S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 500,000 Max Cl/Cd: 60.86 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9026-il-500000.txt Download as CSV file: xf-s9026-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S9026 (9.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9304 0.10873 0.10623 0.0093 1.0000 0.0141
-15.000 -0.9852 0.09205 0.08935 -0.0011 1.0000 0.0135
-14.750 -1.0263 0.07929 0.07639 -0.0094 1.0000 0.0132
-14.500 -1.0579 0.06908 0.06598 -0.0162 1.0000 0.0129
-14.250 -1.0797 0.06118 0.05789 -0.0217 1.0000 0.0129
-14.000 -1.0954 0.05481 0.05136 -0.0260 1.0000 0.0129
-13.750 -1.1098 0.04925 0.04562 -0.0295 1.0000 0.0131
-13.500 -1.1176 0.04519 0.04141 -0.0316 1.0000 0.0133
-13.250 -1.1257 0.04159 0.03764 -0.0328 1.0000 0.0136
-13.000 -1.1327 0.03856 0.03444 -0.0329 1.0000 0.0138
-12.750 -1.1344 0.03645 0.03218 -0.0322 1.0000 0.0142
-12.500 -1.1365 0.03450 0.03007 -0.0307 1.0000 0.0145
-12.250 -1.1322 0.03338 0.02880 -0.0288 1.0000 0.0148
-12.000 -1.1436 0.03058 0.02576 -0.0253 1.0000 0.0153
-11.750 -1.1419 0.02845 0.02349 -0.0230 1.0000 0.0160
-11.500 -1.1271 0.02770 0.02272 -0.0218 1.0000 0.0168
-11.250 -1.1109 0.02696 0.02192 -0.0207 1.0000 0.0176
-11.000 -1.0953 0.02594 0.02077 -0.0194 1.0000 0.0184
-10.750 -1.0774 0.02512 0.01981 -0.0183 1.0000 0.0193
-10.500 -1.0579 0.02443 0.01899 -0.0174 1.0000 0.0199
-10.250 -1.0468 0.02221 0.01657 -0.0156 1.0000 0.0209
-10.000 -1.0293 0.02108 0.01537 -0.0145 1.0000 0.0220
-9.750 -1.0082 0.02045 0.01470 -0.0137 1.0000 0.0232
-9.500 -0.9870 0.01975 0.01393 -0.0128 1.0000 0.0243
-9.250 -0.9655 0.01904 0.01312 -0.0120 1.0000 0.0253
-9.000 -0.9427 0.01851 0.01249 -0.0112 1.0000 0.0263
-8.750 -0.9240 0.01731 0.01117 -0.0099 1.0000 0.0275
-8.500 -0.9044 0.01630 0.01011 -0.0088 1.0000 0.0292
-8.250 -0.8817 0.01574 0.00952 -0.0080 1.0000 0.0309
-8.000 -0.8586 0.01523 0.00896 -0.0072 1.0000 0.0327
-7.750 -0.8353 0.01474 0.00838 -0.0064 1.0000 0.0343
-7.500 -0.8147 0.01387 0.00744 -0.0052 1.0000 0.0372
-7.250 -0.7920 0.01332 0.00690 -0.0043 1.0000 0.0409
-7.000 -0.7680 0.01299 0.00651 -0.0035 1.0000 0.0446
-6.750 -0.7464 0.01233 0.00589 -0.0024 1.0000 0.0522
-6.500 -0.7233 0.01191 0.00545 -0.0015 1.0000 0.0591
-6.250 -0.7001 0.01154 0.00509 -0.0006 1.0000 0.0667
-6.000 -0.6772 0.01113 0.00471 0.0003 1.0000 0.0752
-5.750 -0.6538 0.01081 0.00439 0.0012 1.0000 0.0842
-5.500 -0.6304 0.01050 0.00411 0.0021 1.0000 0.0948
-5.250 -0.6075 0.01016 0.00382 0.0030 1.0000 0.1085
-5.000 -0.5847 0.00981 0.00356 0.0040 1.0000 0.1251
-4.750 -0.5620 0.00949 0.00333 0.0050 1.0000 0.1443
-4.500 -0.5394 0.00919 0.00312 0.0060 1.0000 0.1668
-4.000 -0.4948 0.00862 0.00277 0.0080 1.0000 0.2178
-3.750 -0.4728 0.00838 0.00263 0.0091 1.0000 0.2431
-3.500 -0.4509 0.00816 0.00251 0.0102 1.0000 0.2706
-3.250 -0.4110 0.00789 0.00240 0.0074 0.9957 0.3110
-3.000 -0.3722 0.00763 0.00229 0.0050 0.9909 0.3505
-2.750 -0.3339 0.00738 0.00219 0.0027 0.9856 0.3895
-2.500 -0.2955 0.00710 0.00210 0.0004 0.9807 0.4367
-2.250 -0.2590 0.00682 0.00201 -0.0014 0.9735 0.4857
-2.000 -0.2228 0.00657 0.00192 -0.0031 0.9651 0.5287
-1.750 -0.1881 0.00634 0.00183 -0.0043 0.9541 0.5689
-1.500 -0.1566 0.00613 0.00176 -0.0048 0.9394 0.6075
-1.250 -0.1274 0.00596 0.00170 -0.0047 0.9217 0.6445
-1.000 -0.1005 0.00582 0.00165 -0.0041 0.9011 0.6807
-0.750 -0.0751 0.00573 0.00162 -0.0032 0.8784 0.7159
