NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 100,000 Max Cl/Cd: 24.38 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20403-il-100000.txt Download as CSV file: xf-sc20403-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0403 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6872 0.11935 0.11450 0.0253 1.0000 0.0486
-9.000 -0.6868 0.11638 0.11159 0.0210 1.0000 0.0491
-8.750 -0.6863 0.11321 0.10847 0.0165 1.0000 0.0493
-8.500 -0.6843 0.10957 0.10488 0.0108 1.0000 0.0495
-8.250 -0.6756 0.10245 0.09764 0.0179 1.0000 0.0516
-8.000 -0.6695 0.09846 0.09366 0.0182 1.0000 0.0539
-7.750 -0.6656 0.09460 0.08984 0.0160 1.0000 0.0560
-7.500 -0.6588 0.09025 0.08552 0.0113 1.0000 0.0584
-7.250 -0.6472 0.08519 0.08045 0.0018 1.0000 0.0610
-7.000 -0.6287 0.08083 0.07579 -0.0120 1.0000 0.0625
-6.750 -0.6239 0.07456 0.06972 -0.0083 1.0000 0.0647
-6.500 -0.6121 0.07053 0.06569 -0.0086 1.0000 0.0691
-6.250 -0.5837 0.06651 0.06105 -0.0207 1.0000 0.0759
-6.000 -0.5763 0.06064 0.05553 -0.0175 1.0000 0.0798
-5.750 -0.5202 0.04301 0.03818 -0.0200 1.0000 0.0931
-5.500 -0.5025 0.03792 0.03285 -0.0233 1.0000 0.1045
-5.250 -0.4848 0.03353 0.02832 -0.0248 1.0000 0.1182
-5.000 -0.4890 0.04386 0.03802 -0.0277 1.0000 0.1325
-4.750 -0.4669 0.04045 0.03451 -0.0288 1.0000 0.1608
-4.250 -0.4227 0.03420 0.02791 -0.0298 1.0000 0.2487
-4.000 -0.3481 0.02796 0.01965 -0.0327 1.0000 0.0608
-3.750 -0.3157 0.02423 0.01520 -0.0324 1.0000 0.0439
-3.500 -0.2850 0.02168 0.01217 -0.0321 1.0000 0.0418
-3.250 -0.2552 0.02062 0.01064 -0.0316 1.0000 0.0494
-3.000 -0.2267 0.01836 0.00820 -0.0309 1.0000 0.0494
-2.750 -0.1997 0.01600 0.00593 -0.0303 1.0000 0.0522
-2.500 -0.1717 0.01458 0.00450 -0.0299 1.0000 0.0621
-2.250 -0.1540 0.01029 0.00328 -0.0278 1.0000 0.7423
-2.000 -0.1533 0.00947 0.00272 -0.0182 1.0000 1.0000
-1.750 -0.1242 0.00940 0.00227 -0.0188 1.0000 1.0000
-1.500 -0.0954 0.00935 0.00195 -0.0193 1.0000 1.0000
-1.250 -0.0669 0.00931 0.00172 -0.0197 1.0000 1.0000
-1.000 -0.0385 0.00929 0.00151 -0.0201 1.0000 1.0000
-0.750 -0.0105 0.00929 0.00139 -0.0204 1.0000 1.0000
-0.500 0.0174 0.00929 0.00133 -0.0206 1.0000 1.0000
-0.250 0.0451 0.00930 0.00132 -0.0207 1.0000 1.0000
0.000 0.0726 0.00932 0.00136 -0.0209 1.0000 1.0000
0.250 0.1000 0.00936 0.00145 -0.0209 1.0000 1.0000
0.500 0.1274 0.00940 0.00159 -0.0210 1.0000 1.0000
0.750 0.1546 0.00945 0.00184 -0.0209 1.0000 1.0000
1.000 0.1817 0.00951 0.00209 -0.0209 1.0000 1.0000
1.250 0.2088 0.00959 0.00243 -0.0208 1.0000 1.0000
1.500 0.2360 0.00968 0.00292 -0.0206 1.0000 1.0000
1.750 0.2956 0.01515 0.00522 -0.0254 0.0564 1.0000
2.000 0.3219 0.01702 0.00697 -0.0246 0.0497 1.0000
2.250 0.3504 0.01945 0.00944 -0.0240 0.0486 1.0000
2.500 0.3799 0.02193 0.01216 -0.0234 0.0489 1.0000
2.750 0.4099 0.02295 0.01372 -0.0226 0.0420 1.0000
3.000 0.4395 0.02580 0.01701 -0.0219 0.0456 1.0000
3.250 0.4727 0.02970 0.02153 -0.0205 0.0731 1.0000
4.750 0.6386 0.05206 0.04679 -0.0218 0.0937 1.0000
5.000 0.6522 0.05797 0.05239 -0.0211 0.0883 1.0000
5.250 0.6764 0.06045 0.05546 -0.0237 0.0772 1.0000
5.500 0.6953 0.06548 0.06074 -0.0266 0.0719 1.0000
5.750 0.7134 0.06975 0.06517 -0.0290 0.0656 1.0000
6.000 0.7201 0.07558 0.07077 -0.0263 0.0622 1.0000
6.250 0.7375 0.08014 0.07568 -0.0325 0.0606 1.0000
6.500 0.7547 0.08483 0.08056 -0.0401 0.0568 1.0000
6.750 0.7651 0.08959 0.08536 -0.0440 0.0541 1.0000
7.000 0.7731 0.09410 0.08989 -0.0460 0.0517 1.0000
7.250 0.7741 0.10158 0.09726 -0.0360 0.0488 1.0000
7.500 0.7820 0.10575 0.10155 -0.0416 0.0486 1.0000
7.750 0.7884 0.11000 0.10586 -0.0485 0.0484 1.0000
8.000 0.7903 0.11397 0.10981 -0.0552 0.0481 1.0000
8.250 0.7903 0.11757 0.11336 -0.0605 0.0476 1.0000
8.500 0.7908 0.12113 0.11687 -0.0648 0.0468 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0403 AIRFOIL (sc20403-il)