500 -0.4182 0.08125 0.07428 -0.0284 1.0000 0.0726
-7.250 -0.4176 0.07743 0.07048 -0.0291 1.0000 0.0706
-7.000 -0.4378 0.07086 0.06360 -0.0323 1.0000 0.0654
-6.750 -0.4325 0.06793 0.06069 -0.0314 1.0000 0.0647
-6.500 -0.4298 0.06490 0.05762 -0.0303 1.0000 0.0640
-6.250 -0.4276 0.06183 0.05448 -0.0291 1.0000 0.0633
-6.000 -0.4246 0.05876 0.05128 -0.0278 1.0000 0.0626
-5.750 -0.4203 0.05577 0.04812 -0.0264 1.0000 0.0622
-5.500 -0.4142 0.05294 0.04509 -0.0249 1.0000 0.0623
-5.250 -0.4061 0.05024 0.04215 -0.0234 1.0000 0.0627
-5.000 -0.3961 0.04766 0.03930 -0.0220 1.0000 0.0633
-4.750 -0.3840 0.04519 0.03653 -0.0206 1.0000 0.0638
-4.500 -0.3700 0.04285 0.03388 -0.0192 1.0000 0.0641
-4.250 -0.3542 0.04067 0.03140 -0.0180 1.0000 0.0642
-4.000 -0.3368 0.03864 0.02905 -0.0168 1.0000 0.0645
-3.750 -0.3180 0.03677 0.02685 -0.0158 1.0000 0.0649
-3.500 -0.2924 0.03509 0.02493 -0.0159 0.9975 0.0663
-3.250 -0.2489 0.03357 0.02332 -0.0194 0.9875 0.0694
-3.000 -0.2027 0.03189 0.02130 -0.0227 0.9768 0.0724
-2.750 -0.1552 0.03028 0.01936 -0.0259 0.9654 0.0748
-2.500 -0.1098 0.02910 0.01825 -0.0290 0.9524 0.0796
-2.250 -0.0644 0.02799 0.01698 -0.0315 0.9392 0.0853
-2.000 -0.0207 0.02696 0.01604 -0.0338 0.9256 0.0915
-1.750 0.0208 0.02606 0.01514 -0.0357 0.9109 0.1010
-1.500 0.0583 0.02522 0.01431 -0.0368 0.8949 0.1133
-1.250 0.0927 0.02435 0.01355 -0.0374 0.8776 0.1329
-1.000 0.1246 0.02334 0.01277 -0.0376 0.8589 0.1702
-0.750 0.1385 0.02045 0.01244 -0.0343 0.8414 0.6294
-0.500 0.2598 0.01993 0.01207 -0.0455 0.8190 1.0000
-0.250 0.2836 0.01972 0.01159 -0.0438 0.7882 1.0000
0.000 0.3056 0.01952 0.01114 -0.0417 0.7537 1.0000
0.250 0.3262 0.01939 0.01074 -0.0394 0.7156 1.0000
0.500 0.3463 0.01934 0.01040 -0.0371 0.6749 1.0000
0.750 0.3665 0.01936 0.01011 -0.0349 0.6336 1.0000
1.000 0.3866 0.01948 0.00988 -0.0327 0.5926 1.0000
1.250 0.4065 0.01970 0.00975 -0.0307 0.5533 1.0000
1.500 0.4263 0.02001 0.00970 -0.0288 0.5163 1.0000
1.750 0.4462 0.02037 0.00974 -0.0271 0.4822 1.0000
2.000 0.4666 0.02080 0.00984 -0.0256 0.4512 1.0000
2.250 0.4877 0.02126 0.01003 -0.0242 0.4225 1.0000
2.500 0.5091 0.02176 0.01025 -0.0230 0.3964 1.0000
2.750 0.5309 0.02228 0.01055 -0.0219 0.3717 1.0000
3.000 0.5530 0.02283 0.01088 -0.0209 0.3496 1.0000
3.250 0.5754 0.02340 0.01124 -0.0199 0.3293 1.0000
3.500 0.5983 0.02400 0.01166 -0.0191 0.3111 1.0000
3.750 0.6216 0.02461 0.01212 -0.0183 0.2946 1.0000
4.000 0.6449 0.02524 0.01262 -0.0176 0.2797 1.0000
4.250 0.6684 0.02590 0.01311 -0.0169 0.2672 1.0000
4.500 0.6920 0.02656 0.01365 -0.0162 0.2555 1.0000
4.750 0.7159 0.02726 0.01432 -0.0156 0.2447 1.0000
5.000 0.7395 0.02796 0.01482 -0.0150 0.2363 1.0000
5.250 0.7636 0.02875 0.01566 -0.0145 0.2272 1.0000
5.500 0.7872 0.02949 0.01625 -0.0139 0.2203 1.0000
5.750 0.8108 0.03038 0.01719 -0.0134 0.2128 1.0000
6.000 0.8343 0.03121 0.01797 -0.0128 0.2067 1.0000
6.250 0.8582 0.03213 0.01878 -0.0124 0.2019 1.0000
6.500 0.8808 0.03322 0.02003 -0.0118 0.1962 1.0000
6.750 0.9034 0.03418 0.02098 -0.0112 0.1913 1.0000
7.000 0.9272 0.03510 0.02174 -0.0108 0.1874 1.0000
7.250 0.9473 0.03647 0.02335 -0.0101 0.1829 1.0000
7.500 0.9679 0.03783 0.02485 -0.0095 0.1791 1.0000
7.750 0.9888 0.03909 0.02616 -0.0089 0.1759 1.0000
8.000 1.0108 0.04024 0.02726 -0.0084 0.1731 1.0000
8.250 1.0300 0.04176 0.02887 -0.0078 0.1702 1.0000
8.500 1.0429 0.04374 0.03118 -0.0067 0.1669 1.0000
8.750 1.0564 0.04561 0.03326 -0.0058 0.1639 1.0000
9.000 1.0706 0.04740 0.03518 -0.0049 0.1615 1.0000
9.250 1.0853 0.04919 0.03710 -0.0041 0.1595 1.0000
9.500 1.1011 0.05093 0.03888 -0.0033 0.1579 1.0000
9.750 1.1161 0.05283 0.04081 -0.0026 0.1563 1.0000
10.000 1.1054 0.05654 0.04497 -0.0007 0.1547 1.0000
10.250 1.0849 0.06085 0.04969 0.0012 0.1533 1.0000
10.500 1.0454 0.06646 0.05564 0.0028 0.1523 1.0000
10.750 0.8534 0.09912 0.08901 -0.0156 0.1508 1.0000
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Polar data table (+)
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