TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il) Reynolds number: 100,000 Max Cl/Cd: 43.91 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi-r-3a-il-100000-n5.txt Download as CSV file: xf-tsagi-r-3a-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4546 0.08548 0.08084 -0.0081 1.0045 0.0337
-8.250 -0.4506 0.08183 0.07725 -0.0101 1.0045 0.0334
-8.000 -0.4503 0.07732 0.07279 -0.0138 1.0045 0.0330
-7.750 -0.4496 0.07178 0.06725 -0.0188 1.0045 0.0325
-7.500 -0.4488 0.06562 0.06104 -0.0236 1.0045 0.0319
-7.250 -0.4470 0.05929 0.05457 -0.0274 1.0045 0.0316
-7.000 -0.4428 0.05328 0.04834 -0.0300 1.0045 0.0317
-6.750 -0.4358 0.04776 0.04250 -0.0315 1.0045 0.0320
-6.500 -0.4262 0.04279 0.03716 -0.0320 1.0045 0.0323
-6.250 -0.4137 0.03852 0.03244 -0.0318 1.0045 0.0325
-6.000 -0.3909 0.03447 0.02788 -0.0329 0.9817 0.0326
-5.750 -0.3580 0.03080 0.02357 -0.0350 0.9318 0.0329
-5.500 -0.3245 0.02799 0.02012 -0.0363 0.8736 0.0334
-5.250 -0.2970 0.02619 0.01782 -0.0358 0.8094 0.0340
-5.000 -0.2736 0.02510 0.01638 -0.0344 0.7503 0.0348
-4.750 -0.2499 0.02414 0.01506 -0.0332 0.7019 0.0360
-4.500 -0.2250 0.02319 0.01367 -0.0322 0.6645 0.0381
-4.250 -0.1997 0.02239 0.01265 -0.0315 0.6363 0.0400
-4.000 -0.1736 0.02160 0.01167 -0.0308 0.6140 0.0422
-3.750 -0.1474 0.02077 0.01061 -0.0301 0.5955 0.0444
-3.500 -0.1217 0.02011 0.00987 -0.0295 0.5780 0.0472
-3.250 -0.0957 0.01952 0.00914 -0.0289 0.5615 0.0519
-3.000 -0.0696 0.01902 0.00853 -0.0284 0.5466 0.0587
-2.750 -0.0432 0.01854 0.00801 -0.0279 0.5331 0.0673
-2.500 -0.0167 0.01821 0.00764 -0.0275 0.5213 0.0819
-2.250 0.0096 0.01788 0.00733 -0.0271 0.5109 0.1033
-2.000 0.0363 0.01743 0.00696 -0.0267 0.5017 0.1317
-1.750 0.0627 0.01705 0.00663 -0.0262 0.4937 0.1737
-1.500 0.0888 0.01655 0.00640 -0.0259 0.4857 0.2455
-1.250 0.1132 0.01575 0.00626 -0.0254 0.4782 0.4189
-1.000 0.1312 0.01478 0.00636 -0.0225 0.4720 0.7151
-0.750 0.1761 0.01456 0.00647 -0.0237 0.4628 0.9235
-0.500 0.2247 0.01469 0.00632 -0.0273 0.4540 0.9757
-0.250 0.2657 0.01478 0.00620 -0.0298 0.4448 0.9955
0.000 0.2905 0.01493 0.00611 -0.0292 0.4381 0.9955
0.250 0.3156 0.01505 0.00611 -0.0287 0.4300 0.9955
0.500 0.3407 0.01523 0.00609 -0.0280 0.4231 0.9955
0.750 0.3661 0.01539 0.00614 -0.0275 0.4156 0.9955
1.000 0.3915 0.01557 0.00618 -0.0270 0.4081 0.9955
1.250 0.4170 0.01578 0.00624 -0.0264 0.4010 0.9955
1.500 0.4428 0.01596 0.00635 -0.0260 0.3925 0.9955
1.750 0.4684 0.01618 0.00641 -0.0255 0.3854 0.9955
2.000 0.4944 0.01636 0.00657 -0.0250 0.3762 0.9955
