NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Reynolds number: 200,000 Max Cl/Cd: 49.29 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rcsc2-il-200000.txt Download as CSV file: xf-rcsc2-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-SC2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5649 0.10340 0.09933 -0.0226 1.0000 0.0708
-10.000 -0.6255 0.08999 0.08594 -0.0417 1.0000 0.0734
-9.500 -0.6930 0.08277 0.07855 -0.0400 1.0000 0.0736
-9.250 -0.6669 0.07626 0.07222 -0.0408 1.0000 0.0749
-9.000 -0.6603 0.07393 0.06994 -0.0389 1.0000 0.0756
-8.750 -0.6646 0.07138 0.06740 -0.0369 1.0000 0.0764
-8.500 -0.6714 0.06874 0.06474 -0.0346 1.0000 0.0772
-8.250 -0.6795 0.06600 0.06195 -0.0322 1.0000 0.0783
-8.000 -0.6879 0.06313 0.05901 -0.0296 1.0000 0.0797
-7.750 -0.6973 0.06005 0.05579 -0.0268 1.0000 0.0820
-7.500 -0.7317 0.05592 0.05100 -0.0214 1.0000 0.0870
-7.250 -0.7203 0.05268 0.04787 -0.0200 1.0000 0.0880
-7.000 -0.7458 0.03876 0.03229 -0.0118 1.0000 0.0526
-6.750 -0.7352 0.03500 0.02843 -0.0099 1.0000 0.0510
-6.500 -0.7231 0.03208 0.02520 -0.0075 1.0000 0.0498
-6.250 -0.7085 0.02975 0.02254 -0.0053 1.0000 0.0496
-6.000 -0.6914 0.02772 0.02020 -0.0034 1.0000 0.0495
-5.750 -0.6724 0.02580 0.01798 -0.0017 1.0000 0.0493
-5.500 -0.6517 0.02413 0.01606 -0.0003 1.0000 0.0492
-5.250 -0.6298 0.02277 0.01449 0.0010 1.0000 0.0495
-5.000 -0.6073 0.02162 0.01318 0.0021 1.0000 0.0501
-4.750 -0.5841 0.02064 0.01207 0.0031 1.0000 0.0510
-4.500 -0.5606 0.01983 0.01115 0.0041 1.0000 0.0521
-4.250 -0.5372 0.01884 0.01012 0.0050 1.0000 0.0538
-4.000 -0.5146 0.01810 0.00946 0.0058 1.0000 0.0565
-3.750 -0.4918 0.01756 0.00892 0.0068 1.0000 0.0595
-3.500 -0.4688 0.01707 0.00838 0.0078 1.0000 0.0623
-3.250 -0.4466 0.01623 0.00765 0.0087 1.0000 0.0670
-3.000 -0.4237 0.01583 0.00724 0.0096 1.0000 0.0739
-2.750 -0.4010 0.01517 0.00670 0.0104 1.0000 0.0877
-2.500 -0.3779 0.01445 0.00625 0.0110 1.0000 0.1235
-2.250 -0.3546 0.01360 0.00595 0.0113 1.0000 0.2209
-2.000 -0.3321 0.01223 0.00578 0.0115 1.0000 0.4678
-1.750 -0.3121 0.01130 0.00602 0.0135 1.0000 0.7219
-1.500 -0.2939 0.01128 0.00643 0.0166 1.0000 0.8431
-1.250 -0.2711 0.01161 0.00687 0.0188 1.0000 0.9166
-1.000 -0.2253 0.01213 0.00736 0.0160 1.0000 0.9635
-0.750 -0.1671 0.01260 0.00772 0.0099 1.0000 0.9844
-0.500 -0.0794 0.01312 0.00813 -0.0020 1.0000 0.9991
-0.250 -0.0707 0.01307 0.00805 0.0007 1.0000 1.0000
0.000 -0.0400 0.01315 0.00809 -0.0006 0.9967 1.0000
0.250 0.0275 0.01331 0.00822 -0.0088 0.9879 1.0000
0.500 0.0921 0.01332 0.00822 -0.0163 0.9788 1.0000
0.750 0.1547 0.01327 0.00817 -0.0233 0.9726 1.0000
1.000 0.2048 0.01308 0.00802 -0.0277 0.9629 1.0000
1.250 0.2700 0.01269 0.00768 -0.0348 0.9524 1.0000
1.500 0.3422 0.01197 0.00704 -0.0428 0.9385 1.0000
1.750 0.3820 0.01146 0.00659 -0.0446 0.9216 1.0000
2.000 0.4152 0.01094 0.00613 -0.0448 0.9017 1.0000
2.250 0.4419 0.01050 0.00571 -0.0437 0.8710 1.0000
2.500 0.4697 0.01009 0.00526 -0.0427 0.8185 1.0000
2.750 0.4963 0.01007 0.00466 -0.0408 0.6760 1.0000
3.000 0.5073 0.01124 0.00469 -0.0372 0.4565 1.0000
3.250 0.5202 0.01234 0.00497 -0.0347 0.3054 1.0000
3.500 0.5374 0.01306 0.00525 -0.0330 0.2233 1.0000
3.750 0.5555 0.01368 0.00555 -0.0314 0.1687 1.0000
4.000 0.5740 0.01422 0.00588 -0.0297 0.1333 1.0000
4.250 0.5923 0.01478 0.00628 -0.0280 0.1083 1.0000
4.500 0.6099 0.01542 0.00677 -0.0261 0.0874 1.0000
4.750 0.6265 0.01622 0.00744 -0.0240 0.0735 1.0000
5.000 0.6451 0.01679 0.00800 -0.0221 0.0658 1.0000
5.250 0.6623 0.01766 0.00884 -0.0200 0.0611 1.0000
5.500 0.6815 0.01829 0.00948 -0.0183 0.0574 1.0000
5.750 0.7003 0.01906 0.01017 -0.0166 0.0544 1.0000
6.000 0.7202 0.02002 0.01115 -0.0151 0.0521 1.0000
6.250 0.7410 0.02078 0.01198 -0.0136 0.0502 1.0000
6.500 0.7620 0.02168 0.01292 -0.0122 0.0488 1.0000
6.750 0.7832 0.02264 0.01393 -0.0109 0.0476 1.0000
7.000 0.8044 0.02371 0.01505 -0.0097 0.0467 1.0000
7.250 0.8258 0.02505 0.01643 -0.0085 0.0460 1.0000
7.500 0.8469 0.02683 0.01831 -0.0074 0.0455 1.0000
7.750 0.8663 0.02894 0.02061 -0.0060 0.0452 1.0000
8.000 0.8838 0.03103 0.02293 -0.0043 0.0451 1.0000
8.250 0.9000 0.03293 0.02507 -0.0023 0.0452 1.0000
8.500 0.9151 0.03463 0.02704 -0.0001 0.0455 1.0000
8.750 0.9262 0.03676 0.02962 0.0028 0.0463 1.0000
9.000 0.9094 0.04370 0.03764 0.0092 0.0500 1.0000
9.250 0.9099 0.04757 0.04181 0.0121 0.0512 1.0000
9.500 0.9119 0.05146 0.04586 0.0144 0.0523 1.0000
9.750 0.7802 0.07414 0.06998 0.0223 0.0834 1.0000
10.000 0.7353 0.08140 0.07740 0.0194 0.0821 1.0000
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Polar data table (+)
Polar graphs
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