N-13 (n13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: N-13 (n13-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.06 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n13-il-1000000.txt Download as CSV file: xf-n13-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: N-13
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0399 0.10012 0.09730 -0.0234 1.0000 0.0079
-17.500 -1.0572 0.09302 0.09010 -0.0270 1.0000 0.0079
-17.250 -1.0881 0.08393 0.08086 -0.0315 1.0000 0.0078
-17.000 -1.1011 0.07782 0.07462 -0.0347 1.0000 0.0079
-16.750 -1.1131 0.07210 0.06879 -0.0377 1.0000 0.0079
-16.500 -1.1302 0.06587 0.06243 -0.0407 1.0000 0.0079
-16.250 -1.1408 0.06083 0.05727 -0.0431 1.0000 0.0079
-16.000 -1.1505 0.05613 0.05244 -0.0451 1.0000 0.0079
-15.750 -1.1618 0.05153 0.04771 -0.0468 1.0000 0.0079
-15.500 -1.1799 0.04639 0.04240 -0.0482 1.0000 0.0081
-15.250 -1.1800 0.04362 0.03954 -0.0487 1.0000 0.0080
-15.000 -1.1959 0.03937 0.03512 -0.0489 1.0000 0.0082
-14.750 -1.2098 0.03568 0.03129 -0.0484 1.0000 0.0084
-14.500 -1.2141 0.03317 0.02867 -0.0473 1.0000 0.0084
-14.250 -1.2157 0.03111 0.02652 -0.0460 1.0000 0.0086
-14.000 -1.2144 0.02944 0.02477 -0.0443 1.0000 0.0088
-13.750 -1.2107 0.02806 0.02331 -0.0424 1.0000 0.0089
-13.500 -1.2074 0.02676 0.02193 -0.0402 1.0000 0.0091
-13.250 -1.2040 0.02555 0.02063 -0.0377 1.0000 0.0091
-13.000 -1.1970 0.02463 0.01965 -0.0353 1.0000 0.0094
-12.750 -1.1913 0.02369 0.01863 -0.0326 1.0000 0.0097
-12.500 -1.1850 0.02286 0.01772 -0.0297 1.0000 0.0099
-12.250 -1.1777 0.02215 0.01694 -0.0267 1.0000 0.0101
-12.000 -1.1722 0.02144 0.01615 -0.0233 1.0000 0.0102
-11.750 -1.1640 0.02093 0.01558 -0.0200 1.0000 0.0104
-11.500 -1.1588 0.02038 0.01495 -0.0161 1.0000 0.0105
-11.250 -1.1579 0.01947 0.01396 -0.0116 1.0000 0.0108
-11.000 -1.1524 0.01854 0.01295 -0.0078 1.0000 0.0113
-10.750 -1.1405 0.01795 0.01233 -0.0052 1.0000 0.0117
-10.500 -1.1277 0.01740 0.01172 -0.0026 1.0000 0.0121
-10.250 -1.1138 0.01691 0.01120 -0.0001 1.0000 0.0126
-10.000 -1.1002 0.01646 0.01069 0.0024 1.0000 0.0131
-9.750 -1.0876 0.01607 0.01025 0.0052 1.0000 0.0134
-9.500 -1.0629 0.01539 0.00950 0.0053 0.9989 0.0142
-9.250 -1.0335 0.01476 0.00884 0.0044 0.9972 0.0152
-9.000 -1.0031 0.01427 0.00832 0.0034 0.9955 0.0162
-8.750 -0.9719 0.01387 0.00786 0.0023 0.9942 0.0173
-8.500 -0.9449 0.01327 0.00728 0.0020 0.9919 0.0205
-8.250 -0.9162 0.01279 0.00685 0.0015 0.9894 0.0256
-8.000 -0.8855 0.01245 0.00658 0.0005 0.9874 0.0328
-7.750 -0.8543 0.01214 0.00630 -0.0005 0.9857 0.0379
-7.500 -0.8218 0.01196 0.00611 -0.0017 0.9846 0.0408
-7.250 -0.7939 0.01171 0.00583 -0.0020 0.9818 0.0431
-7.000 -0.7677 0.01131 0.00544 -0.0018 0.9778 0.0465
