RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.54 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1410-il-1000000-n5.txt Download as CSV file: xf-rg1410-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 10% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0841 0.05849 0.05594 -0.0507 1.0000 0.0049
-15.500 -1.1371 0.04357 0.04067 -0.0636 1.0000 0.0048
-15.250 -1.1500 0.03885 0.03580 -0.0664 1.0000 0.0048
-15.000 -1.1635 0.03511 0.03189 -0.0671 1.0000 0.0048
-14.750 -1.1701 0.03263 0.02927 -0.0664 1.0000 0.0049
-14.500 -1.1736 0.03072 0.02725 -0.0647 1.0000 0.0049
-14.250 -1.1786 0.02905 0.02544 -0.0621 1.0000 0.0049
-14.000 -1.1808 0.02785 0.02414 -0.0587 1.0000 0.0050
-13.750 -1.1777 0.02677 0.02296 -0.0557 1.0000 0.0052
-13.500 -1.1705 0.02567 0.02175 -0.0534 1.0000 0.0053
-13.250 -1.1611 0.02465 0.02062 -0.0512 1.0000 0.0054
-13.000 -1.1501 0.02369 0.01956 -0.0492 1.0000 0.0055
-12.750 -1.1378 0.02279 0.01855 -0.0472 1.0000 0.0056
-12.500 -1.1244 0.02193 0.01758 -0.0453 1.0000 0.0057
-12.250 -1.1099 0.02114 0.01670 -0.0435 1.0000 0.0058
-12.000 -1.0954 0.02030 0.01575 -0.0416 1.0000 0.0060
-11.750 -1.0802 0.01949 0.01486 -0.0398 1.0000 0.0064
-11.500 -1.0633 0.01884 0.01415 -0.0382 1.0000 0.0066
-11.250 -1.0452 0.01830 0.01356 -0.0368 1.0000 0.0069
-11.000 -1.0272 0.01772 0.01293 -0.0352 1.0000 0.0072
-10.750 -1.0088 0.01721 0.01235 -0.0338 1.0000 0.0075
-10.500 -0.9816 0.01667 0.01175 -0.0341 0.9992 0.0079
-10.250 -0.9526 0.01610 0.01109 -0.0348 0.9980 0.0082
-10.000 -0.9230 0.01559 0.01051 -0.0356 0.9966 0.0084
-9.750 -0.8930 0.01505 0.00994 -0.0365 0.9953 0.0091
-9.500 -0.8619 0.01465 0.00952 -0.0376 0.9942 0.0097
-9.250 -0.8333 0.01425 0.00909 -0.0380 0.9925 0.0102
-9.000 -0.8043 0.01385 0.00863 -0.0385 0.9904 0.0107
-8.750 -0.7746 0.01346 0.00819 -0.0391 0.9885 0.0112
-8.500 -0.7440 0.01311 0.00779 -0.0399 0.9867 0.0115
-8.250 -0.7132 0.01264 0.00726 -0.0409 0.9851 0.0120
-8.000 -0.6814 0.01219 0.00679 -0.0420 0.9837 0.0128
-7.750 -0.6535 0.01188 0.00646 -0.0421 0.9805 0.0135
-7.500 -0.6248 0.01155 0.00610 -0.0424 0.9768 0.0141
-7.250 -0.5938 0.01122 0.00573 -0.0432 0.9738 0.0147
-7.000 -0.5614 0.01090 0.00538 -0.0443 0.9715 0.0152
-6.750 -0.5327 0.01065 0.00510 -0.0446 0.9668 0.0156
-6.500 -0.5040 0.01024 0.00464 -0.0448 0.9614 0.0164
-6.250 -0.4720 0.00987 0.00426 -0.0458 0.9574 0.0173
-6.000 -0.4426 0.00958 0.00395 -0.0462 0.9509 0.0182
-5.750 -0.4108 0.00931 0.00365 -0.0471 0.9445 0.0191
-5.500 -0.3803 0.00906 0.00336 -0.0477 0.9361 0.0199
