NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il) Reynolds number: 50,000 Max Cl/Cd: 14.49 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20402-il-50000-n5.txt Download as CSV file: xf-sc20402-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0402 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6954 0.11455 0.10811 0.0293 1.0000 0.0777
-8.500 -0.6977 0.11211 0.10578 0.0243 1.0000 0.0801
-8.250 -0.6962 0.10921 0.10296 0.0159 1.0000 0.0809
-8.000 -0.6854 0.10297 0.09671 0.0233 1.0000 0.0855
-7.750 -0.6792 0.09905 0.09282 0.0198 1.0000 0.0902
-7.500 -0.6711 0.09572 0.08947 0.0049 1.0000 0.0940
-7.000 -0.6494 0.08642 0.08014 -0.0008 1.0000 0.1072
-6.000 -0.5445 0.05358 0.04700 -0.0064 1.0000 0.1618
-5.500 -0.5252 0.05572 0.04769 -0.0182 1.0000 0.0637
-5.250 -0.4929 0.05066 0.04217 -0.0206 1.0000 0.0385
-5.000 -0.4652 0.04607 0.03720 -0.0229 1.0000 0.0327
-4.750 -0.4329 0.04257 0.03308 -0.0244 1.0000 0.0274
-4.500 -0.4058 0.03857 0.02872 -0.0259 1.0000 0.0253
-4.250 -0.3760 0.03508 0.02473 -0.0270 1.0000 0.0233
-4.000 -0.3455 0.03194 0.02105 -0.0277 1.0000 0.0216
-3.750 -0.3149 0.02916 0.01772 -0.0279 1.0000 0.0201
-3.500 -0.2849 0.02677 0.01480 -0.0277 1.0000 0.0189
-3.250 -0.2564 0.02469 0.01232 -0.0272 1.0000 0.0187
-3.000 -0.2296 0.02292 0.01030 -0.0267 1.0000 0.0217
-2.750 -0.2036 0.02161 0.00870 -0.0257 1.0000 0.0262
-2.500 -0.1775 0.02032 0.00717 -0.0249 1.0000 0.0301
-2.250 -0.1506 0.01912 0.00581 -0.0246 1.0000 0.0340
-2.000 -0.1230 0.01825 0.00474 -0.0245 1.0000 0.0367
-1.250 -0.0561 0.01283 0.00168 -0.0186 1.0000 1.0000
-1.000 -0.0289 0.01280 0.00138 -0.0185 1.0000 1.0000
-0.750 -0.0018 0.01279 0.00118 -0.0185 1.0000 1.0000
-0.500 0.0253 0.01279 0.00108 -0.0184 1.0000 1.0000
-0.250 0.0522 0.01281 0.00108 -0.0184 1.0000 1.0000
0.000 0.0790 0.01283 0.00118 -0.0183 1.0000 1.0000
0.250 0.1058 0.01287 0.00137 -0.0181 1.0000 1.0000
0.500 0.1326 0.01292 0.00167 -0.0180 1.0000 1.0000
1.000 0.2083 0.01788 0.00429 -0.0205 0.0385 1.0000
1.250 0.2362 0.01871 0.00533 -0.0202 0.0350 1.0000
1.500 0.2638 0.01972 0.00652 -0.0199 0.0318 1.0000
1.750 0.2915 0.02119 0.00818 -0.0196 0.0277 1.0000
2.000 0.3203 0.02240 0.00972 -0.0191 0.0230 1.0000
2.250 0.3486 0.02406 0.01163 -0.0187 0.0191 1.0000
2.500 0.3771 0.02611 0.01403 -0.0182 0.0184 1.0000
2.750 0.4066 0.02834 0.01675 -0.0176 0.0195 1.0000
3.000 0.4360 0.03091 0.01985 -0.0171 0.0209 1.0000
3.250 0.4648 0.03379 0.02326 -0.0167 0.0225 1.0000
3.500 0.4928 0.03695 0.02693 -0.0166 0.0243 1.0000
3.750 0.5191 0.04048 0.03089 -0.0168 0.0263 1.0000
4.250 0.5747 0.04780 0.03925 -0.0175 0.0355 1.0000
4.500 0.6019 0.05210 0.04397 -0.0182 0.0474 1.0000
5.000 0.6799 0.06388 0.05699 -0.0262 0.1651 1.0000
5.500 0.7106 0.07282 0.06682 -0.0278 0.1346 1.0000
5.750 0.7244 0.07733 0.07143 -0.0296 0.1214 1.0000
6.250 0.7494 0.08648 0.08080 -0.0380 0.1022 1.0000
6.750 0.7686 0.09621 0.09056 -0.0410 0.0928 1.0000
7.250 0.7843 0.10503 0.09943 -0.0471 0.0821 1.0000
7.500 0.7903 0.11036 0.10471 -0.0487 0.0803 1.0000
7.750 0.7896 0.11349 0.10779 -0.0568 0.0784 1.0000
8.000 0.7900 0.11709 0.11133 -0.0605 0.0752 1.0000
8.250 0.7931 0.12108 0.11529 -0.0623 0.0721 1.0000
8.500 0.8087 0.12904 0.12328 -0.0564 0.0677 1.0000
8.750 0.8071 0.13202 0.12619 -0.0611 0.0674 1.0000
9.000 0.8052 0.13477 0.12886 -0.0654 0.0668 1.0000
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Polar data table (+)
Polar graphs
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