-6.750 -0.7377 0.01102 0.00512 -0.0025 0.9754 0.0489
-6.500 -0.7067 0.01077 0.00484 -0.0034 0.9737 0.0507
-6.250 -0.6750 0.01053 0.00458 -0.0044 0.9724 0.0522
-6.000 -0.6528 0.01022 0.00425 -0.0033 0.9666 0.0558
-5.750 -0.6243 0.00987 0.00393 -0.0036 0.9634 0.0608
-5.500 -0.5951 0.00946 0.00366 -0.0041 0.9610 0.0806
-5.250 -0.5646 0.00924 0.00350 -0.0048 0.9592 0.0981
-5.000 -0.5392 0.00901 0.00330 -0.0043 0.9540 0.1064
-4.750 -0.5082 0.00884 0.00313 -0.0050 0.9511 0.1116
-4.500 -0.4748 0.00865 0.00293 -0.0063 0.9491 0.1164
-4.250 -0.4402 0.00842 0.00273 -0.0079 0.9472 0.1225
-4.000 -0.4067 0.00825 0.00257 -0.0092 0.9440 0.1263
-3.750 -0.3697 0.00805 0.00239 -0.0113 0.9401 0.1333
-3.500 -0.3272 0.00778 0.00219 -0.0148 0.9360 0.1487
-3.250 -0.2884 0.00737 0.00198 -0.0175 0.9310 0.1985
-3.000 -0.2552 0.00703 0.00180 -0.0189 0.9243 0.2437
-2.750 -0.2230 0.00654 0.00161 -0.0203 0.9181 0.3256
-2.500 -0.1989 0.00629 0.00153 -0.0195 0.9103 0.3767
-2.250 -0.1693 0.00608 0.00145 -0.0201 0.9033 0.4212
-2.000 -0.1483 0.00589 0.00140 -0.0186 0.8952 0.4611
-1.750 -0.1230 0.00572 0.00135 -0.0180 0.8874 0.5008
-1.500 -0.1017 0.00558 0.00132 -0.0165 0.8787 0.5341
-1.250 -0.0782 0.00546 0.00129 -0.0154 0.8705 0.5678
-1.000 -0.0560 0.00534 0.00126 -0.0141 0.8606 0.5988
-0.750 -0.0346 0.00522 0.00123 -0.0125 0.8476 0.6277
-0.500 -0.0134 0.00513 0.00118 -0.0109 0.8282 0.6524
-0.250 0.0067 0.00510 0.00110 -0.0090 0.7880 0.6707
0.000 0.0258 0.00518 0.00105 -0.0068 0.7450 0.6863
0.250 0.0471 0.00525 0.00106 -0.0053 0.7209 0.7026
0.500 0.0699 0.00527 0.00108 -0.0041 0.7042 0.7193
0.750 0.0929 0.00529 0.00110 -0.0029 0.6889 0.7366
1.000 0.1158 0.00529 0.00113 -0.0017 0.6742 0.7555
1.250 0.1383 0.00526 0.00116 -0.0004 0.6606 0.7780
1.500 0.1605 0.00525 0.00119 0.0010 0.6425 0.8025
1.750 0.1821 0.00524 0.00124 0.0025 0.6173 0.8332
2.000 0.2048 0.00530 0.00132 0.0038 0.5859 0.8647
2.250 0.2289 0.00547 0.00143 0.0048 0.5416 0.8902
2.500 0.2502 0.00579 0.00157 0.0063 0.4771 0.9103
2.750 0.2729 0.00610 0.00171 0.0074 0.4305 0.9234
3.000 0.3007 0.00640 0.00188 0.0074 0.3912 0.9320
3.250 0.3237 0.00664 0.00202 0.0085 0.3590 0.9413
3.500 0.3546 0.00694 0.00219 0.0078 0.3223 0.9465
3.750 0.3755 0.00719 0.00233 0.0093 0.2913 0.9545
4.000 0.4101 0.00757 0.00256 0.0077 0.2517 0.9578
4.250 0.4451 0.00799 0.00281 0.0060 0.2121 0.9606
4.500 0.4849 0.00845 0.00313 0.0033 0.1802 0.9650
4.750 0.5121 0.00878 0.00338 0.0034 0.1564 0.9701
5.000 0.5484 0.00919 0.00364 0.0013 0.1267 0.9712
5.250 0.5829 0.00956 0.00390 -0.0003 0.1019 0.9725
5.500 0.6159 0.00994 0.00417 -0.0017 0.0839 0.9740
5.750 0.6482 0.01026 0.00443 -0.0028 0.0729 0.9758