-5.250 -0.3498 0.00885 0.00310 -0.0482 0.9264 0.0205
-5.000 -0.3213 0.00862 0.00283 -0.0483 0.9139 0.0221
-4.750 -0.2941 0.00843 0.00260 -0.0481 0.8999 0.0244
-4.500 -0.2672 0.00828 0.00241 -0.0478 0.8858 0.0271
-4.250 -0.2408 0.00810 0.00222 -0.0475 0.8717 0.0335
-4.000 -0.2146 0.00793 0.00205 -0.0471 0.8578 0.0436
-3.750 -0.1884 0.00779 0.00189 -0.0467 0.8436 0.0541
-3.500 -0.1622 0.00766 0.00176 -0.0463 0.8287 0.0647
-3.250 -0.1360 0.00755 0.00163 -0.0459 0.8128 0.0768
-3.000 -0.1100 0.00744 0.00152 -0.0454 0.7962 0.0920
-2.750 -0.0840 0.00731 0.00140 -0.0450 0.7791 0.1126
-2.500 -0.0581 0.00718 0.00131 -0.0446 0.7615 0.1384
-2.250 -0.0323 0.00703 0.00121 -0.0442 0.7439 0.1708
-2.000 -0.0064 0.00691 0.00113 -0.0438 0.7259 0.2035
-1.750 0.0193 0.00677 0.00107 -0.0434 0.7080 0.2433
-1.500 0.0450 0.00665 0.00101 -0.0429 0.6883 0.2847
-1.250 0.0702 0.00656 0.00096 -0.0424 0.6622 0.3305
-1.000 0.0958 0.00648 0.00092 -0.0420 0.6380 0.3726
-0.750 0.1212 0.00633 0.00089 -0.0415 0.6176 0.4343
-0.500 0.1465 0.00617 0.00087 -0.0411 0.5982 0.4989
-0.250 0.1717 0.00604 0.00086 -0.0406 0.5757 0.5627
0.000 0.1967 0.00593 0.00086 -0.0400 0.5515 0.6275
0.250 0.2216 0.00579 0.00088 -0.0394 0.5325 0.6956
0.500 0.2468 0.00575 0.00095 -0.0388 0.5141 0.7525
0.750 0.2729 0.00578 0.00101 -0.0383 0.4973 0.7847
1.000 0.2995 0.00585 0.00106 -0.0380 0.4808 0.8047
1.250 0.3260 0.00595 0.00111 -0.0376 0.4596 0.8180
1.500 0.3523 0.00609 0.00118 -0.0372 0.4350 0.8290
1.750 0.3786 0.00621 0.00125 -0.0368 0.4131 0.8406
2.000 0.4050 0.00634 0.00133 -0.0365 0.3940 0.8515
2.250 0.4309 0.00649 0.00141 -0.0360 0.3682 0.8602
2.750 0.4818 0.00691 0.00163 -0.0351 0.3072 0.8771
3.000 0.5074 0.00709 0.00174 -0.0346 0.2834 0.8868
3.250 0.5326 0.00728 0.00186 -0.0340 0.2600 0.8968
3.500 0.5571 0.00751 0.00201 -0.0333 0.2321 0.9067
3.750 0.5815 0.00772 0.00215 -0.0326 0.2072 0.9175
4.000 0.6057 0.00797 0.00231 -0.0319 0.1807 0.9279
4.250 0.6301 0.00821 0.00249 -0.0312 0.1599 0.9363
4.500 0.6554 0.00842 0.00265 -0.0307 0.1470 0.9443
4.750 0.6816 0.00859 0.00281 -0.0303 0.1380 0.9529
5.000 0.7092 0.00878 0.00298 -0.0303 0.1283 0.9613
5.500 0.7682 0.00928 0.00338 -0.0313 0.1000 0.9775
5.750 0.7986 0.00956 0.00360 -0.0321 0.0873 0.9846
6.000 0.8299 0.00984 0.00384 -0.0331 0.0781 0.9910
6.250 0.8606 0.01013 0.00409 -0.0339 0.0700 0.9986
6.500 0.8858 0.01036 0.00432 -0.0335 0.0646 1.0000
6.750 0.9091 0.01066 0.00458 -0.0327 0.0578 1.0000
7.000 0.9332 0.01091 0.00482 -0.0321 0.0535 1.0000
7.250 0.9567 0.01122 0.00511 -0.0314 0.0477 1.0000
