TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il) Reynolds number: 100,000 Max Cl/Cd: 32.99 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi-r-3a-il-100000.txt Download as CSV file: xf-tsagi-r-3a-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4152 0.10167 0.09721 0.0054 1.0045 0.1049
-8.250 -0.4302 0.09837 0.09401 -0.0023 1.0045 0.1091
-8.000 -0.4492 0.09321 0.08893 -0.0129 1.0045 0.1104
-7.750 -0.4148 0.09011 0.08587 -0.0033 1.0045 0.1128
-7.500 -0.4035 0.08704 0.08285 -0.0031 1.0045 0.1161
-7.250 -0.4037 0.08341 0.07930 -0.0068 1.0045 0.1204
-7.000 -0.4180 0.07710 0.07292 -0.0199 1.0045 0.1256
-6.750 -0.3982 0.07433 0.07029 -0.0156 1.0045 0.1281
-6.500 -0.3856 0.07146 0.06747 -0.0157 1.0045 0.1335
-6.250 -0.3865 0.06621 0.06210 -0.0232 1.0045 0.1421
-6.000 -0.3690 0.06378 0.05983 -0.0205 1.0045 0.1465
-5.750 -0.3642 0.05979 0.05566 -0.0252 1.0045 0.1586
-5.500 -0.3483 0.05710 0.05318 -0.0231 1.0045 0.1627
-5.250 -0.3438 0.05426 0.05025 -0.0250 1.0045 0.1759
-5.000 -0.2939 0.04969 0.04560 -0.0328 0.9581 0.1937
-4.750 -0.2520 0.04589 0.04161 -0.0370 0.8757 0.2121
-4.500 -0.2079 0.02927 0.02205 -0.0412 0.8491 0.0736
-4.250 -0.1848 0.02737 0.01957 -0.0393 0.7917 0.0732
-4.000 -0.1606 0.02593 0.01746 -0.0376 0.7523 0.0748
-3.750 -0.1364 0.02461 0.01599 -0.0366 0.7218 0.0778
-3.500 -0.1103 0.02343 0.01447 -0.0355 0.6970 0.0804
-3.250 -0.0831 0.02232 0.01294 -0.0345 0.6766 0.0839
-3.000 -0.0567 0.02128 0.01182 -0.0337 0.6584 0.0903
-2.750 -0.0300 0.02045 0.01092 -0.0329 0.6422 0.1018
-2.500 -0.0033 0.01968 0.01012 -0.0322 0.6289 0.1186
-2.250 0.0225 0.01911 0.00956 -0.0316 0.6176 0.1454
-2.000 0.0481 0.01826 0.00892 -0.0308 0.6058 0.1831
-1.750 0.0705 0.01680 0.00821 -0.0298 0.5961 0.3114
-1.500 0.0882 0.01493 0.00843 -0.0250 0.5864 0.8565
-1.250 0.1802 0.01519 0.00826 -0.0353 0.5697 0.9955
-1.000 0.2042 0.01536 0.00814 -0.0347 0.5601 0.9955
-0.750 0.2284 0.01551 0.00806 -0.0341 0.5495 0.9955
-0.500 0.2529 0.01572 0.00806 -0.0335 0.5390 0.9955
-0.250 0.2771 0.01595 0.00802 -0.0328 0.5290 0.9955
0.000 0.3019 0.01618 0.00812 -0.0322 0.5174 0.9955
0.250 0.3265 0.01647 0.00817 -0.0315 0.5077 0.9955
0.500 0.3513 0.01673 0.00832 -0.0309 0.4961 0.9955
0.750 0.3762 0.01707 0.00851 -0.0302 0.4850 0.9955
1.000 0.4011 0.01739 0.00860 -0.0295 0.4749 0.9955
1.250 0.4262 0.01774 0.00889 -0.0290 0.4626 0.9955
1.500 0.4514 0.01813 0.00912 -0.0284 0.4524 0.9955
1.750 0.4768 0.01849 0.00934 -0.0278 0.4422 0.9955
2.000 0.5022 0.01899 0.00978 -0.0273 0.4325 0.9955
2.250 0.5280 0.01942 0.01008 -0.0269 0.4243 0.9955
2.500 0.5535 0.02000 0.01063 -0.0265 0.4163 0.9955
2.750 0.5792 0.02048 0.01105 -0.0261 0.4085 0.9955
3.000 0.6050 0.02102 0.01146 -0.0257 0.4024 0.9955
3.250 0.6301 0.02161 0.01213 -0.0254 0.3944 0.9955
3.500 0.6562 0.02208 0.01250 -0.0250 0.3890 0.9955
3.750 0.6814 0.02279 0.01324 -0.0247 0.3835 0.9955
4.000 0.7063 0.02344 0.01396 -0.0244 0.3769 0.9955
4.250 0.7325 0.02385 0.01428 -0.0240 0.3719 0.9955
4.500 0.7571 0.02454 0.01502 -0.0236 0.3663 0.9955
4.750 0.7816 0.02514 0.01570 -0.0233 0.3597 0.9955
5.000 0.8080 0.02543 0.01588 -0.0229 0.3549 0.9955
5.250 0.8318 0.02620 0.01675 -0.0225 0.3495 0.9955
5.500 0.8555 0.02691 0.01756 -0.0221 0.3436 0.9955
5.750 0.8818 0.02720 0.01777 -0.0217 0.3391 0.9955
6.000 0.9056 0.02794 0.01857 -0.0213 0.3342 0.9955
6.250 0.9276 0.02885 0.01965 -0.0209 0.3281 0.9955
6.500 0.9539 0.02907 0.01981 -0.0204 0.3236 0.9955
6.750 0.9776 0.02977 0.02053 -0.0200 0.3189 0.9955
7.000 0.9976 0.03089 0.02188 -0.0195 0.3126 0.9955
7.250 1.0239 0.03109 0.02202 -0.0190 0.3082 0.9955
7.500 1.0467 0.03188 0.02285 -0.0185 0.3034 0.9955
7.750 1.0649 0.03309 0.02428 -0.0179 0.2969 0.9955
8.000 1.0925 0.03312 0.02422 -0.0175 0.2924 0.9955
8.250 1.1108 0.03447 0.02573 -0.0168 0.2872 0.9955
8.500 1.1269 0.03597 0.02744 -0.0160 0.2813 0.9955
8.750 1.1546 0.03608 0.02747 -0.0157 0.2771 0.9955
9.000 1.1690 0.03786 0.02943 -0.0148 0.2719 0.9955
9.250 1.1788 0.03993 0.03175 -0.0138 0.2658 0.9955
9.500 1.2070 0.04003 0.03177 -0.0135 0.2617 0.9955
9.750 1.2242 0.04163 0.03345 -0.0128 0.2577 0.9955
10.000 1.1962 0.04751 0.03993 -0.0109 0.2519 0.9955
10.250 1.2052 0.04954 0.04206 -0.0101 0.2480 0.9955
10.500 1.2489 0.04827 0.04064 -0.0099 0.2449 0.9955
10.750 0.7779 0.13115 0.12420 -0.0494 0.2907 0.9955
11.000 0.7348 0.13513 0.12816 -0.0531 0.2825 0.9955
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Polar data table (+)
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