6.000 0.6789 0.01052 0.00468 -0.0035 0.0657 0.9782
6.250 0.7022 0.01087 0.00499 -0.0026 0.0584 0.9821
6.500 0.7348 0.01107 0.00521 -0.0038 0.0547 0.9834
6.750 0.7679 0.01140 0.00549 -0.0052 0.0493 0.9844
7.000 0.8011 0.01165 0.00576 -0.0066 0.0459 0.9856
7.250 0.8333 0.01191 0.00602 -0.0077 0.0427 0.9871
7.500 0.8634 0.01230 0.00639 -0.0085 0.0385 0.9889
7.750 0.8941 0.01251 0.00663 -0.0093 0.0363 0.9907
8.000 0.9218 0.01284 0.00693 -0.0095 0.0330 0.9927
8.250 0.9503 0.01319 0.00730 -0.0099 0.0302 0.9943
8.500 0.9816 0.01349 0.00758 -0.0110 0.0270 0.9954
8.750 1.0115 0.01390 0.00800 -0.0118 0.0242 0.9968
9.000 1.0411 0.01425 0.00836 -0.0125 0.0219 0.9982
9.250 1.0696 0.01476 0.00889 -0.0131 0.0196 0.9996
9.500 1.0917 0.01510 0.00925 -0.0122 0.0183 1.0000
9.750 1.1061 0.01549 0.00966 -0.0098 0.0172 1.0000
10.000 1.1160 0.01614 0.01035 -0.0065 0.0159 1.0000
10.250 1.1305 0.01646 0.01073 -0.0041 0.0155 1.0000
10.500 1.1429 0.01688 0.01120 -0.0012 0.0149 1.0000
10.750 1.1551 0.01727 0.01163 0.0016 0.0143 1.0000
11.000 1.1649 0.01774 0.01215 0.0048 0.0138 1.0000
11.250 1.1718 0.01832 0.01277 0.0085 0.0132 1.0000
11.500 1.1702 0.01916 0.01368 0.0138 0.0125 1.0000
11.750 1.1730 0.01953 0.01411 0.0183 0.0124 1.0000
12.000 1.1773 0.01994 0.01459 0.0225 0.0122 1.0000
12.250 1.1825 0.02047 0.01520 0.0263 0.0119 1.0000
12.500 1.1914 0.02095 0.01573 0.0294 0.0115 1.0000
12.750 1.1983 0.02161 0.01645 0.0325 0.0113 1.0000
13.000 1.2053 0.02235 0.01726 0.0355 0.0110 1.0000
13.250 1.2134 0.02310 0.01807 0.0380 0.0107 1.0000
13.500 1.2186 0.02408 0.01911 0.0407 0.0103 1.0000
13.750 1.2214 0.02528 0.02039 0.0434 0.0101 1.0000
14.000 1.2113 0.02742 0.02266 0.0469 0.0097 1.0000
14.250 1.2085 0.02925 0.02461 0.0493 0.0096 1.0000
14.500 1.2163 0.03041 0.02586 0.0506 0.0096 1.0000
14.750 1.2208 0.03192 0.02747 0.0518 0.0094 1.0000
15.000 1.2236 0.03369 0.02934 0.0528 0.0093 1.0000
15.250 1.2207 0.03614 0.03191 0.0536 0.0092 1.0000
15.500 1.2217 0.03842 0.03430 0.0538 0.0091 1.0000
15.750 1.2175 0.04142 0.03742 0.0536 0.0089 1.0000
16.000 1.2168 0.04424 0.04034 0.0530 0.0087 1.0000
16.250 1.2074 0.04828 0.04451 0.0518 0.0086 1.0000
16.500 1.1947 0.05307 0.04945 0.0499 0.0086 1.0000
16.750 1.1798 0.05857 0.05509 0.0472 0.0086 1.0000
17.000 1.1701 0.06368 0.06031 0.0445 0.0084 1.0000
17.250 1.1476 0.07101 0.06780 0.0405 0.0086 1.0000
17.500 1.1286 0.07791 0.07483 0.0368 0.0086 1.0000
17.750 1.1022 0.08629 0.08334 0.0324 0.0084 1.0000
18.000 1.0792 0.09418 0.09136 0.0282 0.0084 1.0000
18.250 1.0437 0.10434 0.10167 0.0230 0.0086 1.0000
18.500 1.0194 0.11287 0.11031 0.0185 0.0086 1.0000
|
Polar data table (+)
Polar graphs
<< Back to N-13 (n13-il)