TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il) Reynolds number: 50,000 Max Cl/Cd: 25.75 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi-r-3a-il-50000-n5.txt Download as CSV file: xf-tsagi-r-3a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TsAGI R-3a (12%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4269 0.09668 0.09017 -0.0046 1.0045 0.0641
-8.250 -0.4222 0.09267 0.08622 -0.0063 1.0045 0.0623
-7.750 -0.4330 0.08021 0.07384 -0.0183 1.0045 0.0569
-7.500 -0.4277 0.07598 0.06963 -0.0206 1.0045 0.0561
-7.250 -0.4235 0.07136 0.06500 -0.0232 1.0045 0.0553
-7.000 -0.4191 0.06651 0.06009 -0.0258 1.0045 0.0544
-6.750 -0.4137 0.06161 0.05505 -0.0281 1.0045 0.0537
-6.500 -0.4061 0.05699 0.05025 -0.0298 1.0045 0.0536
-6.250 -0.3959 0.05286 0.04590 -0.0308 1.0045 0.0539
-6.000 -0.3837 0.04902 0.04180 -0.0313 1.0045 0.0546
-5.750 -0.3700 0.04540 0.03786 -0.0313 1.0045 0.0554
-5.500 -0.3551 0.04206 0.03414 -0.0310 1.0045 0.0560
-5.250 -0.3393 0.03906 0.03079 -0.0303 1.0045 0.0565
-5.000 -0.3082 0.03575 0.02694 -0.0321 0.9813 0.0572
-4.750 -0.2651 0.03316 0.02410 -0.0356 0.9332 0.0589
-4.500 -0.2236 0.03115 0.02175 -0.0382 0.8813 0.0626
-4.250 -0.1874 0.02933 0.01946 -0.0391 0.8313 0.0667
-4.000 -0.1578 0.02810 0.01793 -0.0386 0.7861 0.0707
-3.750 -0.1310 0.02699 0.01645 -0.0374 0.7492 0.0761
-3.500 -0.1052 0.02621 0.01539 -0.0363 0.7188 0.0839
-3.250 -0.0796 0.02553 0.01454 -0.0353 0.6947 0.0942
-3.000 -0.0533 0.02490 0.01372 -0.0344 0.6747 0.1081
-2.750 -0.0262 0.02423 0.01286 -0.0337 0.6567 0.1244
-2.500 -0.0005 0.02351 0.01212 -0.0330 0.6396 0.1455
-2.250 0.0245 0.02277 0.01141 -0.0322 0.6230 0.1803
-2.000 0.0485 0.02191 0.01083 -0.0315 0.6072 0.2466
-1.750 0.0663 0.02046 0.01055 -0.0297 0.5930 0.4673
-1.500 0.1067 0.01950 0.01071 -0.0279 0.5766 0.9008
-1.250 0.1732 0.01960 0.01026 -0.0344 0.5591 0.9955
-1.000 0.1969 0.01976 0.01006 -0.0337 0.5477 0.9955
-0.750 0.2211 0.01995 0.00998 -0.0331 0.5361 0.9955
-0.500 0.2451 0.02017 0.00986 -0.0323 0.5262 0.9955
-0.250 0.2694 0.02040 0.00988 -0.0317 0.5151 0.9955
0.000 0.2938 0.02067 0.00990 -0.0310 0.5054 0.9955
0.250 0.3184 0.02094 0.00996 -0.0304 0.4953 0.9955
0.500 0.3434 0.02125 0.01009 -0.0299 0.4853 0.9955
0.750 0.3683 0.02156 0.01018 -0.0293 0.4760 0.9955
1.000 0.3934 0.02192 0.01042 -0.0288 0.4660 0.9955
1.250 0.4185 0.02226 0.01053 -0.0281 0.4575 0.9955
1.500 0.4435 0.02267 0.01087 -0.0277 0.4471 0.9955
1.750 0.4687 0.02303 0.01100 -0.0270 0.4393 0.9955
2.000 0.4936 0.02352 0.01146 -0.0267 0.4290 0.9955
2.250 0.5189 0.02393 0.01167 -0.0261 0.4219 0.9955
2.500 0.5437 0.02453 0.01229 -0.0258 0.4125 0.9955
2.750 0.5690 0.02499 0.01261 -0.0252 0.4055 0.9955
3.000 0.5935 0.02563 0.01327 -0.0249 0.3969 0.9955
3.250 0.6184 0.02615 0.01370 -0.0244 0.3897 0.9955
3.500 0.6430 0.02678 0.01430 -0.0240 0.3828 0.9955
3.750 0.6671 0.02749 0.01506 -0.0237 0.3755 0.9955
4.000 0.6923 0.02802 0.01548 -0.0232 0.3706 0.9955
4.250 0.7153 0.02894 0.01651 -0.0229 0.3636 0.9955
4.500 0.7391 0.02963 0.01722 -0.0225 0.3575 0.9955
4.750 0.7644 0.03007 0.01756 -0.0220 0.3531 0.9955
5.000 0.7852 0.03126 0.01895 -0.0217 0.3460 0.9955
5.250 0.8085 0.03199 0.01969 -0.0212 0.3408 0.9955
5.500 0.8339 0.03238 0.02000 -0.0207 0.3368 0.9955
5.750 0.8519 0.03383 0.02170 -0.0203 0.3295 0.9955
6.000 0.8749 0.03445 0.02233 -0.0198 0.3242 0.9955
6.250 0.8984 0.03501 0.02286 -0.0192 0.3197 0.9955
6.500 0.9147 0.03651 0.02461 -0.0187 0.3127 0.9955
6.750 0.9380 0.03701 0.02509 -0.0181 0.3080 0.9955
7.000 0.9577 0.03800 0.02616 -0.0175 0.3030 0.9955
7.250 0.9724 0.03960 0.02795 -0.0169 0.2968 0.9955
7.500 0.9954 0.04008 0.02844 -0.0162 0.2926 0.9955
7.750 1.0130 0.04128 0.02972 -0.0156 0.2879 0.9955
8.000 1.0214 0.04348 0.03215 -0.0149 0.2817 0.9955
8.250 1.0433 0.04404 0.03274 -0.0142 0.2776 0.9955
8.500 1.0653 0.04465 0.03334 -0.0135 0.2739 0.9955
8.750 1.0522 0.04904 0.03811 -0.0128 0.2670 0.9955
9.000 1.0681 0.05016 0.03928 -0.0120 0.2627 0.9955
9.250 1.0991 0.04978 0.03885 -0.0112 0.2597 0.9955
9.500 0.9761 0.06642 0.05597 -0.0150 0.2492 0.9955
9.750 0.9905 0.06763 0.05720 -0.0144 0.2458 0.9955
10.000 1.0292 0.06548 0.05507 -0.0117 0.2440 0.9955
10.500 0.8742 0.09809 0.08778 -0.0291 0.2231 0.9955
10.750 0.8613 0.10412 0.09384 -0.0314 0.2182 0.9955
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