GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 598 AIRFOIL (goe598-il) Reynolds number: 100,000 Max Cl/Cd: 43.07 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe598-il-100000.txt Download as CSV file: xf-goe598-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 598 AIRFOIL
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 -0.6071 0.09943 0.09471 0.0047 1.0000 0.0957
-8.250 -0.6189 0.09551 0.09089 -0.0037 1.0000 0.0984
-8.000 -0.6307 0.09039 0.08567 -0.0179 1.0000 0.0992
-7.750 -0.6066 0.08653 0.08192 -0.0039 1.0000 0.1041
-7.500 -0.6025 0.08199 0.07738 -0.0086 1.0000 0.1093
-7.250 -0.6051 0.07551 0.07084 -0.0196 1.0000 0.1141
-7.000 -0.5910 0.07212 0.06747 -0.0161 1.0000 0.1181
-6.750 -0.5871 0.06656 0.06165 -0.0243 1.0000 0.1276
-6.500 -0.5721 0.06278 0.05797 -0.0221 1.0000 0.1314
-6.250 -0.5610 0.05812 0.05310 -0.0256 1.0000 0.1424
-6.000 -0.5469 0.05426 0.04905 -0.0272 1.0000 0.1553
-5.750 -0.5315 0.05083 0.04560 -0.0268 1.0000 0.1701
-5.500 -0.5168 0.04807 0.04278 -0.0265 1.0000 0.1969
-5.250 -0.4717 0.03385 0.02624 -0.0310 1.0000 0.0711
-5.000 -0.4491 0.02966 0.02171 -0.0305 1.0000 0.0677
-4.750 -0.4241 0.02630 0.01779 -0.0296 1.0000 0.0655
-4.500 -0.3983 0.02375 0.01477 -0.0287 1.0000 0.0664
-4.250 -0.3722 0.02224 0.01278 -0.0277 1.0000 0.0728
-4.000 -0.3472 0.02013 0.01059 -0.0270 1.0000 0.0774
-3.750 -0.3214 0.01878 0.00904 -0.0261 1.0000 0.0844
-3.500 -0.2971 0.01744 0.00774 -0.0253 1.0000 0.0973
-3.250 -0.2734 0.01603 0.00644 -0.0243 1.0000 0.1110
-3.000 -0.2506 0.01455 0.00527 -0.0234 1.0000 0.1534
-2.750 -0.2331 0.01185 0.00457 -0.0221 1.0000 0.5261
-2.500 -0.2180 0.01096 0.00447 -0.0179 1.0000 0.7576
-2.250 -0.1795 0.01068 0.00435 -0.0179 1.0000 0.9355
-2.000 -0.1227 0.01058 0.00392 -0.0239 1.0000 1.0000
-1.750 -0.1043 0.01052 0.00367 -0.0226 1.0000 1.0000
-1.500 -0.0845 0.01050 0.00345 -0.0214 1.0000 1.0000
-1.250 -0.0638 0.01051 0.00332 -0.0204 1.0000 1.0000
-1.000 -0.0427 0.01056 0.00324 -0.0195 1.0000 1.0000
-0.750 -0.0212 0.01063 0.00321 -0.0187 1.0000 1.0000
-0.500 0.0003 0.01074 0.00323 -0.0180 1.0000 1.0000
-0.250 0.0219 0.01089 0.00329 -0.0174 1.0000 1.0000
0.000 0.0434 0.01107 0.00342 -0.0168 1.0000 1.0000
0.250 0.0649 0.01131 0.00361 -0.0164 1.0000 1.0000
0.500 0.0864 0.01158 0.00386 -0.0160 1.0000 1.0000
0.750 0.1079 0.01190 0.00417 -0.0158 1.0000 1.0000
1.000 0.1294 0.01226 0.00454 -0.0157 1.0000 1.0000
1.250 0.1509 0.01267 0.00495 -0.0157 1.0000 1.0000
1.500 0.1916 0.01307 0.00541 -0.0194 0.9931 1.0000
1.750 0.2485 0.01334 0.00581 -0.0258 0.9776 1.0000
2.000 0.2995 0.01355 0.00621 -0.0308 0.9638 1.0000
2.250 0.3552 0.01356 0.00644 -0.0363 0.9465 1.0000
2.500 0.4124 0.01332 0.00651 -0.0413 0.9276 1.0000
2.750 0.4514 0.01314 0.00657 -0.0425 0.9039 1.0000
3.000 0.4858 0.01274 0.00638 -0.0416 0.8729 1.0000
3.250 0.5083 0.01241 0.00617 -0.0380 0.8281 1.0000
3.500 0.5211 0.01210 0.00562 -0.0314 0.7268 1.0000
3.750 0.5335 0.01262 0.00544 -0.0259 0.5031 1.0000
4.000 0.5385 0.01676 0.00687 -0.0224 0.0871 1.0000
4.250 0.5609 0.01815 0.00821 -0.0211 0.0704 1.0000
4.500 0.5832 0.01988 0.00989 -0.0197 0.0643 1.0000
4.750 0.6079 0.02140 0.01143 -0.0188 0.0573 1.0000
5.000 0.6331 0.02404 0.01401 -0.0180 0.0533 1.0000
5.250 0.6604 0.02629 0.01654 -0.0171 0.0528 1.0000
5.500 0.6866 0.02935 0.01995 -0.0162 0.0533 1.0000
5.750 0.7140 0.03131 0.02241 -0.0149 0.0559 1.0000
6.000 0.7381 0.03547 0.02743 -0.0130 0.0628 1.0000
6.250 0.7588 0.03969 0.03198 -0.0121 0.0652 1.0000
7.500 0.8373 0.07168 0.06661 -0.0106 0.1460 1.0000
7.750 0.8246 0.07485 0.07023 -0.0134 0.1348 1.0000
8.000 0.8167 0.08025 0.07574 -0.0160 0.1288 1.0000
9.000 0.7375 0.09042 0.08611 -0.0062 0.1185 1.0000
9.250 0.7090 0.09559 0.09130 -0.0100 0.1184 1.0000
9.500 0.6796 0.10185 0.09751 -0.0166 0.1181 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 598 AIRFOIL (goe598-il)