-0.500 -0.0501 0.00568 0.00159 -0.0021 0.8532 0.7472
-0.250 -0.0251 0.00565 0.00158 -0.0010 0.8269 0.7745
0.000 0.0000 0.00565 0.00157 0.0000 0.8004 0.8003
0.250 0.0251 0.00565 0.00158 0.0010 0.7745 0.8268
0.500 0.0501 0.00568 0.00159 0.0021 0.7472 0.8532
0.750 0.0751 0.00573 0.00162 0.0032 0.7159 0.8784
1.000 0.1006 0.00582 0.00165 0.0041 0.6809 0.9011
1.250 0.1274 0.00596 0.00170 0.0047 0.6443 0.9215
1.500 0.1566 0.00613 0.00176 0.0048 0.6075 0.9394
1.750 0.1881 0.00634 0.00183 0.0043 0.5687 0.9542
2.000 0.2228 0.00657 0.00192 0.0031 0.5286 0.9650
2.250 0.2589 0.00682 0.00201 0.0014 0.4859 0.9734
2.500 0.2956 0.00710 0.00210 -0.0004 0.4365 0.9807
2.750 0.3339 0.00737 0.00219 -0.0027 0.3899 0.9856
3.000 0.3721 0.00763 0.00229 -0.0050 0.3505 0.9908
3.250 0.4109 0.00789 0.00240 -0.0074 0.3109 0.9956
3.500 0.4509 0.00816 0.00251 -0.0101 0.2702 0.9999
3.750 0.4731 0.00838 0.00263 -0.0091 0.2431 1.0000
4.000 0.4951 0.00862 0.00277 -0.0081 0.2177 1.0000
4.500 0.5396 0.00919 0.00313 -0.0060 0.1667 1.0000
4.750 0.5622 0.00949 0.00333 -0.0050 0.1441 1.0000
5.000 0.5849 0.00981 0.00356 -0.0040 0.1250 1.0000
5.250 0.6077 0.01016 0.00382 -0.0031 0.1086 1.0000
5.500 0.6306 0.01050 0.00411 -0.0021 0.0948 1.0000
5.750 0.6540 0.01081 0.00440 -0.0013 0.0841 1.0000
6.000 0.6774 0.01113 0.00471 -0.0004 0.0752 1.0000
6.250 0.7003 0.01154 0.00509 0.0006 0.0667 1.0000
6.500 0.7234 0.01192 0.00546 0.0015 0.0590 1.0000
6.750 0.7465 0.01233 0.00589 0.0024 0.0521 1.0000
7.000 0.7682 0.01298 0.00650 0.0035 0.0445 1.0000
7.250 0.7921 0.01333 0.00691 0.0043 0.0409 1.0000
7.500 0.8147 0.01388 0.00745 0.0052 0.0371 1.0000
7.750 0.8353 0.01473 0.00837 0.0064 0.0343 1.0000
8.000 0.8586 0.01522 0.00895 0.0072 0.0327 1.0000
8.250 0.8816 0.01574 0.00952 0.0080 0.0309 1.0000
8.500 0.9042 0.01630 0.01011 0.0088 0.0292 1.0000
8.750 0.9238 0.01731 0.01117 0.0100 0.0275 1.0000
9.000 0.9427 0.01848 0.01245 0.0112 0.0263 1.0000
9.250 0.9653 0.01903 0.01311 0.0120 0.0253 1.0000
9.500 0.9868 0.01975 0.01392 0.0129 0.0243 1.0000
9.750 1.0080 0.02044 0.01470 0.0137 0.0232 1.0000
10.000 1.0288 0.02111 0.01541 0.0146 0.0221 1.0000
10.250 1.0465 0.02220 0.01656 0.0157 0.0210 1.0000
10.500 1.0579 0.02435 0.01891 0.0174 0.0199 1.0000
10.750 1.0771 0.02511 0.01980 0.0184 0.0193 1.0000
11.000 1.0944 0.02602 0.02086 0.0195 0.0185 1.0000
11.250 1.1110 0.02689 0.02184 0.0207 0.0176 1.0000
11.500 1.1271 0.02766 0.02267 0.0218 0.0168 1.0000
11.750 1.1406 0.02859 0.02366 0.0231 0.0161 1.0000
12.000 1.1439 0.03052 0.02570 0.0253 0.0153 1.0000
12.250 1.1325 0.03333 0.02875 0.0288 0.0148 1.0000
12.500 1.1333 0.03485 0.03043 0.0309 0.0146 1.0000
12.750 1.1336 0.03653 0.03226 0.0323 0.0142 1.0000
13.000 1.1299 0.03889 0.03479 0.0330 0.0139 1.0000
13.250 1.1246 0.04173 0.03779 0.0328 0.0136 1.0000
13.500 1.1160 0.04542 0.04165 0.0315 0.0134 1.0000
13.750 1.1071 0.04966 0.04605 0.0293 0.0132 1.0000
14.000 1.0934 0.05516 0.05172 0.0258 0.0131 1.0000
14.250 1.0799 0.06120 0.05792 0.0216 0.0129 1.0000
14.500 1.0527 0.07007 0.06700 0.0156 0.0132 1.0000
14.750 1.0205 0.08053 0.07766 0.0085 0.0133 1.0000
15.000 0.9839 0.09240 0.08970 0.0008 0.0136 1.0000
15.250 0.9263 0.10978 0.10728 -0.0100 0.0143 1.0000
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Polar data table (+)
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