REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: REPUBLIC S-3 AIRFOIL (s3-il) Reynolds number: 50,000 Max Cl/Cd: 23.58 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3-il-50000.txt Download as CSV file: xf-s3-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: REPUBLIC S-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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4489 0.09508 0.08875 0.0211 1.0000 0.4332
-7.750 -0.4299 0.09051 0.08416 0.0207 1.0000 0.4407
-6.500 -0.5767 0.05090 0.04352 -0.0203 1.0000 0.1522
-6.250 -0.5652 0.04707 0.03893 -0.0193 1.0000 0.1390
-6.000 -0.5470 0.04315 0.03487 -0.0183 1.0000 0.1349
-5.750 -0.5304 0.03985 0.03093 -0.0167 1.0000 0.1275
-5.500 -0.5108 0.03749 0.02797 -0.0149 1.0000 0.1236
-5.250 -0.4905 0.03499 0.02513 -0.0134 1.0000 0.1236
-5.000 -0.4701 0.03253 0.02243 -0.0119 1.0000 0.1267
-4.750 -0.4475 0.03030 0.02011 -0.0106 1.0000 0.1301
-4.500 -0.4239 0.02845 0.01806 -0.0092 1.0000 0.1336
-4.250 -0.4007 0.02676 0.01626 -0.0077 1.0000 0.1422
-4.000 -0.3768 0.02526 0.01477 -0.0062 1.0000 0.1520
-3.750 -0.3557 0.02384 0.01345 -0.0045 1.0000 0.1669
-3.500 -0.3386 0.02249 0.01227 -0.0024 1.0000 0.1862
-3.250 -0.3247 0.02109 0.01123 -0.0004 1.0000 0.2216
-3.000 -0.3229 0.01859 0.01064 0.0036 1.0000 0.4652
-2.750 -0.0447 0.02233 0.01391 -0.0146 1.0000 0.9775
-2.500 0.0162 0.02112 0.01240 -0.0228 1.0000 0.9972
-2.250 0.0324 0.02059 0.01182 -0.0232 1.0000 1.0000
-2.000 0.0354 0.02031 0.01155 -0.0214 1.0000 1.0000
-1.750 0.0287 0.02022 0.01150 -0.0183 1.0000 1.0000
-1.500 0.0115 0.02028 0.01158 -0.0137 1.0000 1.0000
-1.250 -0.0099 0.02032 0.01162 -0.0085 1.0000 1.0000
-1.000 -0.0308 0.02028 0.01157 -0.0034 1.0000 1.0000
-0.750 -0.0491 0.02020 0.01147 0.0015 1.0000 1.0000
-0.500 -0.0609 0.02021 0.01140 0.0055 1.0000 1.0000
-0.250 -0.0294 0.02069 0.01174 0.0022 0.9898 1.0000
0.000 0.0665 0.02153 0.01245 -0.0116 0.9597 1.0000
0.250 0.1693 0.02189 0.01274 -0.0255 0.9287 1.0000
0.500 0.2746 0.02156 0.01241 -0.0384 0.8942 1.0000
0.750 0.3339 0.02110 0.01192 -0.0422 0.8537 1.0000
1.000 0.3613 0.02091 0.01166 -0.0403 0.8123 1.0000
1.250 0.3805 0.02081 0.01143 -0.0369 0.7743 1.0000
1.500 0.3961 0.02086 0.01135 -0.0332 0.7365 1.0000
1.750 0.4123 0.02094 0.01126 -0.0296 0.7019 1.0000
2.000 0.4274 0.02120 0.01139 -0.0265 0.6654 1.0000
2.250 0.4445 0.02140 0.01144 -0.0237 0.6327 1.0000
2.500 0.4628 0.02163 0.01150 -0.0212 0.6026 1.0000
2.750 0.4821 0.02193 0.01165 -0.0191 0.5748 1.0000
3.000 0.5025 0.02231 0.01189 -0.0172 0.5502 1.0000
3.250 0.5234 0.02277 0.01219 -0.0156 0.5274 1.0000
3.500 0.5447 0.02337 0.01268 -0.0142 0.5066 1.0000
3.750 0.5663 0.02411 0.01335 -0.0130 0.4877 1.0000
4.000 0.5885 0.02496 0.01418 -0.0121 0.4720 1.0000
4.250 0.6109 0.02592 0.01514 -0.0112 0.4582 1.0000
4.500 0.6332 0.02695 0.01616 -0.0105 0.4457 1.0000
4.750 0.6562 0.02795 0.01714 -0.0097 0.4344 1.0000
5.000 0.6782 0.02913 0.01842 -0.0091 0.4236 1.0000
5.250 0.6982 0.03071 0.02020 -0.0087 0.4148 1.0000
5.500 0.7217 0.03196 0.02147 -0.0082 0.4075 1.0000
5.750 0.7381 0.03398 0.02379 -0.0078 0.3994 1.0000
6.000 0.7625 0.03513 0.02495 -0.0072 0.3918 1.0000
6.250 0.7738 0.03780 0.02803 -0.0070 0.3847 1.0000
6.500 0.7952 0.03937 0.02968 -0.0064 0.3779 1.0000
6.750 0.8024 0.04242 0.03306 -0.0062 0.3698 1.0000
7.000 0.8238 0.04360 0.03432 -0.0051 0.3594 1.0000
7.250 0.8487 0.04417 0.03487 -0.0038 0.3466 1.0000
7.500 0.8526 0.04701 0.03803 -0.0031 0.3351 1.0000
7.750 0.8546 0.05026 0.04151 -0.0025 0.3252 1.0000
8.000 0.8709 0.05191 0.04326 -0.0014 0.3142 1.0000
8.250 0.8997 0.05236 0.04376 0.0000 0.3026 1.0000
8.500 0.8507 0.06138 0.05308 -0.0014 0.2989 1.0000
8.750 0.7861 0.07244 0.06408 -0.0055 0.2996 1.0000
9.000 0.8124 0.07283 0.06459 -0.0031 0.2870 1.0000
9.250 0.7584 0.08428 0.07588 -0.0096 0.2891 1.0000
9.500 0.7379 0.09137 0.08291 -0.0127 0.2877 1.0000
9.750 0.7270 0.09772 0.08923 -0.0153 0.2881 1.0000
|
Polar data table (+)
Polar graphs
<< Back to REPUBLIC S-3 AIRFOIL (s3-il)