NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Reynolds number: 50,000 Max Cl/Cd: 33.44 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc10b3-il-50000-n5.txt Download as CSV file: xf-rc10b3-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-10(B)3 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5125 0.11254 0.10530 -0.0142 1.0000 0.1188
-9.500 -0.5111 0.10353 0.09620 -0.0199 1.0000 0.0675
-9.250 -0.5327 0.09520 0.08794 -0.0303 1.0000 0.0594
-9.000 -0.5256 0.09172 0.08447 -0.0296 1.0000 0.0582
-8.750 -0.5269 0.08762 0.08040 -0.0309 1.0000 0.0570
-8.500 -0.5326 0.08353 0.07633 -0.0319 1.0000 0.0560
-8.250 -0.5393 0.07948 0.07227 -0.0324 1.0000 0.0551
-8.000 -0.5451 0.07536 0.06811 -0.0327 1.0000 0.0544
-7.750 -0.5502 0.07139 0.06406 -0.0325 1.0000 0.0539
-7.500 -0.5542 0.06760 0.06016 -0.0315 1.0000 0.0536
-7.250 -0.5568 0.06406 0.05649 -0.0300 1.0000 0.0535
-7.000 -0.5586 0.06076 0.05302 -0.0279 1.0000 0.0535
-6.750 -0.5595 0.05765 0.04972 -0.0253 1.0000 0.0536
-6.500 -0.5592 0.05465 0.04650 -0.0225 1.0000 0.0536
-6.250 -0.5575 0.05173 0.04332 -0.0195 1.0000 0.0535
-6.000 -0.5543 0.04886 0.04014 -0.0164 1.0000 0.0532
-5.750 -0.5489 0.04612 0.03707 -0.0134 1.0000 0.0529
-5.500 -0.5412 0.04353 0.03413 -0.0105 1.0000 0.0528
-5.250 -0.5312 0.04109 0.03133 -0.0077 1.0000 0.0529
-5.000 -0.5189 0.03881 0.02866 -0.0053 1.0000 0.0533
-4.750 -0.5044 0.03669 0.02617 -0.0030 1.0000 0.0538
-4.500 -0.4879 0.03483 0.02395 -0.0010 1.0000 0.0553
-4.250 -0.4695 0.03316 0.02186 0.0007 1.0000 0.0578
-4.000 -0.4492 0.03158 0.01990 0.0023 1.0000 0.0602
-3.750 -0.4284 0.03012 0.01834 0.0033 1.0000 0.0625
-3.500 -0.4056 0.02886 0.01692 0.0043 1.0000 0.0651
-3.250 -0.3813 0.02774 0.01561 0.0051 1.0000 0.0692
-3.000 -0.3562 0.02677 0.01455 0.0056 1.0000 0.0758
-2.750 -0.3295 0.02596 0.01359 0.0059 1.0000 0.0842
-2.500 -0.3047 0.02519 0.01278 0.0063 1.0000 0.0968
-2.000 -0.0835 0.02077 0.01148 -0.0227 1.0000 1.0000
-1.750 -0.0750 0.02089 0.01136 -0.0198 1.0000 1.0000
-1.500 -0.0662 0.02103 0.01128 -0.0169 1.0000 1.0000
-1.250 -0.0569 0.02120 0.01126 -0.0142 1.0000 1.0000
-1.000 -0.0217 0.02135 0.01116 -0.0165 0.9925 1.0000
-0.750 0.0166 0.02154 0.01111 -0.0194 0.9843 1.0000
-0.500 0.0540 0.02171 0.01110 -0.0220 0.9752 1.0000
-0.250 0.0908 0.02188 0.01113 -0.0245 0.9658 1.0000
0.000 0.1304 0.02207 0.01119 -0.0274 0.9572 1.0000
0.250 0.1683 0.02225 0.01127 -0.0300 0.9474 1.0000
0.500 0.2050 0.02242 0.01138 -0.0323 0.9369 1.0000
0.750 0.2460 0.02256 0.01148 -0.0353 0.9273 1.0000
1.000 0.2862 0.02267 0.01157 -0.0380 0.9167 1.0000
1.250 0.3195 0.02278 0.01169 -0.0393 0.9038 1.0000