7.500 0.9807 0.01150 0.00539 -0.0308 0.0431 1.0000
7.750 1.0040 0.01185 0.00571 -0.0301 0.0375 1.0000
8.000 1.0277 0.01217 0.00602 -0.0295 0.0335 1.0000
8.250 1.0509 0.01252 0.00637 -0.0288 0.0297 1.0000
8.500 1.0742 0.01287 0.00672 -0.0281 0.0270 1.0000
8.750 1.0975 0.01321 0.00707 -0.0274 0.0248 1.0000
9.000 1.1197 0.01363 0.00748 -0.0266 0.0216 1.0000
9.250 1.1426 0.01398 0.00786 -0.0259 0.0201 1.0000
9.500 1.1647 0.01439 0.00829 -0.0250 0.0180 1.0000
9.750 1.1864 0.01483 0.00873 -0.0242 0.0161 1.0000
10.000 1.2082 0.01524 0.00917 -0.0233 0.0144 1.0000
10.250 1.2285 0.01575 0.00969 -0.0223 0.0124 1.0000
10.500 1.2490 0.01623 0.01019 -0.0212 0.0106 1.0000
10.750 1.2682 0.01679 0.01077 -0.0201 0.0088 1.0000
11.000 1.2874 0.01732 0.01135 -0.0189 0.0080 1.0000
11.250 1.3049 0.01795 0.01200 -0.0174 0.0068 1.0000
11.500 1.3223 0.01855 0.01265 -0.0160 0.0062 1.0000
11.750 1.3392 0.01913 0.01329 -0.0145 0.0059 1.0000
12.000 1.3535 0.01972 0.01394 -0.0125 0.0056 1.0000
12.250 1.3663 0.02035 0.01463 -0.0103 0.0054 1.0000
12.500 1.3779 0.02104 0.01538 -0.0081 0.0051 1.0000
12.750 1.3886 0.02181 0.01622 -0.0058 0.0048 1.0000
13.000 1.3985 0.02263 0.01712 -0.0035 0.0047 1.0000
13.250 1.4058 0.02364 0.01821 -0.0011 0.0044 1.0000
13.500 1.4125 0.02472 0.01938 0.0011 0.0042 1.0000
13.750 1.4209 0.02571 0.02045 0.0031 0.0041 1.0000
14.000 1.4279 0.02683 0.02166 0.0049 0.0041 1.0000
14.250 1.4335 0.02811 0.02303 0.0067 0.0040 1.0000
14.500 1.4378 0.02956 0.02458 0.0083 0.0039 1.0000
14.750 1.4423 0.03108 0.02619 0.0097 0.0038 1.0000
15.000 1.4441 0.03292 0.02813 0.0109 0.0038 1.0000
15.250 1.4452 0.03494 0.03027 0.0118 0.0037 1.0000
15.500 1.4438 0.03736 0.03279 0.0125 0.0036 1.0000
15.750 1.4440 0.03976 0.03529 0.0127 0.0036 1.0000
16.000 1.4399 0.04281 0.03847 0.0126 0.0035 1.0000
16.250 1.4347 0.04619 0.04197 0.0121 0.0034 1.0000
16.500 1.4278 0.05003 0.04592 0.0111 0.0034 1.0000
16.750 1.4198 0.05424 0.05025 0.0096 0.0033 1.0000
17.000 1.4078 0.05927 0.05542 0.0075 0.0033 1.0000
17.250 1.3937 0.06494 0.06124 0.0049 0.0033 1.0000
17.500 1.3776 0.07123 0.06765 0.0017 0.0032 1.0000
17.750 1.3581 0.07843 0.07501 -0.0021 0.0033 1.0000
18.000 1.3293 0.08766 0.08441 -0.0073 0.0033 1.0000
18.250 1.3001 0.09742 0.09434 -0.0128 0.0033 1.0000
18.500 1.2661 0.10848 0.10557 -0.0191 0.0033 1.0000
18.750 1.2276 0.12097 0.11824 -0.0263 0.0034 1.0000
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Polar data table (+)
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