2.250 0.5202 0.01657 0.00663 -0.0246 0.3692 0.9955
2.500 0.5464 0.01678 0.00684 -0.0242 0.3602 0.9955
2.750 0.5723 0.01700 0.00695 -0.0238 0.3537 0.9955
3.000 0.5985 0.01726 0.00720 -0.0234 0.3460 0.9955
3.250 0.6246 0.01750 0.00736 -0.0230 0.3396 0.9955
3.500 0.6506 0.01777 0.00758 -0.0227 0.3334 0.9955
3.750 0.6767 0.01805 0.00784 -0.0223 0.3266 0.9955
4.000 0.7026 0.01830 0.00799 -0.0219 0.3214 0.9955
4.250 0.7286 0.01864 0.00835 -0.0216 0.3153 0.9955
4.500 0.7544 0.01896 0.00865 -0.0213 0.3102 0.9955
4.750 0.7801 0.01925 0.00885 -0.0209 0.3059 0.9955
5.000 0.8058 0.01962 0.00926 -0.0205 0.2999 0.9955
5.250 0.8312 0.01993 0.00955 -0.0202 0.2943 0.9955
5.500 0.8565 0.02024 0.00976 -0.0198 0.2898 0.9955
5.750 0.8816 0.02067 0.01026 -0.0194 0.2841 0.9955
6.000 0.9066 0.02105 0.01063 -0.0190 0.2793 0.9955
6.250 0.9316 0.02145 0.01095 -0.0186 0.2755 0.9955
6.500 0.9561 0.02196 0.01154 -0.0183 0.2708 0.9955
6.750 0.9805 0.02245 0.01207 -0.0179 0.2662 0.9955
7.000 1.0049 0.02291 0.01253 -0.0174 0.2621 0.9955
7.250 1.0293 0.02344 0.01300 -0.0170 0.2584 0.9955
7.500 1.0525 0.02405 0.01378 -0.0166 0.2538 0.9955
7.750 1.0759 0.02462 0.01443 -0.0161 0.2495 0.9955
8.000 1.0996 0.02515 0.01495 -0.0157 0.2456 0.9955
8.250 1.1228 0.02578 0.01560 -0.0152 0.2418 0.9955
8.500 1.1443 0.02648 0.01650 -0.0146 0.2371 0.9955
8.750 1.1664 0.02711 0.01721 -0.0141 0.2328 0.9955
9.000 1.1893 0.02769 0.01779 -0.0136 0.2293 0.9955
9.250 1.2105 0.02846 0.01866 -0.0130 0.2257 0.9955
9.500 1.2296 0.02930 0.01972 -0.0123 0.2212 0.9955
9.750 1.2500 0.03001 0.02051 -0.0116 0.2171 0.9955
10.000 1.2717 0.03061 0.02110 -0.0110 0.2136 0.9955
10.250 1.2891 0.03157 0.02224 -0.0102 0.2097 0.9955
10.500 1.3048 0.03260 0.02349 -0.0092 0.2055 0.9955
10.750 1.3225 0.03347 0.02447 -0.0084 0.2020 0.9955
11.000 1.3419 0.03419 0.02521 -0.0076 0.1990 0.9955
11.250 1.3560 0.03533 0.02650 -0.0066 0.1959 0.9955
11.500 1.3640 0.03680 0.02824 -0.0052 0.1920 0.9955
11.750 1.3748 0.03798 0.02959 -0.0040 0.1886 0.9955
12.000 1.3883 0.03891 0.03058 -0.0029 0.1859 0.9955
12.250 1.4050 0.03969 0.03134 -0.0020 0.1836 0.9955
12.500 1.3944 0.04210 0.03408 0.0003 0.1809 0.9955
12.750 1.3845 0.04479 0.03701 0.0017 0.1783 0.9955
13.000 1.3763 0.04767 0.04008 0.0021 0.1759 0.9955
13.250 1.3734 0.05028 0.04282 0.0020 0.1736 0.9955
13.500 1.3809 0.05195 0.04453 0.0021 0.1715 0.9955
13.750 1.3737 0.05540 0.04811 0.0013 0.1695 0.9955
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Polar data table (+)
Polar graphs
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