1.500 0.3524 0.02286 0.01180 -0.0403 0.8904 1.0000
1.750 0.3847 0.02292 0.01190 -0.0411 0.8768 1.0000
2.000 0.4160 0.02295 0.01198 -0.0416 0.8627 1.0000
2.250 0.4457 0.02295 0.01205 -0.0417 0.8480 1.0000
2.500 0.4741 0.02294 0.01211 -0.0413 0.8323 1.0000
2.750 0.5014 0.02289 0.01216 -0.0407 0.8157 1.0000
3.000 0.5279 0.02281 0.01216 -0.0398 0.7983 1.0000
3.250 0.5542 0.02268 0.01213 -0.0387 0.7803 1.0000
3.500 0.5806 0.02251 0.01207 -0.0375 0.7619 1.0000
3.750 0.6012 0.02250 0.01216 -0.0355 0.7392 1.0000
4.000 0.6261 0.02228 0.01203 -0.0338 0.7167 1.0000
4.250 0.6471 0.02220 0.01204 -0.0317 0.6895 1.0000
4.500 0.6689 0.02210 0.01204 -0.0296 0.6600 1.0000
4.750 0.6909 0.02202 0.01200 -0.0275 0.6273 1.0000
5.000 0.7116 0.02203 0.01200 -0.0252 0.5886 1.0000
5.250 0.7313 0.02212 0.01203 -0.0227 0.5435 1.0000
5.500 0.7493 0.02241 0.01214 -0.0202 0.4923 1.0000
5.750 0.7652 0.02293 0.01241 -0.0175 0.4384 1.0000
6.000 0.7789 0.02367 0.01287 -0.0149 0.3837 1.0000
6.250 0.7912 0.02455 0.01350 -0.0122 0.3311 1.0000
6.500 0.8028 0.02555 0.01429 -0.0097 0.2817 1.0000
6.750 0.8138 0.02666 0.01517 -0.0072 0.2370 1.0000
7.000 0.8244 0.02789 0.01614 -0.0047 0.1999 1.0000
7.250 0.8359 0.02916 0.01724 -0.0025 0.1700 1.0000
7.500 0.8485 0.03044 0.01844 -0.0003 0.1471 1.0000
7.750 0.8619 0.03175 0.01971 0.0017 0.1309 1.0000
8.000 0.8777 0.03307 0.02105 0.0035 0.1188 1.0000
8.250 0.8937 0.03438 0.02240 0.0051 0.1088 1.0000
8.500 0.9095 0.03574 0.02370 0.0067 0.1011 1.0000
8.750 0.9307 0.03727 0.02549 0.0078 0.0948 1.0000
9.000 0.9484 0.03876 0.02700 0.0091 0.0892 1.0000
9.250 0.9665 0.04049 0.02892 0.0104 0.0841 1.0000
9.500 0.9843 0.04236 0.03105 0.0117 0.0801 1.0000
9.750 1.0009 0.04428 0.03310 0.0129 0.0770 1.0000
10.000 1.0164 0.04644 0.03536 0.0141 0.0740 1.0000
10.250 1.0231 0.04883 0.03822 0.0165 0.0712 1.0000
10.500 1.0288 0.05129 0.04101 0.0187 0.0687 1.0000
10.750 1.0326 0.05396 0.04398 0.0209 0.0672 1.0000
11.000 1.0337 0.05671 0.04699 0.0232 0.0659 1.0000
11.250 1.0329 0.05938 0.04985 0.0254 0.0647 1.0000
11.500 1.0323 0.06196 0.05254 0.0276 0.0634 1.0000
11.750 1.0229 0.06501 0.05575 0.0301 0.0625 1.0000
12.000 1.0021 0.06859 0.05961 0.0325 0.0622 1.0000
12.250 0.9795 0.07277 0.06405 0.0336 0.0620 1.0000
12.500 0.9552 0.07767 0.06918 0.0335 0.0619 1.0000
12.750 0.9294 0.08345 0.07514 0.0320 0.0621 1.0000
13.000 0.9026 0.09024 0.08207 0.0290 0.0623 1.0000
13.250 0.8759 0.09812 0.09005 0.0248 0.0626 1.0000
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Polar data table (+)
Polar graphs
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